Federal Register / Vol. 80, No. 51 / Tuesday, March 17, 2015 / Proposed Rules 13799 

(g) Related Information 

(1) For more information about this AD, 

contact Tomasz Rakowski, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7735; fax: 781–238– 

7199; email: tomasz.rakowski@faa.gov. 

(2) GE GEnx-1B Service Bulletin (SB) No. 

73–0036, dated January 6, 2015, and GE 

GEnx-2B SB No. 73–0035, dated September 

16, 2014, which are not incorporated by 

reference in this proposed AD, can be 

obtained from GE using the contact 

information in paragraph (g)(3) of this 

proposed AD. 

(3) For service information identified in 

this proposed AD, contact General Electric 

Company, GE Aviation, Room 285, 1 

Neumann Way, Cincinnati, OH 45215; 

phone: 513–552–3272; email: geae.aoc@

ge.com. 

(4) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

March 6, 2015. 

Ann C. Mollica, 

Acting Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2015–05897 Filed 3–16–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0490; Directorate 

Identifier 2014–NM–018–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) 2008–22– 

20, for certain Airbus Model A330–200, 

A330–300, and A340–300 series 

airplanes. AD 2008–22–20 currently 

requires repetitive high frequency eddy 

current (HFEC) inspections for cracking, 

repair if necessary, and modification of 

the upper shell structure of the fuselage. 

Since we issued AD 2008–22–20, we 

have determined from a fatigue and 

damage tolerance evaluation that the 

compliance times must be reduced. This 

proposed AD would shorten certain 

compliance times. We are proposing 

this AD to prevent fatigue cracking of 

the upper shell structure of the fuselage, 

which could result in reduced structural 

integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 1, 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 SAS, 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@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– 

0490; 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1138; 

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–2015–0490; Directorate Identifier 

2014–NM–018–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 October 20, 2008, we issued AD 

2008–22–20, Amendment 39–15717 (73 

FR 66747, November 12, 2008). AD 

2008–22–20 requires actions intended to 

address an unsafe condition on certain 

Airbus Model A330–200, A330–300, 

and A340–300 series airplanes. 

Since we issued AD 2008–22–20, 

Amendment 39–15717 (73 FR 66747, 

November 12, 2008), it has been 

determined from a fatigue and damage 

tolerance evaluation that the 

compliance times for certain inspections 

and modification must be reduced. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0012R1, dated January 

24, 2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for the specified 

products. The MCAI states: 

During fatigue tests (EF3) on the A340–600, 

damage was found in the longitudinal 

doubler at the Vertical Tail Plane (VTP) 

attachment cut out between Frame (FR) 80 

and FR86. This damage occurred between 

58,341 and 72,891 simulated flight cycles 

(FC). 

Due to the higher Design Service Goal and 

different design of the affected structural area 

(e.g., doubler thickness) for A330–200/–300 

and A340–300 airplane series, the damage 

assessment concluded that these airplanes 

may be also potentially affected. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the upper shell structure between FR80 

and FR86. 

Prompted by these findings, EASA issued 

AD 2007–0284 [(http://ad.easa.europa.eu/

blob/easa_ad_2007_0284_superseded.pdf/

AD_2007-0284_1)] to require implementation 

of an inspection programme of this structural 

area using a high frequency eddy current 

(HFEC) method and a modification to 

improve the upper shell structure. 

Since that [EASA] AD was issued, in the 

frame of a new fatigue and damage tolerance 

evaluation, taking into account the airplane 


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utilisation, the inspection threshold and 

intervals have been reassessed and the 

conclusion was that the thresholds and 

intervals for inspection, as well as the 

threshold for modifying the airplane, must be 

reduced. 

For the reason described above, this 

[EASA] AD retains the requirements of EASA 

AD 2007–0284, which is superseded and 

introduces redefined thresholds and 

intervals. 

