Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules 32055 

9Regulations for which rulemaking authority has 

transferred to the CFPB are not included in this 

Consumer Protection category. As described in the 

Supplementary Information section of this notice, 

the CFPB is required to review its significant rules 

and publish a report of its review no later than five 

years after they take effect, in a process separate 

from the EGRPRA process. 

Dated: May 27, 2015. 

Thomas J. Curry, 

Comptroller of the Currency. 

By order of the Board of Governors of the 

Federal Reserve System, May 29, 2015. 

Michael Lewandowski, 

Associate Secretary of the Board. 

Dated: May 29, 2015. 

By order of the Board of Directors. 

Federal Deposit Insurance Corporation. 

Robert E. Feldman, 

Executive Secretary. 

[FR Doc. 2015–13749 Filed 6–4–15; 8:45 am] 

BILLING CODE P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1427; Directorate 

Identifier 2013–NM–203–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 96–18–06 

for certain Airbus Model A320–211 and 

–231 airplanes. AD 96–18–06 currently 

requires visual inspections to detect 

cracks of the pressurized floor fittings at 

frame (FR) 36, and renewal of the zone 

protective finish or replacement of 

fittings with new fittings if necessary. 

Since we issued AD 96–18–06, an 

extended service goal analysis by the 

manufacturer revealed that the 

compliance times and repetitive 

inspection intervals should be reduced 

to meet the design service goal. This 

proposed AD would retain the 

requirements of AD 96–18–06, with 

reduced compliance times and 

repetitive inspection intervals. This 

proposed AD would also add Model 

A320–212 airplanes to the applicability. 

We are proposing this AD to detect and 

correct fatigue cracking in the 

pressurized floor fittings at FR 36, 

which could result in failure of a floor 

fitting and subsequent depressurization 

of the fuselage. 

DATES: We must receive comments on 

this proposed AD by July 20, 2015. 

ADDRESSES: You may send comments 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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

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–2015– 

1427; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (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 Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–1427; Directorate Identifier 

2013–NM–203–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 

On August 23, 1996, we issued AD 

96–18–06, Amendment 39–9730 (61 FR 

46703, September 5, 1996). AD 96–18– 

06 requires actions intended to address 

an unsafe condition on certain Airbus 

Model A320–211 and –231 airplanes. 

Since we issued AD 96–18–06, 

Amendment 39–9730 (61 FR 46703, 

September 5, 1996), an extended service 

goal analysis by the manufacturer 

revealed that the compliance times and 

repetitive inspection intervals must be 

reduced to meet the design service goal. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agency 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0226, dated September 

23, 2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for Airbus Model 

A320–211, –212, and –231 airplanes. 

The MCAI states: 

During center fuselage certification full 

scale fatigue test, damage was found on the 

pressurized floor fittings at Frame 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 [manufacturer serial 

number] MSN 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 [an] AD * * * [for 

Model A320–111, –211, and –231 airplanes] 

to require these repetitive inspections and, 

depending on findings, corrective action(s), 

while the modification was specified in that 

AD as optional terminating action for these 

inspections. 

Following new analysis in the frame of 

ESG (Extended Service Goal) exercise, the 

inspection thresholds and intervals have 

been revised to meet the original DSG 

(Design Service Goal). 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
32056 Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules 

For the reasons described above, this 

[EASA] AD retains the requirements of [a] 

DGAC France AD * * *, which is 

superseded, but requires these actions within 

reduced compliance times. [This EASA AD 

also adds Model A320–212 airplanes to its 

applicability.] 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating it in Docket No. FAA– 

2015–1427. 

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 frame (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. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 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 of this NPRM. 

FAA’s Determination and Requirements 

of This Proposed AD 

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 pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Unlike the required actions in the 

MCAI, this proposed AD would not 

permit further flight if damage 

(cracking) is detected during any 

inspection of the pressurized floor 

fittings at FR 36. Instead, this proposed 

AD would require repair of any damage 

before further flight. We find that, to 

achieve an adequate level of safety for 

the affected fleet, damaged structural 

elements must be replaced prior to 

further flight. This difference has been 

coordinated with EASA. 

