3564 Federal Register / Vol. 83, No. 18 / Friday, January 26, 2018 / Rules and Regulations 

Dated: January 23, 2018. 

Dale L. Aultman, 

Secretary to the Board, Farm Credit System 

Insurance Corporation. 

[FR Doc. 2018–01421 Filed 1–25–18; 8:45 am] 

BILLING CODE 6710–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0716; Product 

Identifier 2016–NM–165–AD; Amendment 

39–19165; AD 2018–02–12] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2016–02– 

01, which applied to certain Airbus 

Model A320–211, –212, and –231 

airplanes. AD 2016–02–01 required 

repetitive inspections to detect cracks of 

the pressurized floor fittings at a certain 

frame, and renewal of the zone 

protective finish or replacement of 

fittings with new fittings if necessary. 

AD 2016–02–01 also provided an 

optional modification that was 

terminating action for the repetitive 

inspections. This new AD retains the 

requirements of AD 2016–02–01, and 

requires accomplishment of the 

modification that was optional in AD 

2016–02–01. This AD was prompted by 

the results of an additional fatigue 

analysis of cracking of the pressurized 

floor fittings and a determination that 

the optional modification should 

become a required action. We are 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective March 2, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of March 3, 2016 (81 FR 

4878, January 28, 2016). 

ADDRESSES: For 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.airworth-eas@

airbus.com; internet: http://

www.airbus.com. You may view this 

referenced service information at the 

FAA, Transport Standards Branch, 1601 

Lind Avenue SW, Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

It is also available on the internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2017– 

0716. 

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– 

0716; 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 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, 1601 Lind 

Avenue SW, Renton, WA 98057–3356; 

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 to supersede AD 2016–02–01, 

Amendment 39–18380 (81 FR 4878, 

January 28, 2016) (‘‘AD 2016–02–01’’). 

AD 2016–02–01 applied to certain 

Airbus Model A320–211, –212, and 

–231 airplanes. The NPRM published in 

the Federal Register on August 15, 2017 

(82 FR 38618). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2016–0181, 

dated September 13, 2016 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Model A320–211, 

–212, and –231 airplanes. The MCAI 

states: 

During centre fuselage certification full 

scale fatigue testing, damage was found on 

the pressurized floor fittings at Frame (FR) 

36, below the lower surface panel. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

To prevent such damage, Airbus developed 

modification 21282, which was introduced in 

production from MSN [manufacturer serial 

number] 0105, to reinforce the pressurized 

floor fitting lower surface by changing 

material. For affected in-service aeroplanes, 

Airbus issued Service Bulletin (SB) A320– 

57–1028, introducing repetitive inspections, 

and SB A320–57–1029, which provides 

modification instructions. 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France issued AD 95–099–067 to 

require these repetitive inspections and, 

depending on findings, corrective action(s), 

while the modification was specified in that 

[French] AD as optional terminating action 

for these inspections. 

Following new analysis in the frame of 

Extended Service Goal exercise, the 

inspection thresholds and intervals were 

revised to meet the original Design Service 

Goal. Consequently, EASA issued AD 2013– 

0226 [which corresponds to FAA AD 2016– 

02–01 (81 FR 4878, January 28, 2016)] to 

retain the requirements of DGAC France AD 

95–099–067, which was superseded, but 

required those actions within reduced 

compliance times. 

Since that [EASA] AD was issued, in the 

frame of Widespread Fatigue Damages 

analysis, the situation has been reassessed 

and it has been decided to reclassify the 

modification, still stated as ‘optional’ 

terminating action in EASA AD 2013–0226, 

to the status ‘mandatory’. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2013–0226, which is superseded, but 

requires embodiment of the modification as 

specified in Airbus SB A320–57–1029. 

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– 

0716. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM and the FAA’s 

response to that comment. 

Request To Revise the Applicability 

Allegiant Air noted that the 

applicability specified in paragraph (c) 

of the proposed AD included Airbus 

Model A320–214 airplanes. The 

commenter asked if Model A320–214 

airplanes were included in the 

applicability in error. The commenter 

observed that neither the applicability 

of AD 2016–02–01 or EASA AD 2016– 

0181, nor the effectivity of Airbus 

Service Bulletin A320–57–1028, 

Revision 02, dated June 3, 2013, 

included Model A320–214 airplanes. 

We infer that the commenter is 

requesting that Model A320–214 

airplanes be removed from the 

applicability of the proposed AD. We 

agree, for the reasons provided by the 

commenter. This final rule is not 

applicable to Model A320–214 

airplanes; therefore, we have revised the 


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Federal Register / Vol. 83, No. 18 / Friday, January 26, 2018 / Rules and Regulations 3565 

applicability specified in paragraph (c) 

of this AD by removing Model A320– 

214 airplanes. 

Conclusion 

We reviewed the available data, 

including the comment 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 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 

A320–57–1028, Revision 02, dated June 

3, 2013. The service information 

describes procedures for an inspection 

to detect cracks of the pressurized floor 

fittings at FR 36, renewal of the zone 

protective finish, and replacement of 

fittings with new fittings. 

Airbus has also issued Service 

Bulletin A320–57–1029, Revision 02, 

dated June 16, 1999. The service 

information describes procedures for 

modification of the pressurized floor 

fittings at FR 36. 