This [EASA] AD is revised to clarify that, 

under some conditions, accomplishment of a 

repair constitutes terminating action for the 

repetitive inspections. One of the outcome of 

this clarification is the deletion of paragraph 

(5) of this [EASA] AD. 

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– 

2015–0490. 

Initial compliance time thresholds 

range from 7,300 flight cycles or 47,600 

flight hours, and up to 25,400 flight 

cycles or 76,300 flight hours, depending 

on configuration and range. 

Repetitive compliance time 

thresholds range from 1,700 flight cycles 

or 11,300 flight hours, and up to 4,500 

flight cycles or 13,500 flight hours, 

depending on configuration. 

Widespread Fatigue Damage 

Structural fatigue damage is 

progressive. It begins as minute cracks, 

and those cracks grow under the action 

of repeated stresses. This can happen 

because of normal operational 

conditions and design attributes, or 

because of isolated situations or 

incidents such as material defects, poor 

fabrication quality, or corrosion pits, 

dings, or scratches. Fatigue damage can 

occur locally, in small areas or 

structural design details, or globally. 

Global fatigue damage is general 

degradation of large areas of structure 

with similar structural details and stress 

levels. Multiple-site damage is global 

damage that occurs in a large structural 

element such as a single rivet line of a 

lap splice joining two large skin panels. 

Global damage can also occur in 

multiple elements such as adjacent 

frames or stringers. Multiple-sitedamage and multiple-element-damage 

cracks are typically too small initially to 

be reliably detected with normal 

inspection methods. Without 

intervention, these cracks will grow, 

and eventually compromise the 

structural integrity of the airplane, in a 

condition known as widespread fatigue 

damage (WFD). As an airplane ages, 

WFD will likely occur, and will 

certainly occur if the airplane is 

operated long enough without any 

intervention. 

The FAA’s WFD final rule (75 FR 

69746, November 15, 2010) became 

effective on January 14, 2011. The WFD 

rule requires certain actions to prevent 

structural failure due to WFD 

throughout the operational life of 

certain existing transport category 

airplanes and all of these airplanes that 

will be certificated in the future. For 

existing and future airplanes subject to 

the WFD rule, the rule requires that 

DAHs establish a limit of validity (LOV) 

of the engineering data that support the 

structural maintenance program. 

Operators affected by the WFD rule may 

not fly an airplane beyond its LOV, 

unless an extended LOV is approved. 

The WFD rule (75 FR 69746, 

November 15, 2010) does not require 

identifying and developing maintenance 

actions if the DAHs can show that such 

actions are not necessary to prevent 

WFD before the airplane reaches the 

LOV. Many LOVs, however, do depend 

on accomplishment of future 

maintenance actions. As stated in the 

WFD rule, any maintenance actions 

necessary to reach the LOV will be 

mandated by airworthiness directives 

through separate rulemaking actions. 

In the context of WFD, this action is 

necessary to enable DAHs to propose 

LOVs that allow operators the longest 

operational lives for their airplanes, and 

still ensure that WFD will not occur. 

This approach allows for an 

implementation strategy that provides 

flexibility to DAHs in determining the 

timing of service information 

development (with FAA approval), 

while providing operators with certainty 

regarding the LOV applicable to their 

airplanes. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. This service 

information is reasonably available; see 

ADDRESSES for ways to access this 

service information. 

• Airbus Service Bulletin A330–53– 

3159, Revision 02, dated March 29, 

2010. The service information describes 

procedures for a modification of the 

fuselage, which includes inspections 

(e.g., eddy current rotating probe test of 

fastener holes for cracking, high 

frequency eddy current (HFEC) 

inspections for cracking of the upper 

shell structure of the fuselage, and 

checks of the fastener position for 

clearance) and applicable corrective 

actions (e.g., repair and rework). 

