Federal Register / Vol. 78, No. 128 / Wednesday, July 3, 2013 / Proposed Rules 40069 

incorporate Chapter 5–40–00, Airworthiness 

Limitations, of the Dassault Falcon 7X MM 

DGT 107838, Revision 2, dated August 25, 

2011, into the MM. 

(1) The initial compliance time for the 

operational test of the HSTS trim emergency 

command is within 650 flight hours after the 

modification required by paragraph (o) of this 

AD. 

(2) The initial compliance time for the 

operational test of the HSTS electric motors 

reversion relays is within 5,050 flight hours 

after the modification required by paragraph 

(o) of this AD. 

(3) Accomplishment of the actions required 

in paragraph (q) of this AD terminates the 

actions required by paragraph (l) of this AD. 

(r) New Limitations for Alternative Actions 

or Intervals 

After accomplishing the revision required 

by paragraph (q) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an AMOC in accordance with 

the procedures specified in paragraph (s) of 

this AD. 

(s) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, Transport Airplane Directorate, 

ANM–116, 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: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1137; 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 inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. AMOCs approved previously in 

accordance with AD 2011–16–01, 

Amendment 39–16759 (76 FR 47424, August 

5, 2011), are approved as AMOCs for the 

corresponding provisions of this AD. 

(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. 

(t) Related Information 

(1) Refer to MCAI EASA Airworthiness 

Directive 2011–0241, dated December 19, 

2011, and the service information specified 

in paragraphs (t)(1)(i) though (t)(1)(ix) of this 

AD. 

(i) Chapter 5–40–00, Airworthiness 

Limitations, of the Dassault Falcon 7X MM 

DGT 107838, Revision 2, dated August 25, 

2011. 

(ii) Dassault Change Proposal CP009 to 

Chapter 5–40- 00 of Dassault Falcon 7X 

Maintenance Manual), dated June 10, 2011. 

(iii) Dassault Falcon 7X Airplane Flight 

Manual, Revision 12, dated June 16, 2011. 

(iv) Dassault Falcon 7X Airplane Flight 

Manual, Revision 13, dated August 29, 2011. 

(v) Dassault Mandatory Service Bulletin 

7X–211, Revision 2, including New Standard 

Installation Checklist and Appendix A, dated 

June 22, 2011, including FCS Data Loading 

Procedure, Issue D, dated May 28, 2010. 

(vi) Dassault Mandatory Service Bulletin 

7X–212, Revision 2, dated July 7, 2011. 

(vii) Dassault Mandatory Service Bulletin 

7X–214, dated August 30, 2011. 

(viii) Dassault Mandatory Service Bulletin 

7X–214, Revision Erratum, dated January 26, 

2012. 

(ix) Dassault Service Bulletin 7X–213, 

dated June 22, 2011. 

(2) For service information identified in 

this AD, contact Dassault Falcon Jet, P.O. Box 

2000, South Hackensack, New Jersey 07606; 

telephone 201–440–6700; Internet http:// 

www.dassaultfalcon.com. You may review 

copies of the 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. 

Issued in Renton, Washington, on June 14, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–15949 Filed 7–2–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0539; Directorate 

Identifier 2012–NM–145–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) 2000–12– 

11, that applies to certain Model A300 

B4–600 and Model A300 B4–600R series 

airplanes. That AD currently requires 

repetitive inspections to detect cracks in 

the bolt holes inboard and outboard of 

rib 9 on the bottom booms of the front 

and rear wing spars, and repair if 

necessary. Since we issued that AD, we 

have determined through a fleet survey 

and an updated fatigue and damage 

tolerance analysis that the risk for 

fatigue cracking on the front and rear 

spar bottom booms is higher than was 

initially determined. This proposed AD 

would reduce the initial inspection 

compliance time and repetitive 

inspection interval. We are proposing 

this AD to detect and correct fatigue 

cracks in the bolt holes of the wing 

spars, which could result in reduced 

structural integrity of a wing spar. 

