66668 Federal Register / Vol. 78, No. 215 / Wednesday, November 6, 2013 / Proposed Rules 

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 adding 

the following new AD: 

Diamond Aircraft Industries GmbH: Docket 

No. FAA–2013–0937; Directorate 

Identifier 2013–CE–029–AD. 

(a) Comments Due Date 

We must receive comments by December 

23, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Diamond Aircraft 

Industries GmbH Models DA 42 NG and DA 

42 M–NG airplanes, all serial numbers 

certificated in any category, except those that 

have Supplemental Type Certificate (STC) 

SA02725NY (http://rgl.faa.gov/Regulatory_

and_Guidance_Library/rgstc.nsf/0/286A2

9A0C46D66048625764900624649?Open

Document&Highlight=sa02725ny) 

incorporated. 

Note 1 to paragraph (c) of this AD: STC 

SA02725NY uses a different electrical system 

architecture and the unsafe condition 

addressed in this AD does not apply to that 

system. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 24: Electric Power. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as failure of 

the alternator indication system to indicate 

warning when one alternator is inoperative. 

We are issuing this proposed AD to prevent 

the undetected loss of one engine alternator, 

which could result in reduced capability of 

the electrical generating power system. 

(f) Actions and Compliance 

Unless already done, do the following 

actions as specified in paragraphs (f)(1) 

through (f)(3) of this AD, including all 

subparagraphs: 

(1) For all DA 42 NG airplanes: Within 12 

months after the effective date of this AD, 

install Secondary Configuration Card part 

number (P/N) 010–12074–02 ‘‘Additional 

ALTN FAIL trigger’’ and System Software P/ 

N 010–00670–10 following the 

Accomplishment/Instructions section of 

Diamond Aircraft Industries GmbH 

Mandatory Service Bulletin No. MSB 42NG– 

003/13, dated October 11, 2013; or the 

Accomplishment/Instructions section of 

Diamond Aircraft Industries GmbH 

Mandatory Service Bulletin No. MSB 42NG– 

003/12, dated July 8, 2013. 

(2) For DA 42 M–NG airplanes, serial 

numbers (S/Ns) 42.339, 42.MN001 through 

42.MN0026, and all S/Ns modified through 

Optional Service Bulletin (OSB) 42–081, 

using Work Instruction (WI) OSB–42–081 up 

to Revision 1 inclusive: Within 100 hours 

time-in-service after the effective date of this 

AD or within 12 months after the effective 

date of this AD, whichever occurs first: 

(i) Install GEA Alternator fail control cable 

P/N D62–2510–97–00–SB following the 

Instructions section of Diamond Aircraft 

Industries GmbH Work Instruction WI–MSB 

42MNG–006, dated July 8, 2013, as specified 

in the Accomplishments/Instructions section 

of Diamond Aircraft Industries GmbH 

Mandatory Service Bulletin No. MSB 

42MNG–006, July 8, 2013; and 

(ii) Install Secondary Configuration Card P/ 

N 010–12074–02 ‘‘Additional ALTN FAIL 

trigger’’ and System Software P/N 010– 

00670–10 following the Accomplishment/

Instructions section of Diamond Aircraft 

Industries GmbH Mandatory Service Bulletin 

No. MSB 42NG–003/13, dated October 11, 

2013; or the Accomplishment/Instructions 

section of Diamond Aircraft Industries GmbH 

Mandatory Service Bulletin No. MSB 42NG– 

003/12, dated July 8, 2013. 