• Airbus Service Bulletin A330–53– 

3160, Revision 03, dated January 6, 

2012. The service information describes 

procedures for applicable actions, 

including an eddy current rotating 

probe test for cracking of the fastener 

holes and an HFEC inspection for cracks 

in the upper shell of the fuselage (and 

including checks of the fastener position 

for clearance and applicable corrective 

actions (e.g., repair and rework)), and a 

modification of the airplane upper shell 

structure of the fuselage between FR80 

and FR86. 

• Airbus Service Bulletin A330–53– 

3168, Revision 02, dated December 21, 

2011. The service information describes 

procedures for a HFEC inspection for 

cracking of the upper shell structure of 

the fuselage between FR80 and FR86. 

• Airbus Service Bulletin A340–53– 

4165, Revision 02, dated March 29, 

2010. The service information describes 

procedures for a modification of the 

fuselage, which includes inspections 

(e.g., eddy current rotating probe test of 

fastener holes for cracking, HFEC 

inspections for cracking of the upper 

shell structure of the fuselage, and 

checks of the fastener position for 

clearance) and applicable corrective 

actions (e.g., repair and rework). 

• Airbus Service Bulletin A340–53– 

4172, Revision 01, dated July 8, 2009. 

The service information describes 

procedures for inspections (e.g., rototest 

inspections of fastener holes for 

cracking, HFEC inspections for cracking 

of the upper shell structure of the 

fuselage, and checks of the fastener 

position for clearance) and modification 

of the airplane upper shell structure 

between FR80 and FR86 (including 

applicable corrective actions (e.g., repair 

and rework). 

• Airbus Service Bulletin A340–53– 

4174, Revision 02, dated December 21, 

2011. The service information describes 

procedures for a HFEC inspection for 

cracking of the upper shell structure of 

the fuselage between FR80 and FR86. 

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. 


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Federal Register / Vol. 80, No. 51 / Tuesday, March 17, 2015 / Proposed Rules 13801 

Differences Between This Proposed AD 

and the MCAI or Service Information 

Unlike the procedures described in 

the service information, this proposed 

AD would not permit further flight if 

cracks are detected in the upper shell 

structure. We have determined that, 

because of the safety implications and 

consequences associated with that 

cracking, any cracked upper shell 

structure must be repaired before further 

flight. This difference has been 

coordinated with the EASA and Airbus. 

Explanation of Compliance Time for 

Modification 

The compliance time for the 

modification specified in this proposed 

AD for addressing WFD was established 

to ensure that discrepant structure is 

modified before WFD develops in 

airplanes. Standard inspection 

techniques cannot be relied on to detect 

WFD before it becomes a hazard to 

flight. We will not grant any extensions 

of the compliance time to complete any 

AD-mandated service bulletin related to 

WFD without extensive new data that 

would substantiate and clearly warrant 

such an extension. 

Costs of Compliance 

We estimate that this proposed AD 

affects 26 airplanes of U.S. registry. We 

also estimate that it would take about 

208 work-hours per product to comply 

with the basic requirements (inspection 

and modification) of this proposed AD. 

The average labor rate is $85 per workhour. Required parts would cost about 

$28,360 per product. Based on these 

figures, we estimate the cost of this 

proposed AD on U.S. operators to be 

$1,197,040, or $46,040 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. 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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) 

2008–22–20, Amendment 39–15717 (73 

FR 66747, November 12, 2008), and 

adding the following new AD: 

Airbus: Docket No. FAA–2015–0490; 

Directorate Identifier 2014–NM–018–AD. 

(a) Comments Due Date 

We must receive comments by May 1, 

2015. 

(b) Affected ADs 

This AD replaces AD 2008–22–20, 

Amendment 39–15717 (73 FR 66747, 

November 12, 2008). 

