Federal Register / Vol. 77, No. 216 / Wednesday, November 7, 2012 / Proposed Rules 66757 

iii. Information obtained through 

third parties (subject to any applicable 

information-sharing rules). 

iv. Information obtained through any 

empirically derived, demonstrably and 

statistically sound model that 

reasonably estimates a consumer’s 

income and/or assets. 

3. Examples of considering income for 

young consumers. Assume that an 

applicant is not employed but shares a 

household with another individual (the 

‘‘household member’’) who is 

employed. The applicant is under the 

age of 21 so § 1026.51(b) does apply. 

i. If the household member’s salary is 

deposited into a joint account shared 

with the applicant, a card issuer may 

consider that salary to be the applicant’s 

income for purposes of 

§ 1026.51(b)(1)(i). 

ii. The household member’s salary is 

deposited into an account to which the 

applicant does not have access. 

However, the household member 

regularly transfers a portion of that 

salary into an account to which the 

applicant does have access, which the 

applicant uses for the payment of 

household or other expenses. Whether a 

card issuer may consider the portion of 

the salary that is deposited into the 

account to be the applicant’s income for 

purposes of § 1026.51(b)(1)(i) depends 

on whether a Federal or state Statute or 

regulation grants the applicant an 

ownership interest in the account to 

which the applicant has access. 

iii. No portion of the household 

member’s salary is deposited into an 

account to which the applicant has 

access. However, the household member 

regularly uses that salary to pay for the 

applicant’s expenses. A cards issuer 

may not consider the household 

member’s salary as the applicant’s 

income for purposes of § 1026.51(b)(1)(i) 

because the salary is not current or 

reasonably expected income of the 

applicant. 

iv. No portion of the household 

member’s salary is deposited into an 

account to which the applicant has 

access, the household member does not 

regularly use that salary to pay for the 

applicant’s expenses, and no Federal or 

State statute or regulation grants the 

applicant an ownership interest in that 

salary. The card issuer may not consider 

the household member’s salary to be the 

applicant’s income for purposes of 

§ 1026.51(b)(1)(i). 

Paragraph 51(b)(1)(ii) 

1. Financial information. Information 

regarding income and assets that 

satisfies the requirements of § 1026.51(a) 

also satisfies the requirements of 

§ 1026.51(b)(1)(ii)(B) and card issuers 

may rely on the guidance in comments 

51(a)(1)–4, –5, and –6 for purposes of 

determining whether a cosigner, 

guarantor, or joint applicant who is at 

least 21 years old has the ability to make 

the required minimum periodic 

payments in accordance with 

§ 1026.51(b)(1)(ii)(B). [See comment 

51(a)(1)–4.] fi. 

* * * * * 

Dated: October 17, 2012. 

Richard Cordray, 

Director, Bureau of Consumer Financial 

Protection. 

[FR Doc. 2012–26008 Filed 11–6–12; 8:45 am] 

BILLING CODE 4810–AM–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1161; Directorate 

Identifier 2011–NM–277–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 supersede an 

existing airworthiness directive (AD) 

that applies to certain The Boeing 

Company Model 737–200, –200C, –300, 

–400 and –500 series airplanes. The 

existing AD currently requires a onetime mid-frequency eddy current 

(MFEC) inspection, a low frequency 

eddy current (LFEC) inspection, and a 

detailed inspection for damage or 

cracking of stringer S–4L and S–4R lap 

joints and stringer clips between body 

station (BS) 540 and BS 727, and followon inspections and repair if necessary. 

Since we issued that AD, we have 

received reports of cracking of the lap 

joint lower row. This proposed AD 

would instead require repetitive 

external eddy current inspections for 

cracking of certain fuselage crown lap 

joints and corrective actions; internal 

eddy current and detailed inspections 

for cracking of certain fuselage crown 

lap joints, and repair if necessary; and 

detailed inspections of certain stringer 

clips, and replacement with new 

stringer clips if necessary. This 

proposed AD would also add airplanes 

to the applicability. We are proposing 

this AD to detect and correct cracking of 

the fuselage lap joints, which could 

result in sudden decompression of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by December 24, 

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 AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 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 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 Management Facility 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 Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6447; fax: 

425–917–6590; email: 

wayne.lockett@faa.gov. 

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–2012–1161; Directorate Identifier 

2011–NM–277–AD’’ at the beginning of 


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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 because of 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 April 18, 2003, we issued AD 

2003–08–15, Amendment 39–13128 (68 

FR 20341, April 25, 2003), for certain 

The Boeing Company Model 737–200, 

–200C, –300, –400 and –500 series 

airplanes. That AD requires a one-time 

MFEC, LFEC, and detailed inspection 

for damage or cracking of stringer S–4L 

and S–4R lap joints and stringer clips 

between BS 540 and BS 727, and followon inspections and repair if necessary. 

