23232 Federal Register / Vol. 80, No. 80 / Monday, April 27, 2015 / Rules and Regulations 

Ge ́ne ́rale de l’Aviation Civile (DGAC), 

operators are required to contact the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA. The 

actions must otherwise be accomplished in 

accordance with the applicable CMRs. 

(h) Retained Transition/Grace Period for 

Maintenance Significant Item (MSI) 78.30.00 

Tasks 

This paragraph restates the requirements of 

paragraph (g) of AD 2007–14–05, 

Amendment 39–15127 (72 FR 39307, July 18, 

2007), with no changes. For tasks identified 

in MSI 78.30.00, ‘‘Thrust Reverser Actuation 

and Cowling,’’ of Section 2, ‘‘CMR ‘Two Star’ 

Tasks,’’ of Airbus A300–600 CMR AI/ST5/

829/85, Issue 12, dated February 2005; and 

Airbus A310 CMR AI/ST5/849/85, Issue 12, 

dated February 2005: The initial compliance 

time is within 2,000 flight cycles or 12 

months after August 22, 2007 (the effective 

date of AD 2007–14–05), whichever occurs 

later. Thereafter, actions identified in MSI 

78.30.00 must be accomplished within the 

repetitive interval specified in the applicable 

CMRs. Where the CMRs specify to contact 

the DGAC, operators are required to contact 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA, for 

such approvals. The actions must be 

accomplished in accordance with the 

applicable CMRs. 

(i) New Revision of Maintenance or 

Inspection Program 

Within 3 months after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, to incorporate Airbus 

A310 Airworthiness Limitations Section 

(ALS) Part 3, Certification Maintenance 

Requirements (CMR), dated November 30, 

2012; or Airbus A300–600 ALS Part 3, 

Certification Maintenance Requirements 

(CMR), dated April 18, 2012. Except as 

required by paragraph (k) of this AD, the 

initial compliance time for accomplishing the 

actions is at the applicable time specified in 

Airbus A310 ALS Part 3, Certification 

Maintenance Requirements (CMR), dated 

November 30, 2012; or Airbus A300–600 ALS 

Part 3, Certification Maintenance 

Requirements (CMR), dated April 18, 2012, 

as applicable; or within 3 months after the 

effective date of this AD; whichever occurs 

later. Accomplishing the requirements in this 

paragraph terminates the requirements in 

paragraph (g) of this AD. 

(j) New No Alternative Actions or Intervals 

After accomplishment of the revision 

required by paragraph (i) of this AD, no 

alternative actions (e.g., inspections) or 

intervals, may be used unless the actions or 

intervals are approved as an alternative 

method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (l) of this AD. 

(k) New Compliance Time for Model A300– 

600 Series Airplanes 

For CMR Task 213000–A0001–1–C, 

‘‘Pressurization Control,’’ as identified in 

Sub-part 3–1, CMR Tasks, of the Airbus 

A300–600 ALS Part 3, Certification 

Maintenance Requirements (CMR), dated 

April 18, 2012: The initial compliance time 

for the task is at the applicable time specified 

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

AD. 

(1) For airplanes having accumulated less 

than 40,000 total flight hours since first flight 

of the airplane as of the effective date of this 

AD: Before the accumulation of 40,001 total 

flight hours. 

(2) For airplanes having accumulated 

40,000 total flight hours or more since first 

flight of the airplane as of the effective date 

of this AD, and on which Aging Systems 

Maintenance (ASM) Task 213115–04–1, 

‘‘Cabin Pressure Safety Valve;’’ or 

Maintenance Review Board Report (MRBR) 

Tasks 21.30.00/06 and 21.30.00/08, 

‘‘Pressurization Control,’’ have been 

accomplished: Before the accumulation of 

14,000 flight hours after the most recent 

accomplishment of ASM Tasks 213115–04–1, 

or MRBR Tasks 21.30.00/06 and 21.30.00/08, 

whichever occurs later. 

(3) For airplanes having accumulated 

40,000 total flight hours or more since first 

flight of the airplane as of the effective date 

of this AD, and on which ASM Task 213115– 

04–1, or MRBR Tasks 21.30.00/06 and 

21.30.00/08, have not been accomplished: 

Within 3 months after the effective date of 

this AD. 