(c) Applicability 

This AD applies to Airbus Model A330– 

201, –202, –203, –223, –243, –301, –302, 

–303, –321, –322, –323, –341, –342, and 

–343; and Model A340–311, –312, and –313 

airplanes; certificated in any category; all 

manufacturer serial numbers on which 

Airbus Modification 44205 has been 

embodied in production, except those on 

which Airbus Modification 52974 or 53223 

has been embodied in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by the results of a 

fatigue and damage tolerance evaluation that 

concluded existing compliance times must be 

reduced. We are issuing this AD to prevent 

fatigue cracking of the upper shell structure 

of the fuselage, which could result in 

reduced structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection for Airbus Model A330–300 

and A340–300 Airplanes, Except Model 

A340–300 Weight Variant (WV) 027 

Airplanes 

For Model A330–300 and A340–300 

airplanes, except Model A340–300 WV 027 

airplanes: At the applicable time specified in 

paragraph (g)(1) or (g)(2) of this AD, do a high 

frequency eddy current (HFEC) inspection for 

cracking of the upper shell structure between 

frame (FR) 80 and FR86, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A330–53–3168, Revision 02, 

dated December 21, 2011; or Airbus Service 

Bulletin A340–53–4174, Revision 02, dated 

December 21, 2011; as applicable. Repeat the 

inspection thereafter at the applicable time 

specified in paragraph 1.E., ‘‘COMPLIANCE,’’ 

of Airbus Service Bulletin A330–53–3168, 

Revision 02, dated December 21, 2011; or 

Airbus Service Bulletin A340–53–4174, 

Revision 02, dated December 21, 2011; as 

applicable. 

(1) For airplanes that, as of the effective 

date of this AD, have not been inspected in 

accordance with Airbus Service Bulletin 

A330–53–3168; or Airbus Service Bulletin 

A340–53–4174; as applicable: Inspect at the 

later of the times specified in paragraphs 

(g)(1)(i) and (g)(1)(ii) of this AD. 

(i) Before reaching the applicable threshold 

specified in paragraph 1.E., ‘‘COMPLIANCE,’’ 

of Airbus Service Bulletin A330–53–3168, 

Revision 02, dated December 21, 2011; or 

Airbus Service Bulletin A340–53–4174, 

Revision 02, dated December 21, 2011; as 

applicable for airplane model, configuration, 

and utilization, since the airplane’s first 

flight. 

(ii) Within the threshold defined in 

paragraph 1.E, ‘‘COMPLIANCE,’’ of Airbus 


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Service Bulletin A330–53–3168, Revision 01, 

dated February 15, 2008; or Airbus Service 

Bulletin A340–53–4174, Revision 01, dated 

February 15, 2008; as applicable for airplane 

model, configuration, and utilization since 

the airplane’s first flight; or within 12 months 

after the effective date of this AD; whichever 

occurs first. 

(2) For airplanes that, as of the effective 

date of this AD, have been inspected in 

accordance with Airbus Service Bulletin 

A330–53–3168; or Airbus Service Bulletin 

A340–53–4174; as applicable: Inspect at the 

later of the times specified in paragraphs 

(g)(2)(i) and (g)(2)(ii) of this AD. 

(i) Within the applicable interval specified 

in paragraph 1.E., ‘‘COMPLIANCE,’’ of 

Airbus Service Bulletin A330–53–3168, 

Revision 02, dated December 21, 2011; or 

Airbus Service Bulletin A340–53–4174, 

Revision 02, dated December 21, 2011; as 

applicable; to be counted from the last 

inspection. 

(ii) Within 12 months after the effective 

date of this AD without exceeding the 

intervals defined in paragraph 1.E, 

‘‘COMPLIANCE,’’ of Airbus Service Bulletin 

A330–53–3168, Revision 01, dated February 

15, 2008; or Airbus Service Bulletin A340– 

53–4174, Revision 01, dated February 15, 

2008; as applicable for airplane model, 

configuration, and utilization to be counted 

from the last inspection. 

(h) Corrective Action for Airbus Model 

A330–300 and A340–300 Airplanes, Except 

Model A340–300 WV 027 Airplanes 

If any crack is detected during any HFEC 

inspection required by the introductory text 

to paragraph (g) 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). Accomplishment of a repair 

for a specific area, as required by this 

paragraph, is terminating action for the 

repetitive HFEC inspections required by the 

introductory text to paragraph (g) of this AD, 

as applicable, for that specific repaired area 

only. The need and definition of subsequent 

repetitive inspections (if any) for that specific 

repaired area will be defined in the 

applicable repair 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). 