That AD resulted from a report 

indicating that, during a walk-around 

inspection on a Model 737–200 series 

airplane with 60,333 total flight cycles, 

a 23-inch-long crack was found in the 

lower row of the stringer S–4L lap joint 

between BS 616 and BS 639. Cracking 

was also found between the tear straps 

and in the skin locations common to the 

tear straps. Additionally, we received a 

report of significant cracking on stringer 

S–4R of the lap joint between BS 600 

and BS 727 on a Model 737–300 series 

airplane having 52,400 total flight 

cycles. We issued that AD to detect and 

correct cracking of the fuselage lap 

joints, which could result in sudden 

decompression of the airplane. 

Actions Since Existing AD 2003–08–15, 

Amendment 39–13128 (68 FR 20341, 

April 25, 2003) Was Issued 

Since we issued AD 2003–08–15, 

Amendment 39–13128 (68 FR 20341, 

April 25, 2003), we have received 

reports of lap joint lower row cracking 

on airplanes that were not subject to 

inspections in AD 2002–07–08, 

Amendment 39–12702 (67 FR 17917, 

April 12, 2002). We are proposing to 

supersede AD 2003–08–15 to provide 

inspections for these airplanes. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 737–53A1255, Revision 2, 

dated August 7, 2012. For information 

on the procedures and compliance 

times, see this service information at 

http://www.regulations.gov by searching 

for Docket No. FAA–2012–* * *. 

Other Relevant Rulemaking 

These crown lap joint inspections are 

currently also contained in the 

following service bulletins, which are 

mandated by AD 2002–07–08, 

Amendment 39–12702 (67 FR 17917, 

April 12, 2002): 

• Boeing Service Bulletin 737– 

53A1177, Revision 4, dated September 

2, 1999; 

• Boeing Service Bulletin 737– 

53A1177, Revision 5, dated February 15, 

2001; and 

• Boeing Service Bulletin 737– 

53A1177, Revision 6, dated May 31, 

2001. 

Boeing chose to add the needed 

inspections for the airplanes not 

covered by AD 2002–07–08 to the 

service information included in AD 

2003–08–15, Amendment 39–13128 (68 

FR 20341, April 25, 2003), due to the 

large scope of changes that would be 

needed to revise Boeing Service Bulletin 

737–53A1177, Revision 6, dated May 

31, 2001. We are considering further 

rulemaking to remove reference to those 

crown lap joint inspections from that 

AD. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would retain none 

of the requirements of AD 2003–08–15, 

Amendment 39–13128 (68 FR 20341, 

April 25, 2003). This proposed AD 

would include new inspection 

requirements, reduce certain inspection 

thresholds, and add repetitive 

inspections. This proposed AD would 

also add airplanes to the applicability 

statement of the existing AD. This 

proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. 

The phrase ‘‘related investigative 

actions’’ might be used in this proposed 

AD. ‘‘Related investigative actions’’ are 

follow-on actions that (1) are related to 

the primary actions, and (2) are actions 

that further investigate the nature of any 

condition found. Related investigative 

actions in an AD could include, for 

example, inspections. 

In addition, the phrase ‘‘corrective 

actions’’ might be used in this proposed 

AD. ‘‘Corrective actions’’ are actions 

that correct or address any condition 

found. Corrective actions in an AD 

could include, for example, repairs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 307 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Number of 

airplanes 

Cost on U.S. 

operators 

Internal inspection ............................. Up to 303 work-hours × $85 per 

hour = $25,755.

$0 $25,755 307 $7,906,785 

External inspection ............................ Up to 10 work-hours × $85 per hour 

= $850.

0 850 307 260,950 

We have received no definitive data 

that would enable us to provide a cost 

estimate 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 


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because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have 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 that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2003–08–15, Amendment 39–13128 (68 

FR 20341, April 25, 2003), and adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2012–1161; Directorate Identifier 2011– 

NM–277–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by December 24, 2012. 

(b) Affected ADs 

This AD supersedes AD 2003–08–15, 

Amendment 39–13128 (68 FR 20341, April 

25, 2003). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 737–200, –200C, –300, –400, and –500 

series airplanes; certificated in any category; 

as specified in Boeing Alert Service Bulletin 

737–53A1255, Revision 2, dated August 7, 

2012. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracking of the lap joint lower row. We are 

issuing this AD to detect and correct cracking 

of the fuselage lap joints, which could result 

in sudden decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) External Crown Lap Joint Inspection and 

Repair 

For airplanes on which the lap splice 

modification specified in AD 2002–07–08, 

Amendment 39–12702 (67 FR 17917, April 

12, 2002), has not been accomplished, except 

as required by paragraph (l)(1) and (l)(2) of 

this AD: At the applicable times specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 737–53A1255, 

Revision 2, dated August 7, 2012, do an 

external eddy current inspection for cracking 

in the crown lap joints, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 737–53A1255, 

Revision 2, dated August 7, 2012. At the 

intervals specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1255, Revision 2, dated 

August 7, 2012, repeat the inspections, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1255, Revision 2, dated August 7, 

2012. If any cracking is found in a lap joint, 

before further flight, repair, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1255, 

Revision 2, dated August 7, 2012. 