(l) 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; fax 425–227–1149. 

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

AMOC-REQUESTS@faa.gov. 

(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 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. 

(m) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0072, dated 

March 20, 2013, (corrected January 15, 2015) 

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–2014–0655. 

(n) 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 June 1, 2015. 

(i) Airbus A300–600 Airworthiness 

Limitations Section Part 3, Certification 

Maintenance Requirements, dated April 18, 

2012. 

(ii) Airbus A310 Airworthiness Limitations 

Section Part 3, Certification Maintenance 

Requirements, dated November 30, 2012. 

(4) The following service information was 

approved for IBR on August 22, 2007 (72 FR 

39307, July 18, 2007). 

(i) Airbus A300–600 Certification 

Maintenance Requirements AI/ST5/829/85, 

Issue 12, dated February 2005. 

(ii) Airbus A310 Certification Maintenance 

Requirements AI/ST5/849/85, Issue 12, dated 

February 2005. 

(5) For service information identified in 

this AD, contact Airbus SAS—EAW 

(Airworthiness Office), 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. 

(6) 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. 

(7) 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 April 9, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–09285 Filed 4–24–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0930; Directorate 

Identifier 2015–NM–040–AD; Amendment 

39–18144; AD 2015–08–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 


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Federal Register / Vol. 80, No. 80 / Monday, April 27, 2015 / Rules and Regulations 23233 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2014–26– 

53 and AD 2015–03–02 for certain 

Airbus Model A319–115, A319–133, 

A320–214, A320–232, and A320–233 

airplanes. AD 2014–26–53 required 

repetitive detailed visual inspections to 

detect discrepancies of the wing lower 

skin surface and inboard main landing 

gear (MLG) support rib lower flange 

location fasteners and, depending on 

findings, accomplishment of applicable 

corrective action(s). AD 2015–03–02 

required repetitive detailed visual 

inspections of the outboard MLG 

support rib lower flange fasteners for 

discrepancies, and corrective actions if 

necessary. This new AD retains the 

repetitive detailed visual inspections to 

detect discrepancies of the fasteners 

located in the wing lower skin surface 

and inboard MLG support rib lower 

flange with extended compliance times 

and repetitive intervals, and 

accomplishment of applicable corrective 

actions. This new AD also retains the 

repetitive detailed visual inspections of 

the outboard MLG support rib lower 

flange fasteners for discrepancies, and 

corrective actions if necessary. In 

addition, this new AD adds airplanes to 

the applicability. This AD was 

prompted by a determination that 

certain airplanes were missing from the 

applicability of AD 2014–26–53 and AD 

2015–03–02 and that those airplanes 

may be affected by the unsafe condition 

addressed in AD 2014–26–53 and AD 

2015–03–02. We are issuing this AD to 

detect and correct discrepancies of the 

fasteners at the external surface of the 

lower wing skin and inboard and 

outboard MLG support rib lower 

flanges, which could result in an 

airplane not meeting its maximum loads 

expected in service. This condition 

could result in structural failure. 

DATES: This AD becomes effective May 

12, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 12, 2015. 

We must receive comments on this 

AD by June 11, 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 AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

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

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

www.airbus.com. 

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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0930. 

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– 

0930; or in person at the Docket 

Operations office 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 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: 

Discussion 

On January 7, 2015, we issued AD 

2014–26–53, Amendment 39–18068 (80 

FR 3155, January 22, 2015). AD 2014– 

26–53 applied to certain Airbus Model 

A319–115, A319–133, A320–214, A320– 

232, and A320–233 airplanes. AD 2014– 

26–53 was prompted by reports of 

failure of certain fasteners located at the 

wing lower skin surface and inboard 

MLG support rib lower flange. AD 

2014–26–53 required repetitive detailed 

visual inspections to detect 

discrepancies of the wing lower skin 

surface and inboard MLG support rib 

lower flange location fasteners and, 

depending on findings, accomplishment 

of applicable corrective action(s). We 

issued AD 2014–26–53 to detect and 

correct discrepancies of the fasteners at 

the external surface of the lower wing 

skin and inboard MLG support rib lower 

flange, which could result in an airplane 

not meeting its maximum loads 

expected in service. This condition 

could result in structural failure. 