(i) Optional Terminating Action 

For Airbus Model A330–300 and A340– 

300 airplanes, except Model A340–300 WV 

027 airplanes: Modification, which includes 

inspections and applicable corrective actions, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

53–3159, Revision 02, dated March 29, 2010; 

or Airbus Service Bulletin A340–53–4165, 

Revision 02, dated March 29, 2010; as 

applicable; terminates the repetitive HFEC 

inspections required by the introductory text 

to paragraph (g) of this AD, except where 

Airbus Service Bulletin A330–53–3159, 

Revision 02, dated March 29, 2010; or Airbus 

Service Bulletin A340–53–4165, Revision 02, 

dated March 29, 2010; as applicable; 

specifies to contact the manufacturer, repair 

using a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA; or 

Airbus’s EASA DOA. 

(j) Inspection and Modification for Airbus 

Model A330–200 Airplanes 

(1) Within the compliance times specified 

in paragraph (j)(1)(i) or (j)(1)(ii) of this AD, 

whichever occurs later: Do all applicable 

actions, including an eddy current rotating 

probe test and an HFEC inspection for cracks, 

and modify the airplane upper shell structure 

between FR80 and FR86; in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A330–53–3160, Revision 03, 

dated January 6, 2012. 

(i) Within the compliance times identified 

in paragraph 1.E., ‘‘COMPLIANCE,’’ of 

Airbus Service Bulletin A330–53–3160, 

Revision 03, dated January 6, 2012, as 

applicable for airplane configuration and 

utilization since the airplane’s first flight. 

(ii) Within 12 months after the effective 

date of this AD without exceeding the 

threshold, defined in paragraph 1.E, 

‘‘COMPLIANCE,’’ of Airbus Service Bulletin 

A330–53–3160, Revision 02, dated March 29, 

2010, since the airplane’s first flight. 

(k) Inspection and Modification for Airbus 

Model A340–300 Airplanes, Only WV 027 

For Model A340–300 airplanes, WV 027 

only: Before the accumulation of 14,200 total 

flight cycles from the airplane’s first flight, 

do all applicable inspections and modify the 

airplane upper shell structure between FR80 

and FR86; in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A340–53–4172, Revision 01, 

dated July 8, 2009. 

(l) Corrective Action for Airbus Model A330– 

200 Airplanes; and Model A340–300 

Airplanes, Only WV 027 

If any crack is detected during the 

inspection required by paragraph (j) or (k) of 

this AD, before further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA; or 

Airbus’s EASA DOA; concurrently with 

modification required by paragraph (j) or (k) 

of this AD. 

(m) Definition of ‘‘Threshold’’ and ‘‘Interval’’ 

(1) For the purposes of this AD, the term 

‘‘Threshold,’’ as used in paragraph 1.E., 

‘‘COMPLIANCE,’’ of the service information 

specified in paragraphs (m)(2)(i) through 

(m)(2)(vi) of this AD means the total flight 

cycles or flight hours accumulated since the 

airplane’s first flight. 

(2) For the purposes of this AD, the term 

‘‘Interval’’ as used in paragraph 1.E., 

‘‘COMPLIANCE,’’ of the service information 

specified in paragraphs (m)(2)(i) through 

(m)(2)(vi) of this AD means the total flight 

cycles or flight hours accumulated since the 

last inspection, as applicable. 

(i) Airbus Service Bulletin A330–53–3168, 

dated September 19, 2007. 

(ii) Airbus Service Bulletin A330–53–3168, 

Revision 01, dated February 15, 2008. 

(iii) Airbus Service Bulletin A330–53– 

3168, Revision 02, dated December 21, 2011. 