(3) For all airplanes: As of the effective 

date of this AD, do not install on any airplane 

System Software prior to P/N 010–00670–10. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Mike Kiesov, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4144; fax: (816) 329– 

4090; email: mike.kiesov@faa.gov. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(h) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) AD No.: 2013–0224, dated 

September 19, 2013; Diamond Aircraft 

Industries GmbH Optional Service Bulletin 

OSB 42–081/1; Diamond Aircraft Industries 

GmbH Work Instruction WI–OSB 42–081, 

Rev. 1, both dated December 23, 2010; 

Diamond Aircraft Industries GmbH Optional 

Service Bulletin OSB 42–081; and Diamond 

Aircraft Industries GmbH Work Instruction 

WI–OSB 42–081, Rev. 0, both dated March 

17, 2010, for related information. You may 

examine the MCAI on the Internet at 

http://www.regulations.gov by searching for 

and locating it in Docket No. FAA–2013– 

0937. For service information related to this 

AD, contact Diamond Aircraft Industries 

GmbH, N.A. Otto-Stra+e 5, A–2700 Wiener 

Neustadt, Austria, telephone: +43 2622 

26700; fax: +43 2622 26700 1369; email: 

airworthiness@diamond-air.at; Internet: 

http://www.diamond-air.at. 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. 

Issued in Kansas City, Missouri, on 

October 30, 2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–26571 Filed 11–5–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0938; Directorate 

Identifier 2012–SW–057–AD] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France (Eurocopter) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for 


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Federal Register / Vol. 78, No. 215 / Wednesday, November 6, 2013 / Proposed Rules 66669 

Eurocopter Model SA–365N, SA– 

365N1, AS–365N2, and AS 365 N3 

helicopters. This proposed AD would 

require repetitively inspecting frame 

number (No.) 9 for a crack. This 

proposed AD is prompted by a report of 

a crack in frame No. 9 on an AS365 

helicopter. The proposed actions are 

intended to detect a crack and prevent 

loss of structural integrity and 

subsequent loss of control of the 

helicopter. 

DATES: We must receive comments on 

this proposed AD by January 6, 2014. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

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

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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 proposed AD, the 

foreign authority’s AD, the economic 

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 service information identified in 

this proposed AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

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

www.eurocopter.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. 

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: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD No. 2012– 

0108–E, dated June 15, 2012 (AD 2012– 

0108–E), to correct an unsafe condition 

for Eurocopter Model SA 365 N, SA 365 

N1, AS 365 N2, and AS 365 N3 

helicopters with a frame No. 9 installed, 

if certain ‘‘doublers or repairs have been 

installed.’’ EASA advises that a crack 

was discovered during the ‘‘T’’ 

inspection of an AS365 helicopter. The 

crack started at a rivet hole of a doubler 

that was installed on the frame No. 9 in 

accordance with Eurocopter Alert 

Service Bulletin (ASB) 53.00.42, dated 

January 31, 2001. EASA further states 

that structural alteration of frame No. 9 

by modifications or repairs can result in 

fatigue crack initiation under normal 

operational loads. According to EASA, 

this condition, if not corrected, could 

lead to crack propagation and failure of 

frame No. 9, which would adversely 

affect the structural integrity of the 

helicopter. For these reasons, AD 2012– 

0108–E requires repetitive inspections 

of frame No. 9 for a crack in the area of 

the doubler or any repair performed in 

the area of the latch support and 

stretcher support. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of France and 

are 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 its 

AD. We are proposing this AD because 

we evaluated all known relevant 

information and determined that an 

unsafe condition is likely to exist or 

develop on other products of the same 

type design. 

Related Service Information 

Eurocopter has issued one Emergency 

ASB (EASB) with two numbers: EASB 

No. 05.00.63, Revision 1, dated June 18, 

2012, for Model AS365 helicopters and 

EASB No. 05.00.30, Revision 1, dated 

June 18, 2012, for Model AS565 

helicopters. The EASB applies to 

helicopters with a frame No. 9 that has 

not been modified by modification 

(MOD) 07 53C17 or MOD 07 53D02, and 

that has had doublers installed or 

repairs performed in accordance with 

certain service instructions. The EASB 

describes procedures to inspect the 

frame No. 9 for a crack, and for 

contacting Eurocopter for further 

procedures if there is a crack. 

Proposed AD Requirements 

This proposed AD would require, for 

helicopters that have a No. 9 frame that 

has had any repair or alteration made, 

within 10 hours time-in-service (TIS) 

and every 110 hours TIS thereafter, 

inspecting the left-hand (LH) and righthand (RH) frame No. 9 for a crack in the 

areas of the latch support and stretcher 

support with a 10X or higher power 

magnifying glass. For all other 

helicopters, this proposed AD would 

require this inspection within 110 hours 

TIS and every 110 hours TIS thereafter. 

