Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules 46905 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles ACO Branch, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. In accordance with 

14 CFR 39.19, send your request to your 

principal inspector or local Flight Standards 

District Office, as appropriate. If sending 

information directly to the manager of the 

certification office, send it to the attention of 

the person identified in paragraph (k)(1) of 

this AD. Information may be emailed to: 

9-ANM-LAACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO Branch, FAA, to make those findings. 

To be approved, the repair method, 

modification deviation, or alteration 

deviation must meet the certification basis of 

the airplane, and the approval must 

specifically refer to this AD. 

(k) Related Information 

(1) For more information about this AD, 

contact Galib Abumeri, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles ACO 

Branch, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5324; fax: 562–627–5210; email: 

galib.abumeri@faa.gov. 

(2) 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; 

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

www.myboeingfleet.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. 

Issued in Des Moines, Washington, on 

August 30, 2018. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2018–19840 Filed 9–14–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0795; Product 

Identifier 2018–NM–076–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 supersede 

Airworthiness Directive (AD) 2014–20– 

04, which applies to all Airbus SAS 

Model A318 series airplanes; Airbus 

SAS Model A319 series airplanes; 

Airbus SAS Model A320–111, –211, 

–212, –214, –231, –232, and –233 

airplanes; and Airbus SAS Model A321– 

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

and –232 airplanes. AD 2014–20–04 

requires repetitive inspections for 

cracking of the four titanium angles 

between the belly fairing and the keel 

beam side panel, an inspection for 

cracking of the open holes if any 

cracking is found in the titanium angles, 

and repair or replacement if necessary. 

Since we issued AD 2014–20–04, we 

have determined that additional work is 

necessary for certain airplanes. This 

proposed AD would continue to require 

repetitive inspections for cracking of the 

four titanium angles between the belly 

fairing and the keel beam side panel, an 

inspection for cracking of the open 

holes if any cracking is found in the 

titanium angles, and repair or 

replacement if necessary. This proposed 

AD would also revise the applicability 

by adding Model A320–216 airplanes. 

This proposed AD would also require a 

detailed inspection for and replacement 

of certain rivets (including a rotating 

probe test for cracks in the open holes), 

and corrective actions if necessary. We 

are proposing this AD to address the 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by November 1, 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—EIAS, RondPoint Emile Dewoitine No: 2, 31700 

Blagnac Cedex, France; phone: +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. 

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– 

0795; 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– 

2018–0795; Product Identifier 2018– 

NM–076–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We issued AD 2014–20–04, 

Amendment 39–17977 (79 FR 59636, 


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October 3, 2014) (‘‘AD 2014–20–04’’), 

for all Airbus SAS Model A318 series 

airplanes; Airbus SAS Model A319 

series airplanes; Airbus SAS Model 

A320–211, –212, –214, –231, –232, and 

–233 airplanes; and Airbus SAS Model 

A321–111, –112, –131, –211, –212, 

–213, –231, and –232 airplanes. AD 

2014–20–04 requires repetitive 

inspections for cracking of the four 

titanium angles between the belly 

fairing and the keel beam side panel, an 

inspection for cracking of the open 

holes if any cracking is found in the 

titanium angles, and repair or 

replacement if necessary. AD 2014–20– 

04 resulted from reports of cracks at the 

lower riveting of the four titanium 

angles that connect the belly fairing to 

the keel beam side panels on both sides 

of the fuselage. We issued AD 2014–20– 

04 to address cracking of the titanium 

angles that connect the belly fairing to 

the keel beam side panels on both sides 

of the fuselage, which could affect the 

structural integrity of the airplane. 

Actions Since AD 2014–20–04 Was 

Issued 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2018–0091, 

dated April 20, 2018 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus SAS Model A318 series 

airplanes; Airbus SAS Model A319 

series airplanes; Airbus SAS Model 

A320–211, –212, –214, –216, –231, 

–232, and –233 airplanes; and Airbus 

SAS Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 

airplanes. The MCAI states: 

During the fatigue test campaign of the 

A320 family type design, cracks were found 

at the lower riveting of the four titanium 

angles which connect the belly fairing to the 

keel beam side panels between frames FR40 

and FR42, on both sides of the fuselage. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

To address this potential unsafe condition, 

Airbus issued Service Bulletin (SB) A320– 

53–1014, and DGAC [Direction Ge ́ne ́rale de 

l’Aviation Civile] France issued AD 92–201– 

030 [which corresponds to FAA AD 94–12– 

03, Amendment 39–8930 (59 FR 28763, June 

3, 1994)(‘‘AD 94–12–03’’)] to require 

reinforcement of the belly fairing structure. 