DATES: We must receive comments on 

this proposed AD by August 19, 2013. 

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— 

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. You 

may review copies of the 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; 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 

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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: (425) 227–2125; 

fax: (425) 227–1149. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
40070 Federal Register / Vol. 78, No. 128 / Wednesday, July 3, 2013 / Proposed Rules 

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–2013–0539; Directorate Identifier 

2012–NM–145–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 June 9, 2000, we issued AD 2000– 

12–11, Amendment 39–11789 (65 FR 

37853, June 19, 2000). That AD requires 

actions intended to address an unsafe 

condition on the products listed above. 

Since we issued AD 2000–12–11, the 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0138, 

dated July 26, 2012 (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: 

Full fatigue tests carried out by the 

manufacturer revealed crack initiation from 

the bolts holes at inboard and outboard of rib 

9, on the front and rear spar bottom booms. 

Similar cracks at the same area were reported 

by A300–600 aeroplane operators. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

To address this unsafe condition, 

[Direction Ge ́ne ́rale de l’Aviation Civile] 

DGAC France issued AD 94–208–169(B)R2 

[which corresponds to FAA AD 95–07–05 

Amendment 39–9187 (60 FR 17990, April 10, 

1995)] to require an ultrasonic inspection of 

holes inboard and outboard of rib 9 on the 

front and rear spar bottom booms on Left 

Hand and Right Hand wings. 

Since that [DGAC] AD was issued, a fleet 

survey and updated Fatigue and Damage 

Tolerance analysis have been performed in 

order to substantiate the second A300–600 

Extended Service Goal (ESG2) exercise. The 

results of these analyses have shown that the 

risk for these aeroplanes is higher than 

initially determined and that, consequently, 

the inspection threshold and interval must be 

reduced to allow timely detection of cracks 

and the accomplishment of an applicable 

corrective action [and related investigative 

action]. 

For the reasons explained above, this new 

[EASA] AD retains the requirements of DGAC 

France AD 94–208–169(B)R2, which is 

superseded, and requires the 

accomplishment instructions within the new 

thresholds and intervals specified in 

Revision 04 of Airbus Mandatory Service 

Bulletin (SB) A300–57–6037 [dated February 

24, 2011]. 

The related investigative action 

includes doing inspections for cracking. 

The corrective actions include 

oversizing holes and installing new 

fasteners, and for certain conditions, 

contacting the FAA or EASA (or its 

delegated agent) for instructions. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A300–57–6037, Revision 04, 

dated February 24, 2011. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

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. 

Differences Between This AD and the 

MCAI or Service Information 

Airbus Mandatory Service Bulletin 

A300–57–6037, Revision 04, dated 

February 24, 2011, specifies to contact 

the manufacturer for instructions on 

how to repair certain conditions, but 

this proposed AD would require 

repairing those conditions using a 

method approved by the FAA or the 

EASA (or its delegated agent). In light of 

the type of repair that would be required 

to address the unsafe condition, and 

consistent with existing bilateral 

airworthiness agreements, we have 

determined that, for this proposed AD, 

a repair approved by the FAA or the 

EASA (or its delegated agent) would be 

acceptable for compliance with this 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 29 products of U.S. registry. 

We estimate that it would take about 

18 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Required parts 

would cost about $2,874 per product. 

Where the service information lists 

required parts costs that are covered 

under warranty, we have assumed that 

there will be no charge for these parts. 

As we do not control warranty coverage 

for affected parties, some parties may 

incur costs higher than estimated here. 

Based on these figures, we estimate the 

cost of the proposed AD on U.S. 

operators to be $127,716, or $4,404 per 

product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 128 / Wednesday, July 3, 2013 / Proposed Rules 40071 

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. 

We prepared a regulatory 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 

removing airworthiness directive (AD) 

2000–12–11, Amendment 39–11789 (65 

FR 37853, June 19, 2000), and adding 

the following new AD: 

Airbus: Docket No. FAA–2013–0539; 

Directorate Identifier 2012–NM–145–AD. 