If there is a crack, the proposed AD 

would require, before further flight, 

repairing the crack. 

Differences Between This Proposed AD 

and the EASA AD 

The EASA AD requires contacting 

Eurocopter for repair instructions if 

there is a crack, and the proposed AD 

does not. The proposed AD would apply 

to all Eurocopter 365 helicopters, not 

just those that were altered or repaired 

in accordance with specific Eurocopter 

MODs. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 37 helicopters of U.S. 

Registry. We estimate that operators 

may incur the following costs in order 

to comply with this AD. At an average 


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labor rate of $85 per hour, inspecting LH 

and RH frame No. 9 would require about 

3 work-hours, for a cost per helicopter 

of $255 and a total cost to U.S. operators 

of $9,435 per inspection cycle. 

Repairing a cracked frame No. 9 would 

require about 20 work-hours, and 

required parts would cost about 

$10,000, for a cost per helicopter of 

$11,700. 

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 proposed 

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, 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 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 proposed 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. 

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 adding 

the following new airworthiness 

directive (AD): 

Eurocopter France Helicopters: Docket No. 

FAA–2013–0938; Directorate Identifier 

2012–SW–057–AD. 

(a) Applicability 

This AD applies to Eurocopter France 

(Eurocopter) Model SA–365N, SA–365N1, 

AS–365N2, and AS 365 N3 helicopters, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in frame number (No.) 9, which could 

result in failure of frame No. 9, loss of 

structural integrity, and subsequent loss of 

control of the helicopter. 

(c) Comments Due Date 

We must receive comments by January 6, 

2014. 

(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 

(1) For helicopters that have any repair or 

alteration to the frame No. 9, within 10 hours 

time-in-service (TIS) and thereafter at 

intervals not to exceed 110 hours TIS, using 

a 10X or higher power magnifying glass, 

inspect the left-hand (LH) and right-hand 

(RH) frame No. 9 for a crack in the area of 

the latch support and stretcher support, as 

depicted in Figure 1 of Eurocopter AS365 

Emergency Alert Service Bulletin No. 

05.00.63, Revision 1, dated June 18, 2012. 

(2) For all other helicopters, within 110 

hours TIS and thereafter at intervals not to 

exceed 110 hours TIS, perform the inspection 

in paragraph (e)(1) of this AD. 

(3) If there is a crack, before further flight, 

repair the frame No. 9. Repairing a frame is 

not terminating action for the repetitive 

inspections required by paragraphs (e)(1) and 

(e)(2) of this AD. 

(f) Special flight permit 

Special flight permits may be issued for up 

to 10 hours TIS and a maximum crack length 

of 80 mm. 

(g) 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. 

(h) Additional Information 

(1) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) 

Emergency AD No. 2012–0108–E, dated June 

15, 2012. You may view the EASA AD on the 

Internet at http://www.regulations.gov in 

Docket number FAA–2013–0938. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5300: Fuselage Structure (General). 

Issued in Fort Worth, Texas, on October 30, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–26568 Filed 11–5–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOUSING AND 

URBAN DEVELOPMENT 

24 CFR Part 214 

[Docket No. FR–5339–N–02] 

Housing Counseling Program: New 

Certification Requirements; Extension 

of Public Comment Period 

AGENCY: Office of the Assistant 

Secretary for Housing—Federal Housing 

Commissioner, HUD. 

ACTION: Proposed rule; extension of 

public comment period. 

SUMMARY: On September 13, 2013, HUD 

published a rule in the Federal Register 

inviting public comment on proposed 

changes to the Housing Counseling 

Program regulations for the purpose of 

implementing the Dodd-Frank Wall 

Street Reform and Consumer Protection 

Act amendments to the housing 

counseling statute. This document 

announces that HUD is extending the 

public comment period, for an 

additional 30-day period, to December 

12, 2013. 

DATES: Comment Due Date: For the 

proposed rule published on September 


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