Costs of Compliance 

We estimate that this proposed AD 

affects 13 airplanes of U.S. registry. 

The actions required by AD 96–18–06, 

Amendment 39–9730 (61 FR 46703, 

September 5, 1996), and retained in this 

proposed AD, take about 3 work-hours 

per product, at an average labor rate of 

$85 per work-hour. Required parts cost 

about $0 per product. Based on these 

figures, the estimated cost of the actions 

that are required by AD 96–18–06 is 

$255 per product. 

We also estimate that it would take 

about 11 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $0 per product. 

Based on these figures, we estimate the 

cost of this proposed AD on U.S. 

operators to be $12,155, or $935 per 

product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed 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. 

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) 

96–18–06, Amendment 39–9730 (61 FR 

46703, September 5, 1996), and adding 

the following new AD: 

Airbus: Docket No. FAA–2015–1427; 

Directorate Identifier 2013–NM–203–AD. 

(a) Comments Due Date 

We must receive comments by July 20, 

2015. 

(b) Affected ADs 

This AD replaces AD 96–18–06, 

Amendment 39–9730 (61 FR 46703, 

September 5, 1996). 

(c) Applicability 

This AD applies to Airbus Model A320– 

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

any category, manufacturer serial numbers 

0002 through 0104 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by an extended 

service goal analysis by the manufacturer, 

which revealed that the compliance times 

and repetitive inspection intervals should be 

reduced to meet the design service goal. We 

are issuing this AD to detect and correct 

fatigue cracking in the pressurized floor 

fittings at FR 36, which could result in failure 

of a floor fitting and subsequent 

depressurization of the fuselage. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules 32057 

(g) Retained Inspection 

This paragraph restates the requirements of 

paragraph (a) of AD 96–18–06, Amendment 

39–9730 (61 FR 46703, September 5, 1996), 

with revised service information for Airbus 

Model A320–211 and –231 airplanes. Prior to 

the accumulation of 16,000 total landings, or 

within 6 months after October 10, 1996 (the 

effective date of AD 96–18–06), whichever 

occurs later, perform a visual inspection to 

detect cracks of the 6 fittings of the 

pressurized floor at frame 36 under the lower 

surface panel, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1028, Revision 1, 

dated April 19, 1996; or Airbus Service 

Bulletin A320–57–1028, Revision 02, dated 

June 3, 2013. As of the effective date of this 

AD, use only Airbus Service Bulletin A320– 

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

accomplishing the actions required by this 

paragraph. Accomplishment of the initial 

inspection required by paragraph (i) of this 

AD terminates the actions required by this 

paragraph. 

(1) If no cracking is found, prior to further 

flight, renew the zone protective finish, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1028, Revision 1, dated April 19, 1996; or 

Airbus Service Bulletin A320–57–1028, 

Revision 02, dated June 3, 2013. As of the 

effective date of this AD, use only Airbus 

Service Bulletin A320–57–1028, Revision 02, 

dated June 3, 2013, for accomplishing the 

actions required by this paragraph. Repeat 

the visual inspection thereafter at intervals 

not to exceed 12,000 landings. 

(2) If only 1 of the 6 fittings is found to be 

cracked and that crack is less than or equal 

to 0.59 inch (15 mm) in length, prior to 

further flight, replace the cracked fitting with 

a new fitting, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1028, Revision 1, 

dated April 19, 1996; or Airbus Service 

Bulletin A320–57–1028, Revision 02, dated 

June 3, 2013. Thereafter, prior to the 

accumulation of 500 landings following 

accomplishment of this replacement, replace 

the remaining 5 fittings with new fittings, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1028, Revision 1, dated April 19, 1996; or 

Airbus Service Bulletin A320–57–1028, 

Revision 02, dated June 3, 2013. As of the 

effective date of this AD, use only Airbus 

Service Bulletin A320–57–1028, Revision 02, 

dated June 3, 2013, for accomplishing the 

actions required by this paragraph. 