On January 30, 2015, we issued AD 

2015–03–02, Amendment 39–18098 (80 

FR 6897, February 9, 2015). AD 2015– 

03–02 applied to certain Airbus Model 

A319–115, A319–133, A320–214, A320– 

232, and A320–233 airplanes. AD 2015– 

03–02 was prompted by reports of 

failure of certain fasteners on the MLG 

support rib lower flange. AD 2015–03– 

02 required repetitive detailed visual 

inspections of the outboard MLG 

support rib lower flange fasteners for 

discrepancies, and corrective actions if 

necessary. We issued AD 2015–03–02 to 

detect and correct discrepancies of the 

fasteners at the outboard MLG support 

rib lower flange, which could result in 

an airplane not meeting its maximum 

loads expected in service. This 

condition could result in structural 

failure. 

Since we issued AD 2014–26–53, 

Amendment 39–18068 (80 FR 3155, 

January 22, 2015); and AD 2015–03–02, 

Amendment 39–18098 (80 FR 6897, 

February 9, 2015); we have determined 

that certain airplanes were missing from 

the applicability of AD 2014–26–53 and 

AD 2015–03–02. Airbus Model A319– 

132 airplanes are affected with the 

identified unsafe condition and should 

have been included in the applicability 

of those ADs. In addition, we have also 

determined that the repetitive detailed 

visual inspections to detect 

discrepancies of the wing lower skin 

surface and inboard MLG support rib 

lower flange could be extended from 8- 

day intervals to 60-day intervals. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2015–0026, dated February 19, 

2015 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for certain Airbus 

Model A319–115, A319–132, A319–133, 

A320–214, A320–232, and A320–233 

airplanes. The MCAI states: 

During production of wings, a number of 

taperlok fasteners were found failed after 

installation. The fasteners in question are 

located at the bottom skin of the Main 

Landing Gear (MLG) reinforcing plate, wing 

skin and Gear Support Rib 5 lower flange. 

Based on the results of the preliminary 

investigation, this affects only certain A319 


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23234 Federal Register / Vol. 80, No. 80 / Monday, April 27, 2015 / Rules and Regulations 

and A320 aeroplanes delivered since January 

2014. 

This condition, if not detected and 

corrected could reduce the design safety 

margin of the structure. 

Prompted by these findings, EASA issued 

Emergency AD 2014–0270–E (later revised) 

[which corresponds to certain requirements 

of AD 2014–26–53, Amendment 39–18068 

(80 FR 3155, January 22, 2015)] to require 

repetitive detailed inspections (DET) of the 

bottom skin taperlok fasteners at the MLG 

Rib 5 footprint location and, depending on 

findings, accomplishment of applicable 

corrective action(s). 

Since EASA AD 2014–0270R1 [which 

corresponds to certain requirements of AD 

2015–03–02, Amendment 39–18098 (80 FR 

6897, February 19, 2015)] was issued, based 

on in service feedback and further 

investigation, Airbus issued Revision 01 of 

Alert Operators Transmission (AOT) 

A57N006–14 to extend the original 8 

calendar days inspection interval to 60 

calendar days for the external area and for 

the internal inboard side. In addition, it was 

identified that the model A319–132 was 

missing from the [EASA] AD applicability. 

For the reasons described above, this AD 

retains the requirements of EASA AD 2014– 

0270R1, which is superseded, to amend the 

Applicability and to require those actions 

within the new thresholds and intervals. 

This [EASA] AD is still considered to be 

an interim action and further [EASA] AD 

action may follow. 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–0930. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Airbus Alert 

Operators Transmission (AOT) 

A57N006–14, Revision 01, dated 

February 16, 2015. The service 

information describes procedures for 

repetitive detailed visual inspections to 

detect discrepancies of the wing lower 

skin surface and inboard and outboard 

MLG support rib lower flange location 

fasteners and corrective actions. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

This service information is reasonably 

available at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–0930. Or see ADDRESSES for 

other ways to access this service 

information. 