(iv) Airbus Service Bulletin A340–53– 

4174, dated September 19, 2007. 

(v) Airbus Service Bulletin A340–53–4174, 

Revision 01, dated February 15, 2008. 

(vi) Airbus Service Bulletin A340–53– 

4174, Revision 02, dated December 21, 2011. 

(n) Credit for Previous Actions 

(1) For Model A330–300 and A340–300 

airplanes, except Model A340–300 WV 027 

airplanes: This paragraph provides credit for 

the modification specified in paragraph (i) of 

this AD, if those actions were performed 

before the effective date of this AD using the 

service information identified in paragraph 

(n)(1)(i), (n)(1)(ii), (n)(1)(iii), or (n)(1)(iv) of 

this AD, as applicable. This service 

information is not incorporated by reference 

in this AD. 

(i) Airbus Service Bulletin A330–53–3159, 

dated September 19, 2007. 

(ii) Airbus Service Bulletin A330–53–3159, 

Revision 01, dated June 15, 2009. 

(iii) Airbus Service Bulletin A340–53– 

4165, dated September 19, 2007. 

(iv) Airbus Service Bulletin A340–53– 

4165, Revision 01, dated June 17, 2009. 

(2) For Model A330–200 airplanes: This 

paragraph provides credit for the inspection 

and modification required by paragraph (j) of 

this AD, if those actions were performed 

before the effective date of this AD using the 

service information identified in paragraph 

(n)(2)(i), (n)(2)(ii), or (n)(2)(iii) of this AD, as 

applicable. This service information is not 

incorporated by reference in this AD. 

(i) Airbus Service Bulletin A330–53–3160, 

dated July 9, 2007. 

(ii) Airbus Service Bulletin A330–53–3160, 

Revision 01, dated April 28, 2009. 

(iii) Airbus Service Bulletin A330–53– 

3160, Revision 02, dated March 29, 2010. 

(3) For Model A340–300 airplanes, WV 027 

only: This paragraph provides credit for the 

inspection and modification required by 

paragraph (k) of this AD, if those actions 

were performed before the effective date of 

this AD using Airbus Service Bulletin A340– 

53–4172, dated July 10, 2007, which is not 

incorporated by reference in this AD. 

(o) 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; fax 425- 227–1149. 

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

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 


rljohnson on DSK3VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 51 / Tuesday, March 17, 2015 / Proposed Rules 13803 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference 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. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0012R1, dated 

January 24, 2014, 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–2015–0490. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@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 March 2, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–05720 Filed 3–16–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF EDUCATION 

34 CFR Subtitle A 

[Docket No.: ED–2015–OII–0006; (CFDA) 

Numbers: 84.411A (Scale-up grants), 

84.411B (Validation grants), and 84.411C 

(Development grants)] 

RIN 1855–ZA10 

Proposed Priority—Investing in 

Innovation Fund; Catalog of Federal 

Domestic Assistance 

AGENCY: Office of Innovation and 

Improvement, Department of Education. 

ACTION: Proposed priority. 

SUMMARY: The Assistant Deputy 

Secretary for Innovation and 

Improvement proposes a priority under 

the Investing in Innovation Fund (i3). 

The Assistant Deputy Secretary may use 

this priority for competitions in fiscal 

year (FY) 2015 and later years. The 

proposed priority would not repeal or 

replace currently established priorities 

for this program. 

DATES: We must receive your comments 

on or before April 16, 2015. 

ADDRESSES: Submit your comments 

through the Federal eRulemaking Portal 

or via postal mail, commercial delivery, 

or hand delivery. We will not accept 

comments by fax or by email or those 

submitted after the comment period. To 

ensure that we do not receive duplicate 

copies, please submit your comments 

only once. In addition, please include 

the Docket ID at the top of your 

comments. 

• Federal eRulemaking Portal: Go to 

www.regulations.gov to submit your 

comments electronically. Information 

on using Regulations.gov, including 

instructions for accessing agency 

documents, submitting comments, and 

viewing the docket, is available on the 

site under ‘‘Are you new to this site?’’ 

