Federal Register / Vol. 80, No. 86 / Tuesday, May 5, 2015 / Rules and Regulations 25589 

statements, and documents at such 

times, in such forms, and accompanied 

by such supporting data, as required by 

the CDFI Fund and the U.S. Department 

of the Treasury to ensure compliance 

with the requirements of this part. The 

United States Government, including 

the U.S. Department of the Treasury, the 

Comptroller General, and its duly 

authorized representatives, shall have 

full and free access to the Recipient’s 

offices and facilities, and all books, 

documents, records, and financial 

statements relevant to the award of the 

Federal funds and may copy such 

documents as they deem appropriate. 

(b) The Award Agreement provides 

that the provisions of the Act, this part, 

and the Award Agreement are 

enforceable under 12 U.S.C. 1818 of the 

Federal Deposit Insurance Act by the 

Appropriate Federal Banking Agency, as 

applicable, and that any violation of 

such provisions shall be treated as a 

violation of the Federal Deposit 

Insurance Act. Nothing in this 

paragraph (b) precludes the CDFI Fund 

from directly enforcing the Award 

Agreement as provided for under the 

terms of the Act. 

(c) The CDFI Fund will notify the 

Appropriate Federal Banking Agency 

before imposing any sanctions on a 

Recipient that is examined by or subject 

to the reporting requirements of that 

agency. The CDFI Fund will not impose 

a sanction described in section 

1806.500(b) if the Appropriate Federal 

Banking Agency, in writing, not later 

than 30 calendar days after receiving 

notice from the CDFI Fund: 

(1) Objects to the proposed sanction; 

(2) Determines that the sanction 

would: 

(i) Have a material adverse effect on 

the safety and soundness of the 

Recipient; or 

(ii) Impede or interfere with an 

enforcement action against that 

Recipient by the Appropriate Federal 

Banking Agency; 

(3) Proposes a comparable alternative 

action; and 

(4) Specifically explains: 

(i) The basis for the determination 

under paragraph (c)(2) of this section 

and, if appropriate, provides 

documentation to support the 

determination; and 

(ii) How the alternative action 

suggested pursuant to paragraph (c)(3) 

of this section would be as effective as 

the sanction proposed by the CDFI Fund 

in securing compliance and deterring 

future noncompliance. 

(d) Prior to imposing any sanctions 

pursuant to this section or an Award 

Agreement, the CDFI Fund shall, to the 

maximum extent practicable, provide 

the Recipient with written notice of the 

proposed sanction and an opportunity 

to comment. Nothing in this section, 

however, shall provide a Recipient to 

any formal or informal hearing or 

comparable proceeding not otherwise 

required by law. 

§ 1806.504 Retention of records. 

A Recipient must comply with all 

record retention requirements as set 

forth in the Uniform Administrative 

Requirements. 

Dated: April 30, 2015. 

Mary Ann Donovan, 

Director, Community Development Financial 

Institutions Fund. 

[FR Doc. 2015–10433 Filed 5–4–15; 8:45 am] 

BILLING CODE 4810–70–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0038; Directorate 

Identifier 2013–SW–023–AD; Amendment 

39–18146; AD 2015–09–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Type Certificate 

Previously Held by Eurocopter France) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Model EC225LP helicopters. This AD 

requires repetitive visual and tap test 

inspections of each main rotor blade 

(blade) leading edge stainless steel 

protective strip (strip) for a crack, cut, 

or blind or open debonding 

(debonding), and taking approved 

corrective measures. If there is a crack 

or if there is debonding that exceeds 

acceptable limits, this AD requires, 

before further flight, repairing or 

replacing the blade with an airworthy 

part. This AD was prompted by 

suspected water seepage through a crack 

in the blade strip resulting in significant 

debonding. The actions of this AD are 

intended to prevent loss of the blade 

strip, excessive vibrations induced by 

blade weight imbalance, and subsequent 

loss of control of the helicopter. 

DATES: This AD is effective June 9, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of June 9, 2015. 

ADDRESSES: For service information 

identified in this AD, contact Airbus 

Helicopters, Inc., 2701 N. Forum Drive, 

Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax 

(972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. It is also available 

on the Internet at http://

www.regulations.gov in Docket No. 