Following new investigation which 

showed that these measures addressed only 

part of the unsafe condition, Airbus 

published SB A320–53–1259 and EASA 

issued AD 2013–0122 [which corresponds to 

FAA AD 2014–20–04], retaining the 

requirements of DGAC France AD 92–201– 

030, which was superseded, and requiring 

repetitive detailed inspections (DET) of the 

affected titanium angles and, depending on 

findings, repair or replacement of parts. 

After that [EASA] AD was issued, Airbus 

published Revision (Rev.) 01 and Rev. 02 of 

SB A320–53–1259. [Airbus SB A320–53– 

1259] Rev. 02 provided incorrect instructions 

to use Part Number (P/N) EN6081D4 rivets 

for the titanium angles installation, instead of 

P/N EN6081D5 rivets. Consequently, Airbus 

SB A320–53–1259 was updated (now at Rev. 

03) including reference to the proper rivets. 

For the reason described above, this 

[EASA] AD retains the requirements of EASA 

AD 2013–0122, which is superseded, and 

requires additional work [a detailed 

inspection for and replacement of certain 

rivets, and applicable corrective actions] for 

aeroplanes on which Airbus SB A320–53– 

1259 at Rev. 02 was embodied. 

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– 

0795. 

Model A320–216 Airplanes 

The Airbus SAS Model A320–216 was 

type certificated on December 19, 2016. 

Before that date, any EASA ADs that 

affected Model A320–216 airplanes 

were included on the Required 

Airworthiness Actions List (RAAL). One 

or more Model A320–216 airplanes have 

subsequently been placed on the U.S. 

Register, and will now be included in 

FAA AD actions. For Model A320–216 

airplanes, the requirements that 

correspond to AD 2014–20–04 were 

mandated by the MCAI via the RAAL. 

Although that RAAL requirement is still 

in effect, for continuity and clarity we 

have identified Model A320–216 

airplanes in paragraph (c) of this AD; 

the restated requirements of paragraphs 

(h) through (n) in this proposed AD 

would therefore apply to those 

airplanes. 

Related Service Information Under 1 

CFR Part 51 

Airbus SAS has issued Service 

Bulletin A320–53–1259, Revision 03, 

dated November 30, 2017. This service 

information describes procedures for 

repetitive inspections for cracking of the 

four titanium angles between the belly 

fairing and the keel beam side panel, an 

inspection for cracking of the open 

holes if any cracking is found in the 

titanium angles, repair or replacement if 

necessary, and a detailed inspection for 

and replacement of certain rivets 

(including a rotating probe test for 

cracks in the open holes). 

Airbus also issued Service Bulletin 

A320–53–1014, Revision 2, dated 

September 1, 1994. This service 

information describes procedures for 

reinforcement (modification) of the 

belly fairing structure. 

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 

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 retain all 

requirements of AD 2014–20–04. This 

proposed AD would also require 

accomplishing the actions specified in 

the service information described 

previously. 

Costs of Compliance 

We estimate that this proposed AD 

affects 1,250 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 

295 work-hours × $85 per hour = $25,075 (Old actions of AD 2014–20–04) $1,045 $26,120 .......................... $32,650,000. 

Up to 168 work-hours × $85 per hour = Up to $14,280 (New actions of this 

AD).

0 Up to $14,280 ................ Up to $17,850,000. 


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We estimate the following costs to do 

any necessary replacement that would 

be required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need this replacement: 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Labor cost Parts cost * Cost per 

product 

168 work-hours × $85 per hour = $14,280 ............................................................................................................. $0 $14,280 

* We have received no definitive data that would enable us to provide cost estimates for the on-condition parts costs. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

This proposed AD is issued in 

accordance with authority delegated by 

the Executive Director, Aircraft 

Certification Service, as authorized by 

FAA Order 8000.51C. In accordance 

with that order, issuance of ADs is 

normally a function of the Compliance 

and Airworthiness Division, but during 

this transition period, the Executive 

Director has delegated the authority to 

issue ADs applicable to transport 

category airplanes to the Director of the 

System Oversight Division. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

3. Will not affect intrastate aviation in 

Alaska, and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2014–20–04, Amendment 39–17977 (79 

FR 59636, October 3, 2014), and adding 

the following new AD: 

Airbus SAS: Docket No. FAA–2018–0795; 

Product Identifier 2018–NM–076–AD. 

(a) Comments Due Date 

We must receive comments by November 

1, 2018. 

(b) Affected ADs 

This AD replaces AD 2014–20–04, 

Amendment 39–17977 (79 FR 59636, October 

3, 2014) (‘‘AD 2014–20–04’’). 

(c) Applicability 

This AD applies to the Airbus SAS 

airplanes specified in paragraphs (c)(1), 

(c)(2), (c)(3), and (c)(4) of this AD, certificated 

in any category, all manufacturer serial 

numbers. 

(1) Model A318–111, –112, –121, and –122 

airplanes. 

(2) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(3) Model A320–211, –212, –214, –216, 

–231, –232, and –233 airplanes. 

