This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

51717 

Vol. 77, No. 166 

Monday, August 27, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0858; Directorate 

Identifier 2011–NM–183–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 an 

existing airworthiness directive (AD) 

that applies to certain Airbus Model 

A300 B4–2C, B4–103, and B4–203 

airplanes; and Model A300 B4–601, B4– 

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

622R airplanes. The existing AD 

currently requires performing a onetime detailed visual inspection of the 

forward fitting at frame (FR) 40 on both 

sides of the airplane for cracks, and 

repair if necessary. Since we issued that 

AD, we have received reports that new 

cracks were found in the FR 40 forward 

fitting. This proposed AD would require 

repetitive detailed inspections of the 

forward fitting at FR 40 without nut 

removal, and a one-time eddy current or 

liquid penetrant inspection of the 

forward fitting at FR 40 with nut 

removal, and repair if necessary. We are 

proposing this AD to detect and correct 

cracking of the FR 40 forward fitting, 

which could result in a deterioration of 

the structural integrity of the frame. 

DATES: We must receive comments on 

this proposed AD by October 11, 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, WA 

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–2012–0858; Directorate Identifier 

2011–NM–183–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 March 4, 2010, we issued AD 

2010–06–05, Amendment 39–16229 (75 

FR 11435, March 11, 2010). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2010–06–05, 

Amendment 39–16229 (75 FR 11435, 

March 11, 2010), we have received 

reports that additional cracks have been 

found after the modification had been 

completed. In addition, new inspections 

have been added to address the unsafe 

condition. The European Aviation 

Safety Agency (EASA), which is the 

Technical Agent for the Member States 

of the European Community, has issued 

EASA Airworthiness Directive 2011– 

0163, dated August 30, 2011 (referred to 

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

unsafe condition for the specified 

products. The MCAI states: 

One A300–600 aeroplane operator reported 

that, during a routine inspection, a crack was 

found in the right hand frame (FR) 40 

forward fitting between stringer 32 and 

stringer 33. The subject aeroplane had 

previously been modified in accordance with 

Airbus SB A300–57–6053 (Mod. 10453). 

Therefore and pending completion of the 

full analysis using a refined Finite Element 

Model, EASA issued AD 2009–0094 [which 

corresponds with FAA AD 2010–06–05, 

Amendment 39–16229 (75 FR 11435, March 

11, 2010)] to require a one-time Detailed 

Visual Inspection (DVI) of the post-SB A300– 

57–6053 A300–600 aeroplanes and post-SB 

A300–53–0297 A300 aeroplanes in order to 

ensure the structural integrity of frame 40. 

During a recent maintenance check, on two 

aeroplanes (one A300B4 and one A300–600), 

cracks were found in the FR 40 forward 

fitting. 

These new crack findings are considered as 

unexpected, since they were found after: 

—Application of modification SB A300–57– 

6053 or SB A300–53–0297 which cancels 

the inspection programme, and 

—Accomplishment of EASA AD 2009–0094. 

For the reasons described above, this new 

[EASA] AD, which supersedes EASA AD 

2009–0094, requires repetitive DVI of the FR 

40 forward fitting (without nut removal), 

accomplishment of a one time Eddy Current 


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(EC) inspection or liquid penetrant 

inspection of this area (with nut removal) 

and, depending on findings, the 

accomplishment of associated corrective 

action [repair if any cracking found]. Passing 

the EC or liquid penetrant inspection 

constitutes terminating action for the 

repetitive DVI. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Airbus has issued All Operator Telex 

A300–53A0391, dated August 9, 2011 

(for Model A300 B4–2C, B4–103, and 

B4–203 airplanes); and All Operator 

Telex A300–57A6111, dated August 9, 

2011 (for Model A300 B4–601, B4–603, 

B4–605R, B4–620, B4–622, and B4– 

622R airplanes). 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 134 products of U.S. 

registry. 

The actions that are required by AD 

2010–06–05, Amendment 39–16229 (75 

FR 11435, March 11, 2010), and retained 

in this proposed AD take about 3 workhours per product, at an average labor 

rate of $85 per work hour. Based on 

these figures, the estimated cost of the 

currently required actions is $255 per 

product. 

We estimate that it would take about 

3 work-hours per product to comply 

with the new 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 

$34,170, or $255 per product. 