FAA’s Determination and Requirements 

of This 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 issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because failure of more than two 

fasteners at the outboard MLG support 

rib lower flange could result in an 

airplane not meeting its maximum loads 

expected in-service. This condition 

could result in failure of the structure. 

Therefore, we determined that notice 

and opportunity for public comment 

before issuing this AD are impracticable 

and that good cause exists for making 

this amendment effective in fewer than 

30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2015–0930; 

Directorate Identifier 2015–NM–040– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of 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 AD. 

Costs of Compliance 

We estimate that this AD affects 148 

airplanes of U.S. registry. 

The actions required by AD 2014–26– 

53, Amendment 39–18068 (80 FR 3155, 

January 22, 2015); and AD 2015–03–2, 

Amendment 39–18098 (80 FR 6897, 

February 9, 2015); and retained in this 

AD, take about 2 work-hours per 

product, at an average labor rate of $85 

per work-hour. Based on these figures, 

the estimated cost of the actions that 

were required by AD 2014–26–53 and 

AD 2015–03–06 is $170 per product, per 

inspection cycle. 

We also estimate that it will take 

about 2 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $25,160, or $170 per 

product, per inspection cycle. 

In addition, we estimate that any 

fastener replacement will take about 3 

work-hours and require parts costing 

$400, for a cost of $655 per fastener 

replacement. We have no way of 

determining the number of aircraft that 

might need these actions. 

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 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. 


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Federal Register / Vol. 80, No. 80 / Monday, April 27, 2015 / Rules and Regulations 23235 

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: 

■ a. Removing Airworthiness Directive 

(AD) 2014–26–53, Amendment 39– 

18068 (80 FR 3155, January 22, 2015); 

and AD 2015–03–02, Amendment 39– 

18098 (80 FR 6897, February 9, 2015; 

and 

■ b. Adding the following new AD: 

2015–08–08 Airbus: Amendment 39–18144. 

Docket No. FAA–2015–0930; Directorate 

Identifier 2015–NM–040–AD. 

(a) Effective Date 

This AD becomes effective May 12, 2015. 

(b) Affected ADs 

This AD replaces the following: 

(1) AD 2014–26–53, Amendment 39–18068 

(80 FR 3155, January 22, 2015). 

(2) AD 2015–03–02, Amendment 39–18098 

(80 FR 6897, February 9, 2015). 

(c) Applicability 

This AD applies to Airbus Model A319– 

115, A319–132, A319–133, A320–214, A320– 

232, and A320–233 airplanes, certificated in 

any category, manufacturer serial numbers 

(MSN) 5817, 5826, 5837, 5848, 5855, 5864, 

5875, 5886, 5896, 5910, and 5918 and 

subsequent. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by a determination 

that certain airplanes were not included in 

the applicability of AD 2014–26–53, 

Amendment 39–18068 (80 FR 3155, January 

22, 2015); and AD 2015–03–02, Amendment 

39–18098 (80 FR 6897, February 9, 2015). 

This AD was also prompted by reports of 

failure of certain fasteners located at the wing 

lower skin surface, and inboard and outboard 

main landing gear (MLG) support rib lower 

flanges. We are issuing this AD to detect and 

correct discrepancies of the fasteners at the 

external surface of the lower wing skin and 

inboard and outboard MLG support rib lower 

flanges, which could result in an airplane not 

meeting its maximum loads expected in 

service. This condition could result in 

structural failure. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained for All Airplanes Except Airbus 

Model A319–132 Airplanes: Repetitive 

Inspections, With Extended Compliance 

Time and New Service Information 

This paragraph restates the requirements of 

paragraph (g) of AD 2014–26–53, 

Amendment 39–18068 (80 FR 3155, January 

22, 2015), with an extended compliance time 

and new service information. For Airbus 

Model A319–115, A319–133, A320–214, 

A320–232, and A320–233 airplanes: Within 

60 days after February 6, 2015 (the effective 

date of AD 2014–26–53), or within 60 days 

since the date of issuance of the original 

certificate of airworthiness or the original 

export certificate of airworthiness, or before 

further flight for any airplane that is not in 

operation for more than 60 days, whichever 

occurs later: Do the inspections required by 

paragraphs (g)(1) and (g)(2) of this AD, in 

accordance with Airbus Alert Operators 

Transmission (AOT) A57N006–14, Revision 

00, dated December 4, 2014; or Airbus AOT 

A57N006–14, Revision 01, dated February 

16, 2015. Repeat the inspections thereafter at 

intervals not to exceed 60 days. As of the 

effective date of this AD, only use Airbus 

AOT A57N006–14, Revision 01, dated 

February 16, 2015, to accomplish the actions 

required by this paragraph. 

