63264 Federal Register / Vol. 77, No. 200 / Tuesday, October 16, 2012 / Proposed Rules 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Eurocopter France: Docket No. FAA–2012– 

1087; Directorate Identifier 2009–SW– 

32–AD. 

(a) Applicability 

This AD applies to all Model AS332C, L, 

and L1 helicopters without modification 

(MOD) 0722907, except helicopters with 

serial numbers 2078 and 2102, certificated in 

any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in the outer skin, butt strap, or fuselage 

frame, which could result in loss of airframe 

structural integrity, and subsequent loss of 

control of the helicopter. 

(c) 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. 

(d) Required Actions 

(1) Within 10 hours time-in-service (TIS) 

for helicopters that have 8,800 or more hours 

TIS or before or upon reaching 8,810 hours 

TIS for helicopters that have less than 8,800 

hours TIS, and thereafter at intervals not to 

exceed 10 hours TIS, visually inspect for a 

crack on the outer skin and the butt strap in 

the sliding cowling right-hand and left-hand 

rail attachment areas on Frame 5295 as 

shown in Figure 2 of Eurocopter Alert 

Service Bulletin No. 05.00.76, Revision 0, 

dated February 20, 2008 (ASB). 

(i) If there is a crack in the outer skin or 

in the butt strap per paragraph (d)(1) of this 

AD, before further flight, inspect for a crack 

in Frame 5295 in the areas shown in Figure 

3, Area 1, and Figure 4, of the ASB. 

(ii) If there is a crack in the outer skin, the 

butt strap, or in Frame 5295 in the areas 

inspected as required by this AD, before 

further flight, repair the part in accordance 

with a method approved by the FAA. 

(2) Within 300 hours TIS, for each 

helicopter that has 8,800 or more hours TIS, 

modify the sliding cowling rails and shims in 

the attachment areas on Frame 5295 

(corresponds to MOD 0726478R2), as 

depicted in Figure 5 and by following the 

Accomplishment Instructions, paragraph 

2.B.3., of the ASB. 

(e) Special Flight Permit 

A special flight permit is permitted for a 

helicopter with a crack in the outer skin or 

butt strap to operate the helicopter to a 

location where the requirements of this AD 

can be accomplished. A special flight permit 

is not permitted for a helicopter with a crack 

in Frame 5295. 

(f) Alternative Methods of Compliance 

(AMOC) 

(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 (France) 

AD No. 2008–0035–E, dated February 21, 

2008. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5311, Fuselage, Main Frame. 

Issued in Fort Worth, Texas, on October 2, 

2012. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–25429 Filed 10–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1074; Directorate 

Identifier 2012–NM–027–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Airbus Model A330–200 Freighter series 

airplanes; Model A330–200 and –300 

series airplanes; and Model A340–200 

and –300 series airplanes. This 

proposed AD was prompted by a report 

of a manufacturing defect in certain rods 

installed in the belly fairing, which 

could lead to cracks at the crimped end 

of the rod. This proposed AD would 

require an inspection of the rods to 

determine the manufacturer; and for 

affected parts, an inspection for any 

cracking of the rods, and related 

investigative and corrective actions if 

necessary. We are proposing this AD to 

detect and correct cracking of the rods, 

which could result in rupture of rods 

that attach the belly fairing to the 

airframe, leading to separation of the 

belly fairing from the airframe, and 

consequent damage to airplane structure 

and airplane systems. 

DATES: We must receive comments on 

this proposed AD by November 30, 

2012. 

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 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: 

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. 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
Federal Register / Vol. 77, No. 200 / Tuesday, October 16, 2012 / Proposed Rules 63265 

FAA–2012–1074; Directorate Identifier 

2012–NM–027–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0005, 

dated January 10, 2012 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

A rod manufacturing process defect has 

been identified at the supplier, Technical 

Airborne Components Industries (TAC), 

which could lead to cracks at the crimped 

end of the rod. 

A design review of all affected rods has 

demonstrated that rupture of rods which 

attach the belly fairing can lead to separation 

of the belly fairing from the airframe, which 

would constitute an unsafe condition. 

For the reasons described above, this AD 

requires detailed visual inspections of the 21 

affected rods installed in the belly fairing for 

manufacturer identification, and if TAC is 

identified as manufacturer, or if the 

manufacturer cannot be identified, to further 

inspect the rods to find any crack, using a 

high frequency eddy current (HFEC) method 

and, depending on findings, accomplishment 

of the applicable [related investigative and] 

corrective actions, to ensure structural 

integrity of the belly fairing rods. This AD 

also prohibits installation of an affected TAC 

rod as replacement part in the belly fairing 

to all aeroplanes. 

A design review of all affected rods has 

demonstrated that rupture of rods which 

attach the belly fairing can lead to 

separation of the belly fairing from the 

airframe, which can cause damage to 

airplane structure and airplane systems. 

The related investigative actions include 

an inspection to determine the 

manufacturer and an HFEC inspection 

of any affected replacement rod for any 

cracking. The corrective actions include 

replacing the cracked rod with a new 

rod. You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletins A330–53–3186 and A340–53– 

4185, both including Appendix 01, both 

Revision 01, both dated April 7, 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. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 54 products of U.S. registry. 