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 

removing Airworthiness Directive (AD) 

2010–06–05, Amendment 39–16229 (75 

FR 11435, March 11, 2010), and adding 

the following new AD: 

Airbus: Docket No. FAA–2012–0858; 

Directorate Identifier 2011–NM–183–AD. 

(a) Comments Due Date 

We must receive comments by October 11, 

2012. 

(b) Affected ADs 

This AD supersedes AD 2010–06–05, 

Amendment 39–16229 (75 FR 11435, March 

11, 2010). 

(c) Applicability 

This AD applies to Airbus airplanes, 

certificated in any category, as identified in 

paragraphs (c)(1) and (c)(2) of this AD. For 

airplanes on which Airbus Service Bulletin 

A300–53–0297 or A300–57–6053 (Airbus 

Modification 10453), as applicable, have 

been incorporated as a corrective action 

(repair following crack finding), no action is 

required by this AD. 

(1) Model A300 B4–2C, B4–103, and B4– 

203 airplanes, all serial numbers, modified 

preventively in service (without any 

preliminary crack findings) as specified in 

Airbus Service Bulletin A300–53–0297 

(Airbus Modification 10453). 

(2) Model A300 B4–601, B4–603, B4–605R, 

B4–620, B4–622, and B4–622R airplanes, all 

serial numbers, modified preventively in 

service (without any preliminary crack 

findings) as specified in Airbus Service 

Bulletin A300–57–6053 (Airbus Modification 

10453). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, 57: Fuselage, Wings. 

(e) Reason 

This AD was prompted by reports that 

cracks were found in the frame (FR) 40 

forward fitting. We are issuing this AD to 

detect and correct cracking of the FR 40 

forward fitting, which could result in a 

deterioration of the structural integrity of the 

frame. 

(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) Retained Detailed Inspection 

This paragraph restates the actions 

required by paragraphs (f)(1), (f)(2), and (f)(3) 

of AD 2010–06–05, Amendment 39–16229 

(75 FR 11435, March 11, 2010). 

(1) At the applicable time specified in table 

1 to paragraph (g)(1) of this AD: Do a onetime detailed visual inspection of the forward 

fitting at FR 40 on both sides of the airplane, 

in accordance with Airbus Mandatory 

Service Bulletin A300–57A6108 (for Model 

A300 B4–601, B4–603, B4–605R, B4–620, 

B4–622, and B4–622R airplanes) or A300– 

53A0387 (for Model A300 B4–2C, B4–103, 

and B4–203 airplanes), both including 


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Appendices 01 and 02, both dated September 

12, 2008. 

TABLE 1 TO PARAGRAPH (g)(1) OF THIS AD—COMPLIANCE TIMES

Airplane models/configuration Compliance time 

A300 B4–2C and B4–103 airplanes on which Airbus 

Service Bulletin A300–53–0297 was done prior to 

the accumulation of 9,000 total flight cycles.

Prior to the accumulation of 18,000 total flight cycles, or within 3 months after April 15, 

2010 (the effective date of AD 2010–06–05, Amendment 39–16229 (75 FR 11435, 

March 11, 2010)), whichever occurs later. 

A300 B4–2C and B4–103 airplanes on which Airbus 

Service Bulletin A300–53–0297 was done on or 

after the accumulation of 9,000 total flight cycles.

Within 5,500 flight cycles after accomplishment of Airbus Service Bulletin A300–53–0297, 

or within 6 months after April 15, 2010 (the effective date of AD 2010–06–05, Amendment 39–16229 (75 FR 11435, March 11, 2010)), whichever occurs later; except, for 

airplanes that, as of April 15, 2010 (the effective date of AD 2010–06–05), have accumulated 11,000 flight cycles or more since accomplishment of Airbus Service Bulletin 

A300–53–0297, within 3 months after April 15, 2010 (the effective date of AD 2010– 

06–05). 

A300 B4–203 airplanes on which Airbus Service Bulletin A300–53–0297 was done prior to the accumulation of 8,300 total flight cycles.Prior to the accumulation of 15,000 total flight cycles, or within 3 months after April 15, 

2010 (the effective date of AD 2010–06–05, Amendment 39–16229 (75 FR 11435, 

March 11, 2010)), whichever occurs later. 