(1) Do a detailed visual inspection of the 

external surface of the left-hand and righthand wing lower skin surface to detect 

missing or broken or migrated fasteners. 

(2) Do a detailed visual inspection of the 

inboard MLG support rib lower flange to 

detect missing or broken nuts or fastener 

tails. 

(h) Retained for All Airplanes Except Airbus 

Model A319–132 Airplanes: Corrective 

Actions for the Inspections Required by 

Paragraph (g)(1) of This AD, With New 

Service Information 

This paragraph restates the requirements of 

paragraph (h) of AD 2014–26–53, 

Amendment 39–18068 (80 FR 3155, January 

22, 2015), with new service information. 

(1) If, during any inspection required by 

paragraph (g)(1) of this AD, only one 

discrepancy (any missing or broken or 

migrated fastener) is found on the left- or 

right-side: Before further flight, do corrective 

actions in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA. Replacement of fasteners 

on an airplane does not constitute 

terminating action for any inspection 

required by paragraph (g) of this AD. 

(2) If, during any inspection required by 

paragraph (g)(1) of this AD, more than one 

discrepancy (any missing or broken or 

migrated fastener) is found on the left- or 

right-side: Before further flight, replace all 

affected fasteners on the affected side(s), in 

accordance with Airbus AOT A57N006–14, 

Revision 00, dated December 4, 2014; or 

Airbus AOT A57N006–14, Revision 01, dated 

February 16, 2015. One fastener per side may 

be missing or broken or migrated provided 

the applicable actions required by paragraph 

(h)(1) of this AD are done. Replacement of 

fasteners on an airplane does not constitute 

terminating action for any inspection 

required by paragraph (g) of this AD. As of 

the effective date of this AD, only use Airbus 

AOT A57N006–14, Revision 01, dated 

February 16, 2015, to accomplish the actions 

required by this paragraph. 

(i) Retained for All Airplanes Except Airbus 

Model A319–132 Airplanes: Corrective 

Actions for the Inspections Required by 

Paragraph (g)(2) of This AD, With New 

Service Information 

This paragraph restates the requirements of 

paragraph (i) of AD 2014–26–53, Amendment 

39–18068 (80 FR 3155, January 22, 2015), 

with new service information. 

(1) If, during any inspection required by 

paragraph (g)(2) of this AD, only one 

discrepancy (any missing or broken nut or 

fastener tail) is found on the left- or rightside: Before further flight, do corrective 

actions in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA. Replacement of fasteners 

on an airplane does not constitute 

terminating action for any inspection 

required by paragraph (g) of this AD. 

(2) If, during any inspection required by 

paragraph (g)(2) of this AD, more than one 

discrepancy (any missing or broken nut or 

fastener tail) is found on the left- or rightside: Before further flight, replace all affected 

fasteners on the affected side(s), in 

accordance with Airbus AOT A57N006–14, 

Revision 00, dated December 4, 2014; or 

Airbus AOT A57N006–14, Revision 01, dated 

February 16, 2015. One fastener per side may 

be missing or broken or migrated provided 

the applicable actions required by paragraph 

(i)(1) of this AD are done. Replacement of 

fasteners on an airplane does not constitute 

terminating action for any inspection 

required by paragraph (g) of this AD. As of 

the effective date of this AD, only use Airbus 

AOT A57N006–14, Revision 01, dated 

February 16, 2015, to accomplish the actions 

required by this paragraph. 

