34034 Federal Register / Vol. 83, No. 139 / Thursday, July 19, 2018 / Rules and Regulations 

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 International 

Branch, send it to the attention of the person 

identified in paragraph (l)(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 the 

European Aviation Safety Agency (EASA); or 

EASA Design Organization Approval (DOA). 

If approved by the DOA, the approval must 

include the DOA-authorized signature. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2017–0223R1, dated December 15, 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–2018–0166. 

(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. 

(m) 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) ATR72 Time Limits document, Revision 

15, dated May 2, 2017. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact ATR–GIE Avions de 

Transport Re ́gional, 1, Alle ́e Pierre Nadot, 

31712 Blagnac Cedex, France; telephone +33 

(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; 

email continued.airworthiness@atraircraft.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 July 

3, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–14809 Filed 7–18–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–1093; Product 

Identifier 2017–NM–018–AD; Amendment 

39–19329; AD 2018–14–09] 

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 certain 

Airbus Model A318 series airplanes; 

Model A319 series airplanes; Model 

A320–211, –212, –214, –216, –231, 

–232, and –233 airplanes; and Model 

A321–111, –112, –131, –211, –212, 

–213, –231, and –232 airplanes. This AD 

was prompted by reports of early 

cracking on certain holes of the 

crossbeam splicing at certain fuselage 

frames. This AD requires repetitive 

inspections for cracking of the fastener 

holes in certain fuselage frames, and 

depending on airplane configuration, 

provides an optional terminating action 

to the repetitive inspections. We are 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective August 23, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 23, 2018. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus, Airworthiness Office—EIAS, 

Rond-Point Emile Dewoitine No: 2, 

31700 Blagnac Cedex, France; telephone 

+33 5 61 93 36 96; fax +33 5 61 93 44 

51; email account.airworth-eas@

airbus.com; internet http://

www.airbus.com. 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– 

1093. 

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– 

1093; 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; 

telephone and fax 206–231–3223. 

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 certain Airbus Model A318 

series airplanes; Model A319 series 

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

–216, –231, –232, and –233 airplanes; 

and Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

The NPRM published in the Federal 

Register on November 27, 2017 (82 FR 

55955) (‘‘the NPRM’’). The NPRM was 

prompted by reports of early cracking 

on certain holes of the crossbeam 

splicing at certain fuselage frames. The 

NPRM proposed to require repetitive 

inspections for cracking of the fastener 

holes in certain fuselage frames, and 

depending on airplane configuration, 

would provide an optional terminating 

action to the repetitive inspections. We 

are issuing this AD to address cracking 

at two upper rows of fasteners of the 

crossbeam splicing at frame (FR)16 and 

FR20, on both the left-hand (LH) and 

right-hand (RH) sides, which can result 

in reduced structural integrity of the 

airplane due to the failure of structural 

components. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2016–0139, 

dated July 14, 2016 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 


sradovich on DSK3GMQ082PROD with RULES
Federal Register / Vol. 83, No. 139 / Thursday, July 19, 2018 / Rules and Regulations 34035 

for certain Model A318 series airplanes; 

Model A319 series airplanes; Model 

A320–211, –212, –214, –216, –231, 

–232, and –233 airplanes; and Model 

A321–111, –112, –131, –211, –212, 

–213, –231, and –232 airplanes. The 

MCAI states: 

Following addition of a new airworthiness 

limitation item (ALI) task 531110 in the 

Airworthiness Limitation Section (ALS) Part 

2 in the revision dated April 2012, numerous 

findings have been reported of early cracks 

on the four holes of the crossbeam splicing 

at frame (FR)16 and FR20 on both left-hand 

(LH) and right-hand (RH) sides. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the airframe. 

To allow an earlier crack detection, Airbus 

decided to transfer the repetitive inspections 

from ALI task 531110 to Airbus Service 

Bulletin (SB) A320–53–1286, later revised, 

including new recommended inspection 

thresholds. 