FAA–2014–0038. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov 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 European 

Aviation Safety Agency (EASA) AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Gary 

Roach, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On January 31, 2014, at 79 FR 5321, 

the Federal Register published our 

notice of proposed rulemaking (NPRM), 

which proposed to amend 14 CFR part 

39 by adding an AD that would apply 

to Airbus Helicopters. The NPRM 

proposed to require repetitive visual 

and tap test inspections of each blade 

strip for a crack, cut, or debonding. If 

there is a crack or if there is debonding 

beyond acceptable limits or located 

outside a specific area, the NPRM 

proposed to require, before further 

flight, repairing or replacing the blade 

with an airworthy part. If there is a cut 

in the blade root polyurethane 

protective strip, the NPRM proposed to 

require tap test inspecting the blade for 

debonding. The proposed requirements 

were intended to prevent loss of the 

blade strip, excessive vibrations 

induced by blade weight imbalance, and 

subsequent loss of control of the 

helicopter. 

The NPRM was prompted by AD No. 

2013–0103, dated May 2, 2013, issued 


rljohnson on DSK3VPTVN1PROD with RULES
25590 Federal Register / Vol. 80, No. 86 / Tuesday, May 5, 2015 / Rules and Regulations 

by EASA, which is the Technical Agent 

for the Member States of the European 

Union, to correct an unsafe condition 

for Eurocopter (now Airbus Helicopters) 

Model EC225LP helicopters with certain 

blades installed. EASA advises that an 

investigation of significant debonding of 

a blade strip revealed rapidly 

progressing debonding caused by water 

seepage through a crack in the blade 

strip. EASA issued AD 2013–0103 

requiring repetitive inspections of the 

blade strip to correct this condition. 

Comments 

After our NPRM (79 FR 5321, January 

31, 2014) was published, we received 

comments from 2 commenters. 

Request 

Two commenters requested that a 

helicopter be allowed to operate with a 

crack in the leading edge blade strip as 

long as the crack is within the limits 

prescribed by the manufacturer. The 

commenters stated that EASA and the 

manufacturer allow for a helicopter to 

fly if the blade strip has a crack that is 

within limits because the blade strip is 

sacrificial and nonstructural. The 

commenters state that requiring 

repairing or replacing the blade strip if 

there is a crack results in a higher cost 

and greater out-of-service time for 

operators without a justifiable or 

measured increase in safety. 

We agree with allowing a crack in the 

blade strip that is within limits and has 

been properly sealed. Therefore, we 

have changed paragraph (e)(5) of the AD 

to require sealing the crack instead of 

repairing or replacing the blade if there 

is a crack within acceptable limits. 

FAA’s Determination 

This helicopter has been approved by 

the aviation authority of France and is 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA, reviewed the 

relevant information, considered the 

comments received, and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

this same type design and that air safety 

and the public interest require adopting 

the AD requirements as proposed with 

the change described previously. This 

change is consistent with the intent of 

the proposals in the NPRM (79 FR 5321, 

January 31, 2014) and will not increase 

the economic burden on any operator 

nor increase the scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

Eurocopter issued Emergency Alert 

Service Bulletin No. 05A010, Revision 

2, dated April 22, 2013 (EASB), for the 

Model EC225LP helicopter and for the 

non-FAA typed certificated Model 

EC725AP military helicopter. The EASB 

specifies a visual check and tapping test 

of the bonding of the strip on the 

leading edge of the blades for cracks, 

cuts, and debonding and taking 

corrective actions as applicable. 

Revision 1 to the EASB changed the 

visual check and the tapping test so that 

they can be performed without 

removing the blades. Revision 2 

extended the applicability to additional 

part-numbered blades with a modified 

blade strip installed. This information is 

reasonably available at http://

www.regulations.gov in Docket No. 

FAA–2014–0038. Or see ADDRESSES for 

other ways to access this service 

information. 

Costs of Compliance 

We estimate that this AD affects 4 

helicopters of U.S. Registry. We estimate 

that operators may incur the following 

costs in order to comply with this AD. 

Labor costs are estimated at $85 per 

work hour. We estimate 4 work hours to 

inspect the helicopter for a total of $340 

per helicopter and $1,360 for the U.S. 

operator fleet per inspection cycle. If 

necessary, it will take 4 work hours to 

repair the blade and $600 for required 

parts for a total of $940 per helicopter. 

It will take about 5 work hours to 

replace a blade at a cost of $425 for 

labor. Parts will cost $315,495 to replace 

part number (P/N) 332A11–0050–01 and 

$403,650 to replace P/N 332A11–0055– 

00, for a total cost of $315,920 and 

$404,075, respectively. 

Regulatory Findings 

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 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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 adding 

the following new airworthiness 

directive (AD): 

2015–09–01 Airbus Helicopters (Type 

Certificate previously held by 

Eurocopter France): Amendment 39– 

18146, Docket No. FAA–2014–0038, 

Directorate Identifier 2013–SW–023–AD. 