(j) Retained for All Airplanes Except Airbus 

Model A319–132 Airplanes: Repetitive 

Inspections of the Outboard MLG Support 

Rib Lower Flange, With New Service 

Information 

This paragraph restates the requirements of 

paragraph (g) of AD 2015–03–02, 

Amendment 39–18098 (80 FR 6897, February 

9, 2015), with new service information. For 

Airbus Model A319–115, A319–133, A320– 

214, A320–232, and A320–233 airplanes: 

Within 4 months after February 24, 2015 (the 

effective date of AD 2015–03–02), or within 

4 months after the date of issuance of the 

original certificate of airworthiness or the 

original export certificate of airworthiness, or 

before further flight for any airplane that is 

not in operation for more than 4 months, 

whichever occurs latest: Do a detailed visual 

inspection of the left and right outboard MLG 

support rib lower flange to detect any 

discrepancy (broken or missing fastener tails 

or nuts), in accordance with Airbus AOT 

A57N006–14, Revision 00, dated December 4, 


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23236 Federal Register / Vol. 80, No. 80 / Monday, April 27, 2015 / Rules and Regulations 

2014; or Airbus AOT A57N006–14, Revision 

01, dated February 16, 2015. Repeat the 

inspection thereafter at intervals not to 

exceed 4 months. As of the effective date of 

this AD, only use Airbus AOT A57N006–14, 

Revision 01, dated February 16, 2015, for the 

actions required by this paragraph. 

(k) Retained for All Airplanes Except Airbus 

Model A319–132 Airplanes: Corrective 

Actions for the Inspections Required by 

Paragraph (j) of This AD, With New Service 

Information 

This paragraph restates the requirements of 

paragraph (h) of AD 2015–03–02, 

Amendment 39–18098 (80 FR 6897, February 

9, 2015), with new service information. If, 

during any inspection required by paragraph 

(j) of this AD, any discrepancy is found on 

the left or right outboard MLG support rib 

lower flange: Before further flight, replace all 

affected fasteners on the affected side(s), in 

accordance with Airbus AOT A57N006–14, 

Revision 00, dated December 4, 2014; or 

Airbus AOT A57N006–14, Revision 01, dated 

February 16, 2015. Replacement of fasteners 

on an airplane does not constitute 

terminating action for the repetitive 

inspections required by paragraph (j) of this 

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

use Airbus AOT A57N006–14, Revision 01, 

dated February 16, 2015, for the actions 

required by this paragraph. 

(l) For Airbus Model A319–132 Airplanes: 

New Repetitive Inspections of External 

Surface of Wing Lower Skin and Inboard 

MLG Support Rib Lower Flange 

For Airbus Model A319–132 airplanes: 

Within 60 days after the effective date of this 

AD, or within 60 days since the date of 

issuance of the original certificate of 

airworthiness or the original export 

certificate of airworthiness, or before further 

flight for any airplane that is not in operation 

for more than 60 days, whichever occurs 

later: Do the inspections required by 

paragraphs (l)(1) and (l)(2) of this AD, in 

accordance with Airbus AOT A57N006–14, 

Revision 01, dated February 16, 2015. Repeat 

the inspections thereafter at intervals not to 

exceed 60 days. 

(1) Do a detailed visual inspection of the 

external surface of the left-hand and righthand wing lower skin surface to detect 

missing or broken or migrated fasteners. 

(2) Do a detailed visual inspection of the 

inboard MLG support rib lower flange to 

detect missing or broken nuts or fastener 

tails. 

(m) For Airbus Model A319–132 Airplanes: 

Corrective Actions for the Inspections 

Required by Paragraph (l)(1) of This AD 

(1) If, during any inspection required by 

paragraph (l)(1) of this AD, only one 

discrepancy (any missing or broken or 

migrated fastener) is found on the left- or 

right-side: Before further flight, do corrective 

actions in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA. Replacement of fasteners 

on an airplane does not constitute 

terminating action for any inspection 

required by paragraph (l) of this AD. 

(2) If, during any inspection required by 

paragraph (l)(1) of this AD, more than one 

discrepancy (any missing or broken or 

migrated fastener) is found on the left- or 

right-side: Before further flight, replace all 

affected fasteners on the affected side(s), in 

accordance with Airbus AOT A57N006–14, 

Revision 01, dated February 16, 2015. One 

fastener per side may be missing or broken 

or migrated provided the applicable actions 

required by paragraph (m)(1) of this AD are 

done. Replacement of fasteners on an 

airplane does not constitute terminating 

action for any inspection required by 

paragraph (l) of this AD. 