For the reasons described above, this 

[EASA] AD requires repetitive special 

detailed [rototest] inspections (SDI) of the 

two upper rows of fasteners of the crossbeam 

splicing at FR16 and FR20, on both LH and 

RH sides, [installation of new fasteners on 

crack-free frames, related investigative and 

corrective actions,] and, depending on 

aeroplane configuration, provides an optional 

terminating action to the repetitive 

inspections required by this [EASA] AD. 

Related investigative actions include 

checking the edge margins of the holes. 

Corrective actions include reaming 

affected crossbeams and frames and 

cold working the frames. 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– 

1093. 

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. 

Requests To Revise Repair Instructions 

for Repairs Done Using an Airbus 

Repair Design Approval Sheet (RDAS) 

American Airlines (AAL) and United 

Airlines (UAL) requested that the repair 

instructions in paragraph (l) of the 

proposed AD be revised to remove 

requirements to obtain new repair 

instructions for any airplanes on which 

repairs were done using the instructions 

in an Airbus RDAS. AAL noted that the 

original RDAS approval was given by an 

EASA Design Organization Approval 

(DOA), so new approval should not be 

needed. Instead, AAL suggested that the 

issuer of the RDASs should be required 

to revise the RDASs as necessary. UAL 

noted that an RDAS already defines 

repair life and inspection instructions or 

limits. UAL also noted that the MCAI 

does not require obtaining new repair 

instructions, but instead says to 

accomplish the repair instructions given 

in the RDAS for repaired fastener holes. 

We disagree to require the issuer of 

the RDAS to revise the RDAS. An RDAS 

is an Airbus document that is not 

approved by the FAA, and the FAA has 

no authority to require Airbus to revise 

the RDAS. 

We agree with the requests to remove 

the requirement to obtain repair 

instructions in paragraph (l) of this AD. 

We have confirmed that EASA intended 

the corresponding paragraph in the 

MCAI to be informational, rather than a 

new requirement. We have revised 

paragraph (l) of this AD to note that the 

information on the next inspection and 

compliance time for the inspection of 

repaired holes is specified in the 

applicable RDAS; therefore, there is no 

requirement to obtain and follow new 

instructions. 

Request To Supersede Certain 

Inspections 

UAL requested that we revise 

paragraph (l) of the proposed AD to state 

that previous repair instructions that 

superseded ALI 531110 also terminate 

the inspections required by paragraph 

(g) of the proposed AD for the repaired 

holes. UAL noted that they had several 

RDASs that state that the inspection 

requirements of the RDAS supersede 

ALI 531110 for the repaired fasteners. 

UAL stated that these repairs involved 

enlarging the holes and fasteners, 

thereby making it impossible for them to 

accomplish the inspections in 

accordance with Airbus Service Bulletin 

A320–53–1286, Revision 01, dated 

December 22, 2015. 

We disagree with revising paragraph 

(l) of this AD to specify terminating 

action to paragraph (g) of this AD. An 

operator who is unable to complete 

certain requirements in this AD due to 

existing repairs may request an 

alternative method of compliance 

(AMOC) under the provisions of 

paragraph (s)(1) of this AD. 

Request To Remove or Revise 

Paragraph (n) of the Proposed AD 

AAL requested that paragraph (n) of 

the proposed AD be revised to remove 

requirements to obtain new repair 

instructions for any airplanes on which 

repairs were done using the instructions 

in an Airbus RDAS unrelated to ALI 

task 531110. AAL noted that the original 

RDAS approval was given by an EASA 

DOA, so new approval should not be 

needed. Instead, AAL suggested that the 

issuer of the RDASs should be required 

to revise the RDASs as necessary. 

UAL requested that paragraph (n) of 

the proposed AD be removed. UAL 

stated that determining if a repair is 

unrelated to ALI task 531110 may be 

inconclusive, since the ALI task is an 

inspection that may or may not be 

referenced in a documented repair. UAL 

added that each repair approval will 

have damage tolerance considerations 

regardless of how the damage was 

found. UAL further noted that if a repair 

unrelated to ALI task 531110 prevents 

inspection or repair as specified in the 

proposed AD, operators would need to 

request an AMOC. 

