30228 Federal Register / Vol. 77, No. 99 / Tuesday, May 22, 2012 / Proposed Rules 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0488; Directorate 

Identifier 2011–NM–106–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 certain 

Airbus Model A300 B4–600 and A300 

B4–600R, Model A300, and Model A310 

series airplanes. This proposed AD was 

prompted by reports of fatigue cracking 

in the crossbeams at the junction of the 

actuator beam of the lower deck cargo 

door. This proposed AD would require 

repetitive inspections of the crossbeams 

of certain fuselage frames, and repair if 

necessary. We are proposing this AD to 

detect and correct cracking of the 

crossbeams at the junction of the 

actuator beam of the lower deck cargo 

door, which could result in failure to 

withstand ultimate load conditions, and 

consequent reduced structural integrity 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by July 6, 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— 

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, Washington. 

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, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–0488; Directorate Identifier 

2011–NM–106–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 aviation authority 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2011–0086, 

dated May 12, 2011 (referred to after 

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

condition for the specified products. 

The MCAI states: 

Some operators have reported cracked 

crossbeams at the junction with the lower 

deck cargo door actuator beam. The 

investigation results indicate that these 

cracks initiated in the fastener hole, 

propagated in a vertical direction and were 

due to fatigue. 

This condition, if not corrected, could lead, 

in case of cracks propagation in a crossbeam 

(upper and lower web), to the floor grid being 

unable to withstand ultimate load condition. 

For the reasons described above, this 

[EASA] AD requires repetitive [high 

frequency eddy current] inspections [for 

cracks] of certain crossbeams including those 

previously repaired by the Structure Repair 

Manual (SRM) or Repair Approval Sheet 

(RAS). 

The required actions include 

repairing any cracking. As an option, 

modifying the crossbeams terminates 

the repetitive inspections. You may 

obtain further information by examining 

the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued the following 

Service Bulletins: 

• A300–53–0389, Revision 02, dated 

April 27, 2011; 

• A310–53–2133, Revision 02, dated 

April 27, 2011; and 

• A300–53–6166, Revision 01, dated 

May 21, 2010. 

Airbus has also issued the following 

Mandatory Service Bulletins: 

• A300–53–0390, dated January 15, 

2010; 

• A310–53–2134, dated January 15, 

2010; and 

• A300–53–6168, dated January 15, 

2010. 

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 Proposed AD 

and the MCAI or Service Information 

Where the service information 

identified in the ‘‘Relevant Service 

Information’’ section specifies to contact 

the manufacturer for instructions on 

certain cracking conditions, this 

proposed AD would require repairing 

those conditions using a method 

approved by the FAA or EASA (or its 

delegated agent). In light of the type of 

repair that would be required to address 

the unsafe condition, and consistent 


srobinson on DSK4SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 99 / Tuesday, May 22, 2012 / Proposed Rules 30229 

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. 

Although the MCAI allows further 

flight after cracks are found during 

compliance with the required action, 

this proposed AD would require repair 

of any cracked/damaged frames before 

further flight. This difference has been 

coordinated with the EASA. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 152 products of U.S. 

registry. We also estimate that it would 

take about 1 work-hour 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 

$12,920, or $85 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); 

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: 

The Boeing Company: Docket No. FAA– 

2012–0488; Directorate Identifier 2011– 

NM–106–AD. 

(a) Comments Due Date 

We must receive comments by July 6, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A300 B2– 

1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, 

and B4–203; Model A300 B4–601, B4–603, 

B4–620, and B4–622 airplanes; Model A300 

B4–605R and B4–622R airplanes; and Model 

A310–203, –204, –221, –222, –304, –322, 

–324, and –325 airplanes; certificated in any 

category; except those identified in paragraph 

(c)(1), (c)(2), or (c)(3) of this AD, as 

applicable. 

(1) Airplanes on which Airbus Service 

Bulletin A300–53–6166 (Airbus Modification 

13434) has been embodied in service (for 

Model A300 B4–600 and A300 B4–600R 

series airplanes). 

(2) Airplanes on which Airbus Service 

Bulletin A300–53–0389 (Airbus Modification 

13434) has been embodied in service (for 

Model A300 series airplanes). 

(3) Airplanes on which Airbus Service 

Bulletin A310–53–2133 (Airbus Modification 

13434) has been embodied in service (for 

Model A310 series airplanes). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53: Fuselage. 

(e) Reason 

This AD was prompted by reports of 

fatigue cracking in the crossbeams at the 

junction of the actuator beam of the lower 

deck cargo door. We are issuing this AD to 

detect and correct cracking of the crossbeams 

at the junction of actuator beam of the lower 

deck cargo door, which could result in failure 

to withstand ultimate load conditions, and 

consequent reduced structural integrity of the 

airplane. 