(n) For Airbus Model A319–132 Airplanes: 

Corrective Actions for the Inspections 

Required by Paragraph (l)(2) of This AD 

(1) If, during any inspection required by 

paragraph (l)(2) of this AD, only one 

discrepancy (any missing or broken nut or 

fastener tail) is found on the left- or rightside: Before further flight, do corrective 

actions in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA. Replacement of fasteners 

on an airplane does not constitute 

terminating action for any inspection 

required by paragraph (l) of this AD. 

(2) If, during any inspection required by 

paragraph (l)(2) of this AD, more than one 

discrepancy (any missing or broken nut or 

fastener tail) is found on the left- or rightside: Before further flight, replace all affected 

fasteners on the affected side(s), in 

accordance with Airbus AOT A57N006–14, 

Revision 01, dated February 16, 2015. One 

fastener per side may be missing or broken 

or migrated provided the applicable actions 

required by paragraph (n)(1) of this AD are 

done. Replacement of fasteners on an 

airplane does not constitute terminating 

action for any inspection required by 

paragraph (l) of this AD. 

(o) For Airbus Model A319–132 Airplanes: 

New Repetitive Inspections of Outboard 

MLG Support Rib Lower Flange 

For Airbus Model A319–132 airplanes: 

Within 4 months after the effective date of 

this AD, or within 4 months after the date of 

issuance of the original certificate of 

airworthiness or the original export 

certificate of airworthiness, or before further 

flight for any airplane that is not in operation 

for more than 4 months, whichever occurs 

later: Do a detailed visual inspection of the 

left and right outboard MLG support rib 

lower flange to detect any discrepancy 

(broken or missing fastener tails or nuts), in 

accordance with Airbus AOT A57N006–14, 

Revision 01, dated February 16, 2015. Repeat 

the inspection thereafter at intervals not to 

exceed 4 months. 

(p) For Airbus Model A319–132 Airplanes: 

Corrective Actions for the Inspections 

Required by Paragraph (o) of This AD 

If, during any inspection required by 

paragraph (o) of this AD, any discrepancy is 

found on the left or right outboard MLG 

support rib lower flange: Before further flight, 

replace all affected fasteners on the affected 

side(s), in accordance with Airbus AOT 

A57N006–14, Revision 01, dated February 

16, 2015. Replacement of fasteners on an 

airplane does not constitute terminating 

action for the repetitive inspections required 

by paragraph (o) of this AD. 

(q) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (l), (m)(2), (n)(2), (o), 

and (p) of this AD, if those actions were 

performed before the effective date of this AD 

using Airbus AOT A57N006–14, Revision 00, 

dated December 4, 2014, which was 

incorporated by reference in AD 2014–26–53, 

Amendment 39–18068 (80 FR 3155, January 

22, 2015). 

(r) Other FAA AD Provisions 

(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 

2014–26–53, Amendment 39–18068 (80 FR 

3155, January 22, 2015); and AD 2015–03–02, 

Amendment 39–18098 (80 FR 6897, February 

19, 2015); 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 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. 

(s) Special Flight Permits 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

(t) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0026, dated 

February 19, 2015, 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–2015–0930. 


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Federal Register / Vol. 80, No. 80 / Monday, April 27, 2015 / Rules and Regulations 23237 

(2) 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 Alert Operators Transmission 

A57N006–14, Revision 01, dated February 

16, 2015. 

(ii) Reserved. 

(3) 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. 

(4) 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. 

(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 Renton, Washington, on April 14, 

2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–09465 Filed 4–24–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE TREASURY 

Internal Revenue Service 

26 CFR Part 1 

[TD 9717] 

RIN 1545–BL77 

Allocation of Controlled Group 

Research Credit; Correction 

AGENCY: Internal Revenue Service (IRS), 

Treasury. 

ACTION: Final and temporary 

regulations; correction. 

SUMMARY: This document contains 

corrections to final regulations (TD 

9717) that were published in the 

Federal Register on Friday, April 3, 

2015 (80 FR 18096). The final 

regulations are relating to the allocation 

of the credit for increasing research 

activities (research credit) to 

corporations and trades or businesses 

under common control (controlled 

groups). 