We disagree with the commenters’ 

requests. EASA has determined that 

repairs unrelated to ALI task 531110, 

which could include minor repairs 

unrelated to the unsafe condition, may 

not adequately address the unsafe 

condition. For this reason, operators 

must request new corrective actions for 

such repairs, as specified in paragraph 

(n) of this AD. 

Requests To Revise Repair Instructions 

for Airplanes on Which Certain Repairs 

Were Previously Applied 

UAL and AAL requested that 

paragraphs (i) and (j) of the proposed 

AD be revised to list specific affected 

manufacturer serial numbers (MSNs). In 

addition, UAL and AAL requested that 

the original equipment manufacturer 

(OEM) revise the Airbus RDASs to 

correct any problems. AAL pointed out 

that the original RDAS was approved by 

an EASA DOA and stated that operators 

should therefore not be required to 

obtain a new approval. UAL requested 

that if we do not provide revised RDASs 

or a list of affected MSNs, we instead 

provide a pre-defined solution for the 

repair. UAL suggested that we should 

provide instructions for replacing 

EN6114 fasteners with EN6115 

fasteners. UAL further requested that if 

the repairs require case-by-case 

evaluations, the repair instructions 

should define the repair compliance 

time, rather than having a set 24 month 

compliance time, which may not work 

for every configuration. 

UAL also noted that the issue with 

Airbus Repair Instruction R53112926 

issue A or B is that it called out the 

wrong fastener; EN6115 should have 

been used instead of EN6114. 

UAL requested that we add a 

statement to paragraph (j) of this AD 

stating that no additional repair 

instructions are needed if a repair was 

accomplished using Airbus Repair 

Instruction R53112926 issue A or B and 

EN6115 fasteners. 


sradovich on DSK3GMQ082PROD with RULES
34036 Federal Register / Vol. 83, No. 139 / Thursday, July 19, 2018 / Rules and Regulations 

We disagree with the commenters’ 

requests to revise paragraphs (i) and (j) 

of this AD to list specific affected MSNs. 

EASA, as the state of design authority, 

and Airbus have both stated that they do 

not have knowledge of prior approved 

repairs; therefore we do not have a list 

of affected MSNs. In addition, an RDAS 

is an Airbus document that is not 

approved by the FAA, and the FAA has 

no authority to require Airbus to revise 

the RDAS. Therefore, each existing 

repair must be individually analyzed 

before a new corrective action can be 

provided. For this reason, we are not 

able to provide a single pre-defined 

solution for the repair that would 

address every affected configuration. We 

have determined that 24 months is an 

appropriate time frame to address the 

unsafe condition related to the EN6114 

fasteners. An AMOC in accordance with 

paragraph (s)(1) of this AD may be 

requested if additional time is needed to 

address the unsafe condition. 

We do not agree to add a statement to 

paragraphs (i) or (j) of this AD regarding 

no additional repair instructions are 

necessary if those repairs were applied 

with the installation of EN6115 

fasteners, but we do agree to clarify that 

paragraphs (i) and (j) of this AD only 

apply to airplanes on which Airbus 

Repair Instruction R53112926 issue A or 

B or any other repair involving the 

installation of EN6114 fasteners was 

applied. If EN6115 fasteners were 

installed in the accomplishment of 

Airbus Repair Instruction R53112926 

issue A or B or any other repair, the 

actions specified in paragraphs (i) or (j) 

of this AD are not required on the 

repaired airplane. 

Request To Include Corrections to 

Service Information 

UAL requested that we update 

paragraph (k) of the proposed AD to 

reflect corrections to Airbus Service 

Bulletin A320–53–1295, including 

Appendixes 01 and 02, dated June 29, 

2015. UAL noted that Airbus has 

released Operators Information 

Transmission (OIT) 15–0097, Revision 

01, dated January 7, 2016, to correct 

discrepancies in the effectivity section 

and existing hole diameters for certain 

subtasks in Airbus Service Bulletin 

A320–53–1295, including Appendixes 

01 and 02, dated June 29, 2015. 