A300 B4–203 airplanes on which Airbus Service Bulletin A300–53–0297 was done on or after the accumulation of 8,300 total flight cycles.Within 4,100 flight cycles after accomplishment of Airbus Service Bulletin A300–53–0297, 

or within 6 months after April 15, 2010 (the effective date of AD 2010–06–05, Amendment 39–16229 (75 FR 11435, March 11, 2010)), whichever occurs later; except, for 

airplanes that, as of April 15, 2010 (the effective date of AD 2010–06–05), have accumulated 8,200 flight cycles or more since accomplishment of Airbus Service Bulletin 

A300–53–0297, within 3 months after April 15, 2010 (the effective date of AD 2010– 

06–05). 

A300 B4–601, B4–603, B4–605R, B4–620, B4–622, 

and B4–622R airplanes on which Airbus Service 

Bulletin A300–57–6053 was done prior to the accumulation of 6,100 total flight cycles.

Prior to the accumulation of 11,500 total flight cycles, or within 3 months after April 15, 

2010 (the effective date of AD 2010–06–05, Amendment 39–16229 (75 FR 11435, 

March 11, 2010)), whichever occurs later. 

A300 B4–601, B4–603, B4–605R, B4–620, B4–622, 

and B4–622R airplanes on which Airbus Service 

Bulletin A300–57–6053 was done on or after the 

accumulation of 6,100 total flight cycles.

Within 3,300 flight cycles after accomplishment of Airbus Service Bulletin A300–57–6053, 

or within 6 months after April 15, 2010 (the effective date of AD 2010–06–05, Amendment 39–16229 (75 FR 11435, March 11, 2010)), whichever occurs later; except, for 

airplanes that, as of April 15, 2010 (the effective date of AD 2010–06–05), have accumulated 6,600 flight cycles or more since accomplishment of Airbus Service Bulletin 

A300–57–6053, within 3 months after April 15, 2010 (the effective date of AD 2010– 

06–05). 

(2) Except as required by paragraph (g)(3) 

of this AD: If any crack is found during the 

inspection required by paragraph (g)(1) of 

this AD, before further flight, do a temporary 

or definitive repair, as applicable, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

53–0268, Revision 06, dated January 7, 2002 

(for Model A300 B4–2C, B4–103, and B4–203 

airplanes); or A300–57–6052, Revision 03, 

dated May 27, 2002, including Airbus 

Drawings 15R53810394, Issue A, dated 

December 21, 1998, and 21R57110247, Issue 

A, dated June 20, 1997 (for Model A300 B4– 

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

B4–622R airplanes). 

(3) If any crack found during the inspection 

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

cannot be repaired in accordance with Airbus 

Service Bulletin A300–53–0268, Revision 06, 

dated January 7, 2002 (for Model A300 B4– 

2C, B4–103, and B4–203 airplanes); or A300– 

57–6052, Revision 03, dated May 27, 2002 

including Airbus Drawings 15R53810394, 

Issue A, dated December 21, 1998, and 

21R57110247, Issue A, dated June 20, 1997 

(for Model A300 B4–601, B4–603, B4–605R, 

B4–620, B4–622, and B4–622R airplanes): 

Contact Airbus for repair instructions and, 

before further flight, repair the crack using 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) Retained Reporting Requirement 

This paragraph restates the requirements of 

paragraph (f)(4) of AD 2010–06–05, 

Amendment 39–16229 (75 FR 11435, March 

11, 2010). Submit an inspection report in 

accordance with Appendix 01 of Airbus 

Mandatory Service Bulletin A300–53A0387, 

including Appendices 01 and 02, dated 

September 12, 2008 (for Model A300 B4–2C, 

B4–103, and B4–203 airplanes); or Airbus 

Mandatory Service Bulletin A300–57A6108, 

including Appendices 01 and 02, dated 

September 12, 2008 (for Model A300 B4–601, 

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

622R airplanes); to the address identified on 

the reporting sheet, at the applicable time 

specified in paragraph (h)(1) or (h)(2) of this 

AD. 

(1) If the inspection was done on or after 

April 15, 2010 (the effective date of AD 

2010–06–05, Amendment 39–16229 (75 FR 

11435, March 11, 2010)): Submit the report 

within 30 days after the inspection. 

(2) If the inspection was done before April 

15, 2010 (the effective date of AD 2010–06– 

05, Amendment 39–16229 (75 FR 11435, 

March 11, 2010)): Submit the report within 

30 days after April 15, 2010 (the effective 

date of AD 2010–06–05). 