(a) Comments Due Date 

We must receive comments by August 19, 

2013. 

(b) Affected ADs 

This AD supersedes AD 2000–12–11, 

Amendment 39–11789 (65 FR 37853, June 

19, 2000). 

(c) Applicability 

This AD applies to Airbus Model A300 B4– 

601, B4–603, B4–620, B4–622, B4–605R and 

B4–622R airplanes; certificated in any 

category; all manufacturer serial numbers, 

except airplanes on which Airbus 

Modification 10161 has been incorporated in 

production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by a fleet survey 

and an updated fatigue and damage tolerance 

analysis indicating a high risk for fatigue 

cracking on the front and rear spar bottom 

booms. We are issuing this AD to detect and 

correct fatigue cracks in the bolt holes of the 

wing spars, which could result in reduced 

structural integrity of a wing spar. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Repetitive Inspections 

At the applicable time specified in 

paragraph (g)(1) or (g)(2) of this AD: Perform 

an ultrasonic inspection to detect fatigue 

cracking of the bolt holes inboard and 

outboard of rib 9 on the bottom booms of the 

front and rear wing spars, in accordance with 

the Accomplishment Instruction of Airbus 

Mandatory Service Bulletin A300–57–6037, 

Revision 04, dated February 24, 2011, except 

as specified in paragraph (k) of this AD. 

Repeat the inspection thereafter at intervals 

not to exceed the applicable time specified in 

paragraph (h) of this AD. 

(1) For normal range airplanes, at the later 

of the times in paragraphs (g)(1)(i) and 

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

(i) Within 14,100 flight cycles or 30,400 

flight hours since airplane first flight or 

within 14,100 flight cycles or 30,400 flight 

hours since airplane modification done as 

specified in the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

57–6039, whichever occurs first. 

(ii) Within 1,600 flight cycles or 3,400 

flight hours, whichever occurs first after the 

effective date of this AD. 

(2) For short range airplanes, at the later of 

the times in paragraphs (g)(2)(i) and (g)(2)(ii) 

of this AD. 

(i) Within 15,200 flight cycles or 22,800 

flight hours since airplane first flight, or 

since airplane modification done as specified 

in the Accomplishment Instructions of 

Airbus Service Bulletin A300–57–6039, 

whichever occurs first. 

(ii) Within 1,700 flight cycles or 2,500 

flight hours, whichever occurs first after the 

effective date of this AD. 

(h) Repetitive Inspection Compliance Times 

At the applicable time specified in 

paragraph (h)(1) or (h)(2) of this AD, repeat 

the inspection required by paragraph (g) of 

this AD. 

(1) For normal range airplanes: Repeat the 

inspection thereafter at intervals not to 

exceed 3,900 flight cycles or 8,400 flight 

hours, whichever occurs first. 

(2) For short range airplanes: Repeat the 

inspection thereafter at intervals not to 

exceed 4,200 flight cycles or 6,300 flight 

hours, whichever occurs first. 

(i) Corrective Action for Cracking 

If any crack is found during any inspection 

required by paragraph (g) of this AD: Before 

further flight, repair the cracking including 

applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–57–6037, 

Revision 04, dated February 24, 2011, except 

as specified in paragraph (k) of this AD. Do 

related investigative and corrective actions 

before further flight. Thereafter, repeat the 

inspection required by paragraph (g) of this 

AD at intervals not to exceed the applicable 

time specified in paragraph (h) of this AD. 

Corrective actions required by this paragraph 

do not constitute terminating action for the 

repetitive inspections required by paragraph 

(h) of this AD. 

(j) Definition of Short Range and Long Range 

Airplanes 

For purposes of this AD, short range 

airplanes are those with an average flight 

time lower than 1.5 flight hours, and normal 

range airplanes are those with an average 

flight time equal to or higher than 1.5 flight 

hours. 