We also estimate that it would take 

about 13 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$59,670, or $1,105 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

28 work-hours and require parts costing 

$0, for a cost of $2,380 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. 

We have no way of determining the 

number of products that may need these 

actions. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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. 

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 adding 

the following new AD: 

Airbus: Docket No. FAA–2012–1074; 

Directorate Identifier 2012–NM–027–AD. 

(a) Comments Due Date 

We must receive comments by November 

30, 2012. 

(b) Affected ADs 

None. 


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63266 Federal Register / Vol. 77, No. 200 / Tuesday, October 16, 2012 / Proposed Rules 

(c) Applicability 

This AD applies to all airplanes identified 

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

certificated in any category. 

(1) Airbus A330–201, –202, –203, –223, 

–223F, –243, –243F, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes. 

(2) Airbus A340–211, –212, –213, –311, 

–312, and –313 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53; Fuselage. 

(e) Reason 

This AD was prompted by a report of a 

manufacturing defect in certain rods installed 

in the belly fairing, which could lead to 

cracks at the crimped end of the rod. We are 

issuing this AD to detect and correct cracking 

of the rods, which could result in rupture of 

rods that attach the belly fairing to the 

airframe, leading to separation of the belly 

fairing from the airframe, and consequent 

damage to airplane structure and airplane 

systems. 

(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) Actions 

For Model A330–201, –202, –203, –223, 

–223F, –243, –243F, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes, 

having manufacturer serial number (MSN) 

0002 to 1113 inclusive, except MSN 0996, 

1039, 1054, 1059, 1105, 1107, 1108 and 1112; 

and Model A340–211, –212, –213, –311, 

–312, and –313 airplanes: Within 72 months 

after the effective date of this AD, accomplish 

the actions in paragraphs (g)(1) and (g)(2) of 

this AD, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–53–3186, 

excluding Appendix 01, Revision 01, dated 

April 7, 2011 (for Model A330 airplanes); or 

A340–53–4185, excluding Appendix 01, 

Revision 01, dated April 7, 2011 (for Model 

A340 airplanes). 

(1) Do a detailed inspection of the 21 rods 

of the belly fairing identified in Airbus 

Mandatory Service Bulletin A330–53–3186, 

excluding Appendix 01, Revision 01, dated 

April 7, 2011 (for Model A330 airplanes); or 

A340–53–4185, excluding Appendix 01, 

Revision 01, dated April 7, 2011 (for Model 

A340 airplanes); for rod manufacturer 

identification. A review of airplane 

maintenance records is acceptable in lieu of 

this inspection if the manufacturer of the 

rods can be conclusively determined from 

that review. 

(2) If the rod manufacturer is found to be 

Technical Airborne Components Industries 

(TAC), or if the manufacturer cannot be 

identified, do a high frequency eddy current 

(HFEC) inspection for cracking of the 

crimped end of the rod body and, if any crack 

is found, before further flight, do all 

applicable related investigative and 

corrective actions. 

(h) Parts Installation Limitations 

As of the effective date of this AD, no 

person may install any affected TAC rod, as 

identified in Airbus Mandatory Service 

Bulletin A330–53–3186, Revision 01, dated 

April 7, 2011; or A340–53–4185, Revision 01, 

dated April 7, 2011; as applicable; on any 

airplane unless the rod has passed (found to 

have no cracking) the inspection as required 

by paragraph (g)(2) of this AD. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

inspections and corrective actions required 

by paragraph (g) of this AD, if those actions 

were performed before the effective date of 

this AD using Airbus Mandatory Service 

Bulletin A330–53–3186, dated January 17, 

2011; or A340–53–4185, dated January 17, 

2011; which are not incorporated by 

reference. 

(j) 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; 

phone: (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 

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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2012–0005, dated 

January 10, 2012, and the Airbus service 

information identified in paragraphs (k)(1)(i) 

and (k)(1)(ii) of this AD, for related 

information. 

(i) Airbus Mandatory Service Bulletin 

A330–53–3186, excluding Appendix 01, 

Revision 01, dated April 7, 2011. 

(ii) Airbus Mandatory Service Bulletin 

A340–53–4185, excluding Appendix 01, 

Revision 01, dated April 7, 2011. 

(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 

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 October 

4, 2012. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–25427 Filed 10–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1073; Directorate 

Identifier 2012–NM–078–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 767–300 

series airplanes. This proposed AD was 

prompted by a report that, for certain 

airplanes, reinforcement straps were not 

bonded to the center overhead stowage 

bins in the passenger compartment. For 

certain airplanes, this proposed AD 

would require performing an inspection 

of reinforcement straps to ensure they 

are correctly bonded to the center 

overhead stowage bins, and bonding the 

reinforcement straps to the center 

overhead stowage bins if necessary. For 

certain airplanes, this proposed AD 

would require installing reinforcement 

straps on the center overhead stowage 

bins. We are proposing this AD to 

prevent missing or incorrectly bonded 

reinforcement straps, which could result 

in the center overhead stowage bins 

breaking loose and causing injury to 

passengers and damage to equipment 

during in-flight turbulence. 

DATES: We must receive comments on 

this proposed AD by November 30, 

2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 


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