(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 High Frequency Eddy Current 

Inspections 

(1) For airplanes on which the crossbeams 

at frames (FR) 22/23 and FR 61/62 have not 

been repaired as specified in an Airbus 

structural repair manual or repair approval 

sheet as of the effective date of this AD: 

Before the accumulation of 10,000 total flight 

cycles since first flight of the airplane, or 

within 600 flight cycles after the effective 

date of this AD, whichever occurs later; 

perform a high frequency eddy current 

(HFEC) inspection for cracking of the 

crossbeam fuselage frame stations FR 22/23 

and FR 61/62, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of 

this AD. Repeat the inspection thereafter at 

intervals not to exceed 600 flight cycles until 

the modification specified in paragraph (i) of 

this AD has been done. 

(i) Airbus Mandatory Service Bulletin 

A300–53–0390, dated January 15, 2010 (for 

Model A300 series airplanes). 

(ii) Airbus Mandatory Service Bulletin 

A310–53–2134, dated January 15, 2010 (for 

Model A310 series airplanes). 

(iii) Airbus Mandatory Service Bulletin 

A300–53–6168, dated January 15, 2010 (for 

Model A300–600 series airplanes). 

(2) For airplanes on which the crossbeams 

at FR 22/23 and FR 61/62 have been repaired 

as specified in an Airbus structural repair 

manual or repair approval sheet as of the 

effective date of this AD: Before the 

accumulation of 10,000 total flight cycles 

since first flight of the airplane, or within 600 

flight cycles after the effective date of this 

AD, whichever occurs later; repair in 

accordance with a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent). 

(h) Corrective Action 

If any crack is found during any inspection 

required by paragraph (g) of this AD: Before 

further flight repair any crack using a method 

approved by the Manager, International 

Branch, ANM–116; or EASA (or its delegated 

agent). 


srobinson on DSK4SPTVN1PROD with PROPOSALS
30230 Federal Register / Vol. 77, No. 99 / Tuesday, May 22, 2012 / Proposed Rules 

(i) Optional Terminating Action 

Modifying the crossbeam fuselage frame 

stations FR 22/23 and FR 61/62, including 

doing rotating probe inspections for cracks of 

fastener holes in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraph (i)(1), (i)(2), or (i)(3) of this AD, 

and repairing any crack using a method 

approved by the Manager, International 

Branch, ANM–116; or EASA (or its delegated 

agent), terminates the repetitive inspections 

required by paragraph (g)(1) of this AD. 

(1) Airbus Service Bulletin A300–53–0389, 

Revision 02, dated April 27, 2011 (for Model 

A300 series airplanes). 

(2) Airbus Service Bulletin A310–53–2133, 

Revision 02, dated April 27, 2011 (for Model 

A310 series airplanes). 

(3) Airbus Service Bulletin A300–53–6166, 

Revision 01, dated May 21, 2010 (for Model 

A300–600 series airplanes). 

(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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (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. 

(k) Related Information 

Refer to EASA Airworthiness Directive 

2011–0086, dated May 12, 2011; and the 

applicable service bulletin identified in 

paragraphs (k)(1), (k)(2), (k)(3), (k)(4), (k)(5), 

and (k)(6) of this AD for related information. 

(1) Airbus Service Bulletin A300–53–0389, 

Revision 02, dated April 27, 2011. 

(2) Airbus Service Bulletin A310–53–2133, 

Revision 02, dated April 27, 2011. 

(3) Airbus Service Bulletin A300–53–6166, 

Revision 01, dated May 21, 2010. (4) Airbus 

Mandatory Service Bulletin A300–53–0390, 

dated January 15, 2010. 

(5) Airbus Mandatory Service Bulletin 

A310–53–2134, dated January 15, 2010. 

(6) Airbus Mandatory Service Bulletin 

A300–53–6168, dated January 15, 2010. 

Issued in Renton, Washington, on May 10, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–12339 Filed 5–21–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0528; Directorate 

Identifier 2011–SW–068–AD] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Eurocopter Deutschland GmbH Model 

MBB–BK117 C–2 helicopters with 

certain Generator Control Units (GCU) 

installed. This proposed AD is 

prompted by reports of internal short 

circuits in certain GCUs. The proposed 

actions are intended to replace any 

affected GCUs to prevent a short circuit, 

which could result in a loss of electrical 

generating power, loss of systems 

required for continued safe flight and 

landing, and subsequent loss of control 

of the helicopter. 

DATES: We must receive comments on 

this proposed AD by July 23, 2012. 

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 a copy of 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: 

George Schwab, Aviation Safety 

Engineer, FAA, Rotorcraft Directorate, 

Safety Management Group, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5114; email 

george.schwab@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 AD No.: 2011– 

0149R1, dated September 30, 2011 (AD 


srobinson on DSK4SPTVN1PROD with PROPOSALS