(k) Exception to Service Information 

Where the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A300–57– 

6037, Revision 04, dated February 24, 2011, 

specify contacting Airbus for an approved 

repair: Before further flight, contact either the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent), for instructions and do 

those instructions. 

(l) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g) and (h) of this AD, 

if those actions were performed before the 

effective date of this AD using any of the 

service bulletins specified in paragraphs 

(l)(1) through (l)(4) of this AD. 

(1) Airbus Mandatory Service Bulletin 

A300–57–6037, dated August 1, 1994. 

(2) Airbus Mandatory Service Bulletin 

A300–57–6037, Revision 01, dated August 

31, 1995. 

(3) Airbus Mandatory Service Bulletin 

A300–57–6037, Revision 02, dated January 9, 

2001. 

(4) Airbus Mandatory Service Bulletin 

A300–57–6037, Revision 03, dated January 

11, 2002. 

(m) 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; 

phone: (425) 227–2125; 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 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(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. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
40072 Federal Register / Vol. 78, No. 128 / Wednesday, July 3, 2013 / Proposed Rules 

(3) AMOCs Approved Previously: AMOCs 

approved previously in accordance with AD 

2000–12–11, Amendment 39–11789 (65 FR 

37853, June 19, 2000), are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information European 

Aviation Safety Agency Airworthiness 

Directive 2012–0138, dated July 26, 2012, 

and the service information specified in 

paragraphs (m)(1)(i) through (m)(1)(iii) of this 

AD; for related information. 

(i) Airbus Mandatory Service Bulletin 

A300–57–6037, Revision 04, dated February 

24, 2011. 

(ii) Airbus Service Bulletin A300–57–6037, 

dated August 1, 1994. 

(iii) Airbus Service Bulletin A300–57– 

6037, Revision 01, dated August 31, 1995. 

(2) 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.airwortheas@airbus.com; Internet http:// 

www.airbus.com. You may review copies of 

the 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. 

Issued in Renton, Washington, on June 18, 

2013. 

John Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–15959 Filed 7–2–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0573; Directorate 

Identifier 2012–SW–042–AD] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

serial-numbered Eurocopter France 

(Eurocopter) Model AS332C1 and 

AS332L1 helicopters. This proposed AD 

would require replacing the rivets on 

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

Y350 longitudinal beams (longitudinal 

beams Y350). This proposed AD is 

prompted by a report that nonconforming rivets had been installed on 

an AS332 helicopter during a 

production modification. The proposed 

actions are intended to prevent failure 

of the longitudinal beams Y350 and 

subsequent loss of control of the 

helicopter. 

DATES: We must receive comments on 

this proposed AD by September 3, 2013. 

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 

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 Emergency AD 

No.: 2012–0046–E, dated March 21, 

2012 (EAD 2012–0046–E), to correct an 

unsafe condition for Eurocopter Model 

AS332 C1 and AS332 L1 helicopters. 

EASA advises that an AS332 helicopter 

was found on the production line with 

non-conforming rivets installed on the 

RH and LH longitudinal beams Y350 of 

the bottom structure of the fuselage, 

between sections X4780 and X5295. 

According to EASA, the investigation 

revealed that a limited number of 

helicopters were documented as 

receiving a production modification 

requiring the replacement of certain 3.2 

mm rivets with 4.8 mm rivets, but the 

actual replacement of the rivets had not 

been performed. EASA states that this 

condition leads to significant reduction 

in the safety margins during sling 

operations and may cause failure of the 

web/flange assembly connections of the 

longitudinal beams Y350, possibly 

resulting in loss of control of the 

helicopter. For these reasons, EASA 

issued EAD 2012–0046–E, which, 

pending inspection of the helicopter 

beams Y350 and replacement of the 

affected rivets, prohibits sling 

operations or limits the 3-ton sling to 

external loads of 2.28 tons or less. 

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 


tkelley on DSK3SPTVN1PROD with PROPOSALS