We agree with the commenter’s 

request for the reasons provided. We 

have added paragraph (r) to this AD to 

clarify the hole-diameter correction 

provided in Airbus OIT 15–0097, 

Revision 01, dated January 7, 2016. We 

have also updated other paragraphs of 

this AD that refer to Airbus Service 

Bulletin A320–53–1295, including 

Appendixes 01 and 02, dated June 29, 

2015, to include this exception. We also 

acknowledge the discrepancy in the 

effectivity section of Airbus Service 

Bulletin A320–53–1295, including 

Appendixes 01 and 02, dated June 29, 

2015, and the correction provided in 

Airbus OIT 15–0097, Revision 01, dated 

January 7, 2016. However, the 

applicability of this AD does not refer to 

Airbus Service Bulletin A320–53–1295, 

including Appendixes 01 and 02, dated 

June 29, 2015. Therefore, we have not 

changed this AD in this regard. 

Request To Verify Title of Table 1 to 

Paragraphs (g) and (n) of This AD 

Virgin America requested that we 

review the title of table 1 to paragraphs 

(g) and (n) of this AD. Virgin America 

noted that the related MCAI table refers 

to airplanes having not embodied any of 

‘‘mod 20416 and mod 21999,’’ while the 

proposed AD refers to ‘‘pre-modification 

20416 or pre-modification 21999’’ 

airplanes. Virgin America suggested this 

might be a typographical error, and 

asked that it be corrected if it is in error. 

We acknowledge that the wording in 

the MCAI and this AD is not the same 

and agree to clarify. Table 1 of the MCAI 

is intended to apply to airplanes that 

have not embodied any part of 

modification 20416 or any part of 

modification 21999. Therefore, it is 

accurate to state ‘‘pre-modification 

20416 or pre-modification 21999 

airplanes.’’ We have not changed this 

AD in this regard. 

Request To Verify Referenced Service 

Information is at the Latest Revision 

UAL requested that we verify the 

service bulletins referenced in the 

proposed AD are at the latest revision 

level. UAL noted this would eliminate 

the need to request an AMOC 

immediately following publication of 

this AD. 

We agree with the commenter’s 

request. We have verified that no 

revisions of the referenced service 

information have been published since 

we issued our proposed AD. 

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 

and 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 the following 

service information. 

• Service Bulletin A320–53–1286, 

Revision 01, dated December 22, 2015, 

which describes procedures for rototest 

inspections for cracking of the holes in 

certain fuselage frames and crossbeams. 

• Service Bulletin A320–53–1295, 

including Appendixes 01 and 02, dated 

June 29, 2015, which describes 

procedures for modifying the airplane, 

including cold working instructions in 

certain fuselage frames and crossbeams. 

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 928 

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 

Inspections ...................... 116 work-hours × $85 per hour = $9,860 per inspection cycle.$960 $10,820 per inspection cycle .......... $10,040,960 per inspection 

cycle. 

Optional Modification ....... 28 work-hours × times; $85 per hour = $2,380 .......... 3,020 $5,400 ............................................. Up to $5,011,200. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

Authority for this Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 


sradovich on DSK3GMQ082PROD with RULES
Federal Register / Vol. 83, No. 139 / Thursday, July 19, 2018 / Rules and Regulations 34037 

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 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): 

2018–14–09 Airbus: Amendment 39–19329; 

Docket No. FAA–2017–1093; Product 

Identifier 2017–NM–018–AD. 

(a) Effective Date 

This AD is effective August 23, 2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A318– 

111, –112, –121, and –122 airplanes; Model 

A319–111, –112, –113, –114, –115, –131, 

–132, and –133 airplanes; Model A320–211, 

–212, –214, –216, –231, –232, and –233 

airplanes; and Model A321–111, –112, –131, 

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

certificated in any category, all manufacturer 

serial numbers, except the airplanes specified 

in paragraphs (c)(1), (c)(2), and (c)(3) of this 

AD. 

(1) Airplanes on which Airbus 

modification 161255 has been embodied in 

production. 

(2) Model A319 series airplanes on which 

Airbus modifications 28238, 28162, and 

28342 have been concurrently embodied in 

production. 