(a) Applicability 

This AD applies to Model EC225LP 

helicopters with a main rotor blade (blade), 

part number 332A11.0050.00, 

332A11.0055.00, 332A11.0050.02, or 

332A11.0055.02, installed, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

loss of a blade stainless steel protective strip 

(strip), which could result in excessive 

vibrations induced by blade weight 

imbalance and subsequent loss of control of 

the helicopter. 

(c) Effective Date 

This AD becomes effective June 9, 2015. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

Within 15 hours time-in-service (TIS) and 

thereafter at intervals not to exceed 85 hours 

TIS, visually and tap test inspect each blade 

strip for a crack, a cut, or open and blind 

debonding. For purposes of this AD, open 

debonding, also known as edge bond 

separation, occurs when a bonded part 

becomes unattached (debonded) leaving the 

surface under it exposed to open air around 

the periphery of the part. Blind debonding 

occurs when a bonded part becomes 

unattached internally yet remains bonded 

around its entire periphery. 


rljohnson on DSK3VPTVN1PROD with RULES
Federal Register / Vol. 80, No. 86 / Tuesday, May 5, 2015 / Rules and Regulations 25591 

(1) If there is open or blind debonding 

within acceptable limits and the debonded 

area is located inside Area D of Figure 1 of 

Eurocopter Emergency Alert Service Bulletin 

No. 05A010, Revision 2, dated April 22, 2013 

(EASB), no further action is required until 

the next inspection. 

(2) If there is open or blind debonding and 

the debonded area is located outside Area D 

of Figure 1 of the EASB, before further flight, 

repair or replace the blade. 

(3) If there is open or blind debonding 

beyond acceptable limits, before further 

flight, repair or replace the blade. 

(4) If there is a cut in the blade root 

polyurethane protective strip as depicted in 

Area A of Figure 2 of the EASB, tap test 

inspect the area. 

(i) If there is no open and blind debonding, 

at intervals not to exceed 15 hours TIS, tap 

test inspect the blade strip in the blade root 

area, in the stainless steel leading edge/

neoprene junction area for open or blind 

debonding. 

(ii) If there is open or blind debonding 

within acceptable limits and the debonded 

area is located inside Area D of Figure 1 of 

the EASB, no further action is required until 

the next inspection. 

(iii) If there is open or blind and the 

debonded area is located outside Area D of 

Figure 1 of the EASB, before further flight, 

repair or replace the blade. 

(iv) If there is open or blind debonding 

beyond acceptable limits, before further 

flight, repair or replace the blade. 

(5) If there is a crack within acceptable 

limits, before further flight, seal the crack. If 

there is a crack beyond the acceptable limits, 

before further flight, repair or replace the 

blade. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Gary Roach, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2013–0103, dated May 2, 2013. You may 

view the EASA AD on the Internet at 

www.regulations.gov in Docket No. FAA– 

2014–0038. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6210 Main Rotor Blades. 

(i) 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 the AD specifies otherwise. 

(i) Eurocopter Emergency Alert Service 

Bulletin No. 05A010, Revision 2, dated April 

22, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus Helicopters, Inc., 

2701 N. Forum Drive, Grand Prairie, TX 

75052; telephone (972) 641–0000 or (800) 

232–0323; fax (972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on April 16, 

2015. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–09548 Filed 5–4–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1130; Directorate 

Identifier 2015–CE–008–AD; Amendment 

39–18150; AD 2015–09–04] 

RIN 2120–AA64 

Airworthiness Directives; DG 

Flugzeugbau GmbH Gliders 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for comments 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for DG 

Flugzeugbau GmbH Model DG–1000T 

gliders equipped with a Solo 

Kleinmotoren Model 2350 C engine that 

supersedes AD 2013–22–14 R1. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

issued by the aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as engine shaft failure with 

consequent propeller detachment. We 

are issuing this AD to require actions to 

address the unsafe condition on these 

products. 

DATES: This AD is effective May 26, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of May 26, 2015. 

We must receive comments on this 

AD by June 19, 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 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this AD, contact Solo Kleinmotoren 

GmbH, Postfach 600152, 71050 

Sindelfingen, Germany; telephone: +49 

7031 301–0; fax: +49 7031 301–136; 

email: aircraft@solo-germany.com; 

Internet: http://aircraft.solo-online.com/ 

com. You may review copies of the 

referenced service information at the 

FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. 

For information on the availability of 

this material at the FAA, call (816) 329– 

4148. It is also available on the Internet 

at http://www.regulations.gov by 

searching for locating Docket No. FAA– 

2015–1130. 

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– 

1130 or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket 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: Jim 

Rutherford, Aerospace Engineer, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4165; fax: 98160 329–4090; email: 

jim.rutherford@faa.gov. 


rljohnson on DSK3VPTVN1PROD with RULES