(i) New Requirement: Repetitive Detailed 

Visual Inspections 

Within 300 flight cycles after the effective 

date of this AD: Perform a detailed inspection 

for cracks of the forward fitting at FR 40 

without nut removal on both sides of the 

airplane, in accordance with Airbus All 

Operator Telex A300–53A0391, dated August 

9, 2011 (for Model A300 B4–2C, B4–103, and 

B4–203 airplanes); or Airbus All Operator 

Telex A300–57A6111, dated August 9, 2011 

(for Model A300 B4–601, B4–603, B4–605R, 

B4–620, B4–622, and B4–622R airplanes). 

Thereafter, repeat the inspection at intervals 

not to exceed 300 flight cycles. 

(j) New Requirement: Eddy Current 

Inspection or Liquid Penetrant Inspection 

Within 36 months after the effective date 

of this AD: Perform an eddy current 

inspection or a liquid penetrant inspection 

for cracks of the forward fitting at FR 40 with 

nut removal on both sides of the airplane, in 

accordance with Airbus All Operator Telex 

A300–53A0391, dated August 9, 2011 (for 

Model A300 B4–2C, B4–103, and B4–203 

airplanes); or Airbus All Operator Telex 

A300–57A6111, dated August 9, 2011 (for 

Model A300 B4–601, B4–603, B4–605R, B4– 

620, B4–622, and B4–622R airplanes). 

(k) New Requirement: Corrective Action 

If, during any inspection required by 

paragraph (i) or (j) of this AD, any crack is 

detected: Before further flight, repair the 

crack in accordance with a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA (or its delegated agent). 


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(l) New Requirement: Reporting 

Requirement 

Submit a one-time report of the findings 

(both positive and negative) of the 

inspections required by paragraphs (i) and (j) 

of this AD to Airbus, Sebastien Faure, SEES1, 

SAS—EAW (Airworthiness Office), 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 31 68; 

fax +33 5 61 93 36 14; email 

sebastien.s.faure@airbus.com, at the 

applicable time specified in paragraph (l)(1) 

or (l)(2) of this AD. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(m) New Requirement: Terminating Action 

Accomplishment of the one-time eddy 

current inspection or a liquid penetrant 

inspection required by paragraph (j) of this 

AD, including doing all applicable repairs, 

constitutes terminating action for the 

inspections required by paragraph (i) of this 

AD. 

(n) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, 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: 

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; 

email: Dan.Rodina@faa.gov. Information may 

be emailed to: 9-ANM-116-AMOCREQUESTS@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 

2010–06–05, Amendment 39–16229 (75 FR 

11435, March 11, 2010), 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. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(o) Related Information 

(1) Refer to MCAI EASA Airworthiness 

Directive 2011–0163, dated August 30, 2011, 

and the service information in paragraphs 

(o)(1)(i) through (o)(1)(vi) of this AD, for 

related information. 

(i) Airbus All Operator Telex A300– 

53A0391, dated August 9, 2011. 

(ii) Airbus All Operator Telex A300– 

57A6111, dated August 9, 2011. 

(iii) Airbus Mandatory Service Bulletin 

A300–57A6108, including Appendices 01 

and 02, dated September 12, 2008. 

(iv) Airbus Mandatory Service Bulletin 

A300–53A0387, including Appendices 01 

and 02, dated September 12, 2008. 

(v) Airbus Service Bulletin A300–53–0268, 

Revision 06, dated January 7, 2002. 

(vi) Airbus Service Bulletin A300–57– 

6052, Revision 03, dated May 27, 2002, 

including Airbus Drawings 15R53810394, 

Issue A, dated December 21, 1998, and 

21R57110247, Issue A, dated June 20, 1997. 

(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 August 

17, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–20966 Filed 8–24–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0860; Directorate 

Identifier 2012–NM–123–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 737–600, 

–700, –800, and –900ER series 

airplanes. This proposed AD was 

prompted by incorrect wire support 

clamps installed within the left 

environmental cooling systems (ECS) 

bay, which could allow wiring to come 

in contact with the exposed metal of the 

improper clamp. This proposed AD 

would require inspections to identify 

the part number of the wire support 

clamp, related investigative actions, and 

corrective actions if necessary. We are 

proposing this AD to prevent electrical 

arcing and a potential ignition source, 

which in combination with flammable 

fuel vapors could result in a fuel tank 

explosion, and consequent loss of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by October 11, 2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 


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