(3) Model A318 series airplanes on which 

Airbus modification 39195 has been 

embodied in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by reports of early 

cracking on the four holes of the crossbeam 

splicing at certain fuselage frames (FR). We 

are issuing this AD to detect and correct 

cracking at two upper rows of fasteners of the 

crossbeam splicing at FR16 and FR20, on 

both the left-hand (LH) and right-hand (RH) 

sides, which can result in reduced structural 

integrity of the airplane due to the failure of 

structural components. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Rototest Inspections 

Before exceeding the threshold specified in 

table 1 to paragraphs (g) and (n) of this AD, 

or table 2 to paragraphs (g) and (n) of this AD, 

as applicable to airplane configuration (preor post-modification 20416 or pre- or postmodification 21999): Do a special detailed 

(rototest) inspection of the two upper rows of 

fasteners of the crossbeam splicing at FR16 

and FR20 on both LH and RH sides, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1286, Revision 01, dated December 22, 

2015. Thereafter, repeat the inspection at the 

intervals specified in table 1 to paragraphs (g) 

and (n) of this AD, or table 2 to paragraphs 

(g) and (n) of this AD, as applicable to 

airplane configuration (pre- or postmodification 20416 or pre- or postmodification 21999). 

BILLING CODE 4910–13–P 


sradovich on DSK3GMQ082PROD with RULES
34038 Federal Register / Vol. 83, No. 139 / Thursday, July 19, 2018 / Rules and Regulations 

BILLING CODE 4910–13–C 

(h) Post-Inspection Actions 

Depending on the results from any 

inspection required by paragraph (g) of this 

AD, do the actions in paragraphs (h)(1) or 

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

(1) If, during any inspection required by 

paragraph (g) of this AD, any crack is 

detected: Before further flight, do all 

applicable related investigative and 

corrective actions in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1286, Revision 01, 

dated December 22, 2015; except where 

Airbus Service Bulletin A320–53–1286, 

Revision 01, dated December 22, 2015, 

specifies to contact Airbus for appropriate 

repair, and specifies that action as ‘‘RC’’ 

(Required for Compliance), accomplish 

corrective actions before further flight in 

accordance with the procedures specified in 

paragraph (s)(2) of this AD. Repair of an 

airplane as required by this paragraph does 

not constitute terminating action for the 

repetitive inspections required by paragraph 

(g) of this AD for that airplane, unless 

specified otherwise in the repair instructions. 

(2) If, during any inspection required by 

paragraph (g) of this AD, no cracks are 

detected: Before further flight, do all 

applicable fastener installations, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1286, Revision 01, dated December 22, 

2015. 

(i) Airplanes on Which Airbus Repair 

Instruction R53112926 With Installation of 

EN6114 Countersunk Fasteners Was Applied 

on the Frame and/or Crossbeam 

For airplanes on which Airbus Repair 

Instruction R53112926 at issue A or B with 

installation of EN6114 countersunk fasteners 

was applied on the frame and/or crossbeam 

at FR16 LH or RH, or at FR20 LH or RH: 

Within 24 months after the effective date of 

this AD, modify the repair using a method 

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). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(j) Airplanes on Which a Repair With 

Installation of EN6114 Countersunk 

Fasteners Was Applied on the Frame and/or 

Crossbeam 

For airplanes on which a repair with 

installation of EN6114 countersunk fasteners, 

approved by the FAA, EASA, Airbus’s EASA 

DOA, or an EASA DOA (other than Airbus’s 

EASA DOA), was applied on the frame and/ 

or crossbeam at FR16 LH or RH, or at FR20 

LH or RH, in the area covered by paragraph 

(g) of this AD: Within 24 months after the 

effective date of this AD, modify the repair 

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 DOA-authorized signature. 


sradovich on DSK3GMQ082PROD with RULESER19JY18.002</GPH> ER19JY18.003</GPH>
Federal Register / Vol. 83, No. 139 / Thursday, July 19, 2018 / Rules and Regulations 34039 

(k) Optional Terminating Action for 

Airplanes Post-Modification 20416 or PostModification 21999 

Modification of an airplane postmodification 20416 or post-modification 

21999 in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1295, including 

Appendixes 01 and 02, dated June 29, 2015, 

except as required by paragraph (r) of this 

AD, constitutes terminating action for the 

repetitive inspections required by paragraph 

(g) of this AD for that airplane. 