(4) Model A321–111, –112, –131, –211, 

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

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by reports of cracks 

at the lower riveting of the four titanium 

angles that connect the belly fairing to the 

keel beam side panels on both sides of the 

fuselage. We are issuing this AD to detect and 

correct cracking of the titanium angles that 

connect the belly fairing to the keel beam 

side panels on both sides of the fuselage, 

which could affect the structural integrity of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Modification, With No Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2014–20–04, with no 

changes. For Model A320–111, –211, and 

–231 series airplanes, manufacturer serial 

numbers 003 through 092 inclusive: Prior to 

the accumulation of 12,000 total landings on 

the airplane, or within 300 days after January 

10, 1994 (the effective date of AD 93–24–11, 

Amendment 39–8760 (58 FR 64875, 

December 10, 1993)), whichever occurs later, 

modify the belly fairing structure, in 

accordance with the Accomplishment 

Instructions of an Airbus service bulletin 

specified in paragraph (g)(1), (g)(2), or (g)(3) 

of this AD. As of the effective date of this AD, 

use only the Airbus service bulletin specified 

in paragraph (g)(3) of this AD. 

(1) Airbus Industrie Service Bulletin A320– 

53–1014, dated June 25, 1992. 

(2) Airbus Industrie Service Bulletin A320– 

53–1014, Revision 1, dated May 26, 1993. 

(3) Airbus Service Bulletin A320–53–1014, 

Revision 2, dated September 1, 1994. 

(h) Retained Repetitive Inspection, With 

Updated Service Information 

This paragraph restates the requirements of 

paragraph (h) of AD 2014–20–04, with 

updated service information. At the latest of 

the compliance times specified in paragraphs 

(h)(1), (h)(2), and (h)(3) of this AD: Do a 

detailed inspection for cracking of the four 

titanium angles between the belly fairing and 

the keel beam side panel, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1259, dated 

November 6, 2012; or Airbus Service Bulletin 

A320–53–1259, Revision 03, dated November 

30, 2017. After the effective date of this AD 

only Airbus Service Bulletin A320–53–1259, 

Revision 03, dated November 30, 2017, may 

be used. 


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(1) Before the accumulation of 30,000 total 

flight cycles or 60,000 total flight hours, 

whichever occurs first after first flight of the 

airplane. 

(2) Within 30,000 flight cycles or 60,000 

flight hours, whichever occurs first after 

modification of the airplane as required by 

paragraph (g) of this AD, or after installation 

of new titanium angles, provided that, prior 

to installation, a rototest for cracking on the 

open holes has been accomplished with no 

crack findings, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1259, dated 

November 6, 2012; or Airbus Service Bulletin 

A320–53–1259, Revision 03, dated November 

30, 2017. After the effective date of this AD, 

only Airbus Service Bulletin A320–53–1259, 

Revision 03, dated November 30, 2017, may 

be used. 

(3) Within 3,000 flight cycles or 6,000 

flight hours, whichever occurs first after the 

effective date of this AD. 

(i) Retained Post-Inspection Actions for No 

Crack Findings, With Updated Service 

Information 

This paragraph restates the requirements of 

paragraph (i) of AD 2014–20–04, with 

updated service information. If, during any 

inspection required by paragraph (h) of this 

AD, there is no crack finding: Accomplish 

the actions specified in either paragraph (i)(1) 

or (i)(2) of this AD. 

(1) Repeat the inspection required by 

paragraph (h) of this AD at intervals not to 

exceed 5,000 flight cycles or 10,000 flight 

hours, whichever occurs first. 

(2) Before further flight after the inspection 

required by paragraph (h) of this AD, remove 

all inspected titanium angles, accomplish a 

rototest for cracking on the open holes and, 

provided no cracks are found, install new 

titanium angles, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1259, dated 

November 6, 2012; or Airbus Service Bulletin 

A320–53–1259, Revision 03, dated November 

30, 2017. After the effective date of this AD, 

only Airbus Service Bulletin A320–53–1259, 

Revision 03, dated November 30, 2017, may 

be used. 

(j) Retained Post-Inspection Actions for Any 

Crack Findings, With Updated Service 

Information 

This paragraph restates the requirements of 

paragraph (j) of AD 2014–20–04, with 

updated service information. If, during any 

inspection required by paragraph (h) of this 

AD, there is any crack finding: Before further 

flight, remove the affected titanium angle(s), 

accomplish a rototest for cracking on the 

open holes, and, provided no cracks are 

found, install new titanium angles, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1259, dated November 6, 2012; or Airbus 

Service Bulletin A320–53–1259, Revision 03, 

dated November 30, 2017. After the effective 

date of this AD, only Airbus Service Bulletin 

A320–53–1259, Revision 03, dated November 

30, 2017, may be used. 