• Postal Mail, Commercial Delivery, 

or Hand Delivery: If you mail or deliver 

your comments about these proposed 

regulations, address them to Allison 

Moss, U.S. Department of Education, 

400 Maryland Avenue SW., Room 

4W319, Washington, DC 20202–5930. 

Privacy Note: The Department of 

Education’s (Department) policy is to make 

all comments received from members of the 

public available for public viewing in their 

entirety on the Federal eRulemaking Portal at 

www.regulations.gov. Therefore, commenters 

should be careful to include in their 

comments only information that they wish to 

make publicly available. 

FOR FURTHER INFORMATION CONTACT: 

Allison Moss. Telephone: (202) 205– 

7726 or by email: Allison.moss@ed.gov. 

If you use a telecommunications 

device for the deaf (TDD) or a text 

telephone (TTY), call the Federal Relay 

Service (FRS), toll free, at 1–800–877– 

8339. 

SUPPLEMENTARY INFORMATION: 

Summary of the Major Provisions of 

This Regulatory Action: In this 

document, the Department proposes a 

priority for the i3 program that would 

promote the implementation of 

comprehensive high school reform and 

redesign strategies. This proposed 

priority could be used in the 

Development, Validation, or Scale-up 

tier of the i3 program in future years, as 

appropriate. 

Costs and Benefits: The Assistant 

Deputy Secretary believes that the 

proposed priority would not impose 

significant costs on eligible applicants 

seeking assistance through the i3 

program. 

The proposed priority is designed to 

be used in conjunction with several 

priorities that have already been 

established under the i3 program, and 

no priority, whether it is used as an 

absolute or competitive preference 

priority, affects the overall amount of 

funding available to individual 

applicants in any given fiscal year. 

In addition, we note that participation 

in this program is voluntary. Potential 

applicants need to consider carefully 

the effort that will be required to 

prepare a strong application, their 

capacity to implement a project 

successfully, and their chances of 

submitting a successful application. We 

believe that the costs imposed on 

applicants by the proposed priority 

would be limited to paperwork burden 

related to preparing an application and 

that the benefits of implementing these 

proposals would outweigh any costs 

incurred by applicants. The costs of 

carrying out activities would be paid for 

with program funds and with matching 

funds provided by private-sector 

partners. Thus, the costs of 

implementation would not be a burden 

for any eligible applicants, including 

small entities. 

Invitation to Comment: We invite you 

to submit comments regarding this 

notice. 

We invite you to assist us in 

complying with the specific 

requirements of Executive Orders 12866 

and 13563 and their overall requirement 

of reducing regulatory burden that 

might result from this proposed priority. 

Please let us know of any further ways 

we could reduce potential costs or 

increase potential benefits while 

preserving the effective and efficient 

administration of the program. 

During and after the comment period, 

you may inspect all public comments 

about this notice by accessing 

Regulations.gov. You may also inspect 

the comments in person in Room 

4W335, 400 Maryland Avenue SW., 

Washington, DC, between the hours of 

8:30 a.m. and 4:00 p.m., Washington, 

DC time, Monday through Friday of 

each week except Federal holidays. 

Please contact the person listed under 

FOR FURTHER INFORMATION CONTACT in 

order to schedule a time to inspect 

comments in person. 

Assistance to Individuals With 

Disabilities in Reviewing the 

Rulemaking Record: On request we will 

provide an appropriate accommodation 

or auxiliary aid to an individual with a 

disability who needs assistance to 

review the comments or other 

documents in the public rulemaking 

record for this notice. If you want to 

schedule an appointment for this type of 

accommodation or auxiliary aid, please 

contact the person listed under FOR

FURTHER INFORMATION CONTACT. 

Purpose of Program: The i3 program 

addresses two related challenges. First, 


rljohnson on DSK3VPTVN1PROD with PROPOSALS