(l) Information on Post-Repair Actions for 

Certain Airplanes 

For an airplane that has been inspected per 

ALI task 531110 and repaired before the 

effective date of this AD using the 

instructions in an Airbus Repair Design 

Approval Sheet (RDAS): each applicable 

RDAS contains next inspection and 

compliance time for the inspection for each 

repaired hole. 

(m) Partial Terminating Action for Airplanes 

Post-Modification 20416 or PostModification 21999 

For an airplane post-modification 20416 or 

post-modification 21999, modification in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1295, including Appendixes 01 and 02, 

dated June 29, 2015, except as required by 

paragraph (r) of this AD, for the applicable 

fastener holes, where no damage or cracks 

were detected (i.e., those not repaired) during 

the latest inspection as required by paragraph 

(g) of this AD, constitutes terminating action 

for the repetitive inspections of those fastener 

holes as required by paragraph (g) of this AD 

for that airplane. 

(n) Actions for Airplanes With Certain 

Repairs 

For an airplane that has been repaired 

before the effective date of this AD in the 

areas described in this AD using the 

instructions in an Airbus RDAS unrelated to 

ALI task 531110: Before exceeding the 

compliance times specified in table 1 to 

paragraphs (g) and (n) of this AD or table 2 

to paragraphs (g) and (n) of this AD, as 

applicable, contact the Manager, 

International Section, Transport Standards 

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

DOA for corrective action instructions and 

accomplish those instructions accordingly. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

Accomplishment of corrective action(s) on an 

airplane, as required by this paragraph, does 

not constitute terminating action for the 

repetitive inspections required by paragraph 

(g) of this AD for that airplane, as applicable, 

unless specified otherwise in the 

instructions. 

(o) Terminating Action for ALI Tasks 

(1) Accomplishment of an inspection as 

required by paragraph (g) of this AD or 

instructions as required by paragraph (l) of 

this AD, as applicable, constitutes 

terminating action for the inspection 

requirements of ALI task 531110, for that 

airplane. 

(2) Modification of the two upper rows of 

fasteners of the crossbeam splicing at FR16 

and FR20 on both LH and RH sides of an 

airplane, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1295, including 

Appendixes 01 and 02, dated June 29, 2015, 

except as required by paragraph (r) of this 

AD, as specified in paragraphs (k) and (m) of 

this AD, constitutes terminating action for 

the inspection requirements of ALI task 

531110, for those holes for that airplane. 

(p) No Reporting Requirement 

Although Airbus Service Bulletin A320– 

53–1286, Revision 01, dated December 22, 

2015, specifies to submit certain information 

to the manufacturer, and specifies that action 

as ‘‘RC’’ (Required for Compliance), this AD 

does not include that requirement. 

(q) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) and (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–53–1286, dated June 29, 2015. 

(r) Service Information Exceptions 

Where Subtasks 531295–960–001–001 and 

532195–960–002–001 of Airbus Service 

Bulletin A320–53–1295, including 

Appendixes 01 and 02, dated June 29, 2015, 

refer to actions when an existing hole 

diameter is ‘‘more than or equal to the 

minimum starting hole diameter,’’ this AD 

requires applicable actions in cases where 

the hole diameter is ‘‘more than or equal to 

the maximum starting hole diameter.’’ 

(s) 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 (t)(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’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraphs (h)(1) and (p) 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. 

(t) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2016–0139, dated July 14, 2016, 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–2017–1093. 

(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; telephone and fax 206– 

231–3223. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(u) 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 A320–53–1286, 

Revision 01, dated December 22, 2015. 

(ii) Airbus Service Bulletin A320–53–1295, 

including Appendixes 01 and 02, dated June 

29, 2015. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, Rond-Point Emile Dewoitine 

No: 2, 31700 Blagnac Cedex, France; 

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

93 44 51; email account.airworth-eas@

airbus.com; internet http://www.airbus.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 June 

29, 2018. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2018–14687 Filed 7–18–18; 8:45 am] 

BILLING CODE 4910–13–P 


sradovich on DSK3GMQ082PROD with RULES