(k) Retained Post-Installation Repetitive 

Inspections, With Updated Service 

Information 

This paragraph restates the requirements of 

paragraph (k) of AD 2014–20–04, with 

updated service information. For airplanes 

on which new titanium angles were installed 

as specified in paragraph (i)(2) or (j) of this 

AD: Within 30,000 flight cycles or 60,000 

flight hours, whichever occurs first after the 

installation, accomplish a detailed inspection 

for cracking of the four titanium angles 

between the belly fairing and the keel beam 

side panel, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1259, dated 

November 6, 2012; or Airbus Service Bulletin 

A320–53–1259, Revision 03, dated November 

30, 2017. After the effective date of this AD, 

only Airbus Service Bulletin A320–53–1259, 

Revision 03, dated November 30, 2017, may 

be used. Repeat the inspection thereafter at 

intervals not to exceed 5,000 flight cycles or 

10,000 flight hours, whichever occurs first. 

(l) Retained Post-Inspection Actions for Any 

Crack Findings During Post-Installation 

Inspections, With Updated Service 

Information 

This paragraph restates the requirements of 

paragraph (l) of AD 2014–20–04, with 

updated service information. If, during any 

inspection as required by paragraph (k) of 

this AD, there is any crack finding: Before 

further flight, remove the affected titanium 

angles, accomplish a rototest for cracking on 

the open holes, and, provided no cracks are 

found, install new titanium angles, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1259, dated November 6, 2012; or Airbus 

Service Bulletin A320–53–1259, Revision 03, 

dated November 30, 2017. After the effective 

date of this AD, only Airbus Service Bulletin 

A320–53–1259, Revision 03, dated November 

30, 2017, may be used. 

(m) Retained Corrective Action for Rototest 

Crack Finding, With Updated Contact 

Information 

This paragraph restates the requirements of 

paragraph (m) of AD 2014–20–04, with 

updated contact information. If, during any 

rototest as required by paragraph (i), (j), or (l) 

of this AD, any crack is found: Before further 

flight, repair using a method 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). If approved by the DOA, the approval 

must include the DOA-authorized signature. 

(n) Retained No Termination Action for 

Repetitive Inspections, With No Changes 

This paragraph restates the requirements of 

paragraph (n) of AD 2014–20–04, with no 

changes. Repair or replacement of parts as 

specified in this AD does not terminate the 

repetitive inspections required by this AD. 

(o) New Requirement of This AD: Detailed 

Inspection for Certain Rivets 

For airplanes previously inspected using 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1259, dated 

November 6, 2012: At the earlier of the times 

specified in paragraphs (o)(1) and (o)(2) of 

this AD, do a detailed inspection of the rivet 

installation in the belly fairing shear walls 

and the titanium angles for part number 

EN6081D4 series rivets in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1259, Revision 03, 

dated November 30, 2017. A review of the 

airplane maintenance records is acceptable to 

comply with the requirements this paragraph 

for that airplane, provided it can be 

determined that no titanium angles have 

been installed on that airplane in accordance 

with the Accomplishment Instructions of 

Revision 02 of Airbus Service Bulletin A320– 

53–1259, or if only rivets part number 

EN6081D5 have been used to install the 

titanium angles on that airplane. 

(1) Within 2,000 flight cycles or 4,000 

flight hours, whichever occurs first after the 

effective date of this AD. 

(2) Before exceeding 5,000 flight cycles or 

10,000 flight hours, whichever occurs first 

after accomplishment of the last inspection 

specified in paragraph (h) of this AD. 

(p) New Requirements of This AD: 

Replacement of Certain Rivets 

If any part number EN6081D4 series rivet 

is found during any inspection required by 

paragraph (o) of this AD, before further flight, 

do the actions specified in paragraphs (p)(1) 

and (p)(2) of this AD. 

(1) Remove the part number EN6081D4 

series rivets and do a rotating probe test of 

the open holes for cracks, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1259, Revision 03, 

dated November 30, 2017. If any crack 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. 

(2) Replace part number EN6081D4 series 

rivets with part number EN6081D5 series 

rivets in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1259, Revision 03, 

dated November 30, 2017. 

(q) Other FAA AD Provisions 

(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 (r)(2) of this AD. Information may 

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

(i) 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. 


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Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules 46909 

(ii) AMOCs approved previously for AD 

2014–20–04, Amendment 39–17977 (79 FR 

59636, October 3, 2014), are approved as 

AMOCs for the corresponding provisions of 

paragraphs (o) and (p) of this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, 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 

SAS’s EASA DOA. If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(3) Required for Compliance (RC): 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. 

(r) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2018–0091, dated April 20, 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–2018–0795. 

(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—EIAS, Rond-Point Emile Dewoitine 

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

+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 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 

August 29, 2018. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2018–19932 Filed 9–14–18; 8:45 am] 

BILLING CODE 4910–13–P 


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