(3) If only 1 of the 6 fittings is found to be 

cracked, and that crack is greater than 0.59 

inch (15 mm) in length, prior to further flight, 

replace all six fittings with new fittings, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1028, Revision 1, dated April 19, 1996; or 

Airbus Service Bulletin A320–57–1028, 

Revision 02, dated June 3, 2013. As of the 

effective date of this AD, use only Airbus 

Service Bulletin A320–57–1028, Revision 02, 

dated June 3, 2013, for accomplishing the 

actions required by this paragraph. 

(4) If 2 or more fittings are found to be 

cracked, prior to further flight, replace all 6 

fittings with new fittings, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1028, Revision 1, 

dated April 19, 1996; or Airbus Service 

Bulletin A320–57–1028, Revision 02, dated 

June 3, 2013. As of the effective date of this 

AD, use only Airbus Service Bulletin A320– 

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

accomplishing the actions required by this 

paragraph. 

(h) Retained Optional Terminating Action 

This paragraph restates the provisions of 

paragraph (b) of AD 96–18–06, Amendment 

39–9730 (61 FR 46703, September 5, 1996), 

with revised service information for Airbus 

Model A320–211 and –231 airplanes. 

Replacement of all 6 fittings with new 

fittings, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1028, Revision 01, 

dated April 19, 1996; or Airbus Service 

Bulletin A320–57–1028, Revision 02, dated 

June 3, 2013; constitutes terminating action 

for the inspection requirements of paragraph 

(g) of this AD. 

(i) New Inspection 

(1) At the latest of the times in paragraph 

(i)(1)(i), (i)(1)(ii), or (i)(1)(iii) of this AD: Do 

a detailed inspection of the pressurized floor 

fittings at frame 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. Accomplishment of 

the initial inspection required by this 

paragraph terminates the actions required by 

paragraph (g) of this AD. 

(i) Prior to the accumulation of 20,900 total 

flight cycles or 41,800 total flight hours, 

whichever occurs first. 

(ii) Prior to the accumulation of 9,300 flight 

cycles or 18,600 flight cycles since the most 

recent inspection required by paragraph (g) 

or (i) of this AD, whichever occurs first. 

(iii) At the earlier of the times specified in 

paragraph (i)(iii)(A) and (i)(iii)(B) of this AD. 

(A) Prior to the accumulation of 1,250 

flight cycles or 2,500 flight hours after the 

effective date of this AD, whichever occurs 

first. 

(B) Prior to the accumulation of 12,000 

flight cycles since the most recent inspection 

required by paragraph (g) or (i) of this AD. 

(2) If any crack is found during any 

inspection required by paragraph (i)(1) of this 

AD: Before further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA); or Airbus’s 

EASA Design Organization Approval (DOA). 

(j) New Optional Terminating Action 

Modification (replacement of aluminum 

fittings with titanium fittings) of the 

pressurized floor fittings at frame 36, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

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

is terminating action for the repetitive 

inspections required by paragraphs (g) and (i) 

of this AD. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

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

AMOC-REQUESTS@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. The AMOC 

approval letter must specifically reference 

this AD. 

(ii) AMOCs approved previously for AD 

96–18–06, Amendment 39–9730 (61 FR 

46703, September 5, 1996), are approved as 

AMOCs for the corresponding provisions 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 Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or Airbus’s EASA 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 

Airworthiness Directive 2013–0226, dated 

September 23, 2013, 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–2015–1427. 

(2) 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. 

You may view this service information at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

Issued in Renton, Washington, on May 19, 

2015. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–13340 Filed 6–4–15; 8:45 am] 

BILLING CODE 4910–13–P 


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