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 13 

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 

Inspection ...................... 11 work-hours × $85 per hour = $935 per inspection cycle.$0 $935 per inspection 

cycle.

$12,155 per inspection 

cycle. 

Modification ................... 85 work-hours × $85 per hour = $7,225 ............ 5,320 $12,545 ........................ $163,085. 

We have received no definitive data 

that will 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 

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 

removing Airworthiness Directive (AD) 

2016–02–01, Amendment 39–18380 (81 

FR 4878, January 28, 2016), and adding 

the following new AD: 

2018–02–12 Airbus: Amendment 39–19165; 

Docket No. FAA–2017–0716; Product 

Identifier 2016–NM–165–AD. 

(a) Effective Date 

This AD is effective March 2, 2018. 

(b) Affected ADs 

This AD replaces AD 2016–02–01, 

Amendment 39–18380 (81 FR 4878, January 

28, 2016) (‘‘AD 2016–02–01’’). 

(c) Applicability 

This AD applies to Airbus Model A320– 

211, –212, and –231 airplanes, certificated in 

any category, manufacturer serial numbers 

up through 0104 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD is intended to complete certain 

mandated programs intended to support the 

airplane reaching its limit of validity (LOV) 

of the engineering data that support the 

established structural maintenance program. 

We are issuing this AD to prevent fatigue 

cracking in the pressurized floor fittings at 

frame (FR) 36, which could result in the 

reduced structural integrity of the floor 


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3566 Federal Register / Vol. 83, No. 18 / Friday, January 26, 2018 / Rules and Regulations 

fittings and subsequent depressurization of 

the fuselage. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

(1) At the latest of the times specified in 

paragraphs (g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of 

this AD: Do a detailed inspection of the 

pressurized floor fittings at FR 36, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1028, Revision 02, dated June 3, 2013. 

Repeat the inspection thereafter at intervals 

not to exceed 9,300 flight cycles or 18,600 

flight hours, whichever occurs first. 

(i) Before exceeding 20,900 flight cycles or 

41,800 flight hours, whichever occurs first 

since first flight of the airplane. 

(ii) Within 9,300 flight cycles or 18,600 

flight cycles since the most recent inspection 

accomplished in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1028, Revision 02, 

dated June 3, 2013. 

(iii) Within 1,250 flight cycles or 2,500 

flight hours after March 3, 2016 (the effective 

date of AD 2016–02–01), without exceeding 

12,000 flight cycles since the most recent 

inspection accomplished in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1028, Revision 02, 

dated June 3, 2013. 

(2) If any crack is found during any 

inspection required by paragraph (g)(1) of 

this AD: 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’s EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(h) Modification 

Before exceeding 48,000 total flight cycles 

or 96,000 total flight hours, whichever occurs 

first since first flight of the airplane: Modify 

(replace aluminum fittings with titanium 

fittings) the pressurized floor fittings at FR 

36, in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1029, Revision 02, dated June 16, 1999. 

Accomplishment of this modification is 

terminating action for the repetitive 

inspections required by paragraph (g) of this 

AD for the modified airplane only. 

(i) Credit for Previous Actions 

(1) This paragraph provides credit for the 

inspection required by paragraph (g) of this 

AD, if that inspection was performed before 

the effective date of this AD using Airbus 

Service Bulletin A320–57–1028, dated 

August 12, 1991; or Revision 01, dated April 

19, 1996. 

(2) This paragraph provides credit for the 

modification required by paragraph (h) of 

this AD, if that modification was performed 

before the effective date of this AD using 

Airbus Service Bulletin A320–57–1029, 

dated August 12, 1991; or Revision 01, dated 

November 10, 1992. 

(j) 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 (k)(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: 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’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2016–0181, dated September 13, 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–2017–0716. 

(2) For more information about this AD, 

contact Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 1601 Lind Avenue SW, 

Renton, WA 98057–3356; telephone: 425– 

227–1405; fax: 425–227–1149. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (l)(4) and (l)(5) 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 this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on March 3, 2016 (81 FR 

4878, January 28, 2016). 

(i) Airbus Service Bulletin A320–57–1028, 

Revision 02, dated June 3, 2013. 

(ii) Airbus Service Bulletin A320–57–1029, 

Revision 02, dated June 16, 1999. 

(4) For 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.airworth-eas@

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

(5) You may view this service information 

at the FAA, Transport Standards Branch, 

1601 Lind Avenue SW, Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(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 Renton, Washington, on January 

10, 2018. 

John P. Piccola, Jr., 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–01197 Filed 1–25–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–1201; Product 

Identifier 2017–SW–068–AD; Amendment 

39–19155; AD 2018–02–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Model AS350B, AS350BA, 

AS350B1, AS350B2, AS350B3, AS350D, 

AS355E, AS355F, AS355F1, AS355F2, 

AS355N, AS355NP, EC130B4, and 

EC130T2 helicopters. This AD requires 

inspecting the main rotor (M/R) mast jet 

oil lubrication hose (oil hose). This AD 

is prompted by a report of a blocked oil 

hose. The actions of this AD are 

intended to prevent an unsafe condition 

on these helicopters. 

DATES: This AD becomes effective 

February 12, 2018. 

We must receive comments on this 

AD by March 27, 2018. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE, Washington, DC 

20590–0001. 


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