DATES: This correction is effective April 

27, 2015 and applicable April 3, 2015. 

FOR FURTHER INFORMATION CONTACT: 

James Holmes at (202) 317–4137 (not a 

toll-free number). 

SUPPLEMENTARY INFORMATION: 

Background 

The final regulations (TD 9717) that 

are the subject of this correction is 

under section 41 of the Internal Revenue 

Code. 

Need for Correction 

As published, the final regulation (TD 

9717) contains errors that may prove to 

be misleading and are in need of 

clarification. 

Correction of Publication 

Accordingly, the final regulation (TD 

9717), that are the subject of FR Doc. 

2015–07331, are corrected as follows: 

1. On page 18096, in the preamble, 

under paragraph heading 

‘‘Background,’’ the last line, ‘‘Act’’ is 

corrected to read ‘‘American Taxpayer 

Relief Act of 2012, PL 112–240, H. R. 8 

(the ‘‘Act’’). 

2. On page 18097, in the third 

column, under the paragraph heading 

‘‘Explanation of Provisions’’, the first 

full paragraph, fourth line of the 

paragraph, ‘‘credit determined under 

41(a) for a’’ is corrected to read ‘‘credit 

determined under section 41(a) for a’’. 

Martin V. Franks, 

Chief, Publications and Regulations Branch, 

Legal Processing Division, Associate Chief 

Counsel, (Procedure and Administration). 

[FR Doc. 2015–09604 Filed 4–24–15; 8:45 am] 

BILLING CODE 4830–01–P 

DEPARTMENT OF THE TREASURY 

Internal Revenue Service 

26 CFR Part 1 

[TD 9715] 

RIN 1545–BH31 

Regulations Revising Rules Regarding 

Agency for a Consolidated Group; 

Correction 

AGENCY: Internal Revenue Service (IRS), 

Treasury. 

ACTION: Correcting amendment. 

SUMMARY: This document contains 

corrections to final regulations (TD 

9715) that were published in the 

Federal Register on April 1, 2015 (80 FR 

17314). The final regulations are 

regarding the agent for an affiliated 

group of corporations that files a 

consolidated return (consolidated 

group). 

DATES: This correction is effective on 

April 27, 2015 and applicable April 1, 

2015. 

FOR FURTHER INFORMATION CONTACT: 

Gerald Fleming at (202) 317–6975 or 

Richard M. Heinecke at (202) 317–6065 

(not a toll free number). 

SUPPLEMENTARY INFORMATION: 

Background 

The final regulations (TD 9715) that 

are the subject of this correction is 

under section 1502 of the Internal 

Revenue Code. 

Need for Correction 

As published, the final regulations 

(TD 9715) contain errors that may prove 

to be misleading and are in need of 

clarification. 

List of Subjects in 26 CFR Part 1 

Income taxes, Reporting and 

recordkeeping requirements. 

Correction of Publication 

Accordingly, 26 CFR part 1 is 

corrected by making the following 

correcting amendments: 

PART 1—INCOME TAXES 

■ Paragraph 1. The authority citation 

for part 1 continues to read in part as 

follows: 

Authority: 26 U.S.C. 7805 * * * 

■ Par. 2. Section 1.1502–77 is amended 

by revising the second sentence of 

paragraph (c)(1) and the first sentence of 

paragraph (g) to read as follows: 

§ 1.1502–77 Agent for the group. 

* * * * * 

(c) * * * (1) * * * Except as 

specifically provided otherwise in this 

paragraph (c), any entity that is an agent 

pursuant to paragraph (c)(3) of this 

section (agent following group structure 

change), paragraph (c)(5) of this section 

(agent designated by agent terminating 

without default successor), paragraph 

(c)(6) of this section (agent designated 

by Commissioner), or paragraph (c)(7) of 

this section (agent designated by 

resigning agent), or any entity 

subsequently serving as agent following 

such agent, acts as an agent for and 

under the same terms and conditions 

that apply to a common parent. * * * 

* * * * * 

(g) Examples. Unless otherwise 

indicated, all entities are domestic and 

have a calendar year taxable year, and 

each of P, S, S–1, S–2, S–3, T, U, V, W, 


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