(h) Optional Internal Inspections for MidBay Fastener Locations 

As an option to confirm cracks found 

during the inspections required by paragraph 

(g) of this AD, do an internal mid-frequency 

eddy current (MFEC) inspection for cracking 

in the lap joint fastener row between tear 

straps of the crown lap and do a detailed 

inspection of the lap joint lower fastener row 

for cracking, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1255, Revision 2, 

dated August 7, 2012. 

(i) Internal Crown Lap Joint Inspection and 

Repair 

For airplanes on which the lap splice 

modification specified in AD 2002–07–08, 

Amendment 39–12702 (67 FR 17917, April 

12, 2002) has not been accomplished: At the 

times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1255, Revision 2, dated 

August 7, 2012, except as required by 

paragraphs (l)(1) and (l)(2) of this AD, do an 

internal MFEC, low frequency eddy current 

(LFEC), and detailed inspection for cracking 

in the crown lap joints and stringer clips, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1255, Revision 2, dated August 7, 

2012. 

(1) If any cracking is found in any lap joint, 

before further flight, repair, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1255, 

Revision 2, dated August 7, 2012. 

(2) If any cracking is found in any stringer 

clip, before further flight, replace the stringer 

clip with a new stringer clip, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1255, 

Revision 2, dated August 7, 2012. 

(3) Repeat the inspections at the intervals 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1255, 

Revision 2, dated August 7, 2012. 

(j) Optional Inspections for Tear Strap 

Locations Only 

As an option to confirm cracks found while 

doing the inspections required by paragraph 

(i) of this AD, do an open-hole inspection for 

cracking at the tear strap locations, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1255, Revision 2, dated August 7, 

2012. 

(k) Terminating Action 

(1) Accomplishing a repair of a crown lap 

joint in accordance with Boeing Alert Service 

Bulletin 737–53A1255, Revision 2, dated 

August 7, 2012, terminates the inspections 

required by paragraphs (g) and (i) of this AD 

for the repaired area only. 

(2) Accomplishing the modification of the 

crown lap joints in accordance with any of 

the service bulletins specified in paragraphs 

(k)(2)(i), (k)(2)(ii), and (k)(2)(iii) of this AD 

terminates the inspections required by 

paragraphs (g) and (i) of this AD for the 

modified area only. 

(i) Boeing Service Bulletin 737–53A1177, 

Revision 4, dated September 2, 1999. 

(ii) Boeing Service Bulletin 737–53A1177, 

Revision 5, dated February 15, 2001. 

(iii) Boeing Service Bulletin 737–53A1177, 

Revision 6, dated May 31, 2001. 

(l) Exceptions 

(1) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1255, 

Revision 2, dated August 7, 2012, states a 

compliance time ‘‘from the Revision 1 date 

of this service bulletin,’’ this AD requires a 

compliance time ‘‘after the effective date of 

this AD.’’ 

(2) Where the ‘‘condition’’ column, in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 737–53A1255, 

Revision 2, dated August 7, 2012, specifies 

airplanes with certain flight cycles ‘‘at the 

Revision 1 date of this service bulletin,’’ for 

this AD the condition is for airplanes with 

corresponding flight cycles ‘‘as of the 

effective date of this AD.’’ 

(m) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g), (h), (i), 

and (j) of this AD, if those actions were 

performed before the effective date of this AD 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
66760 Federal Register / Vol. 77, No. 216 / Wednesday, November 7, 2012 / Proposed Rules 

using Boeing Alert Service Bulletin 737– 

53A1255, Revision 1, dated November 7, 

2011, which is not incorporated by reference 

in this AD. 

(n) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9–ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for paragraphs (a), 

(b), (c), (d), and (e) of AD 2002–07–08, 

Amendment 39–12702 (67 FR 17917, April 

12, 2002) before the effective date of this AD, 

are approved for the corresponding 

requirements of paragraphs (g), (i), and (k) of 

this AD. 

(5) As of the effective date of this AD, any 

AMOCs approved for paragraphs (g) and (i) 

of this AD are approved as AMOCs for the 

corresponding requirements of paragraphs 

(a), (b), (c), (d), and (e) of AD 2002–07–08, 

Amendment 39–12702 (67 FR 17917, April 

12, 2002). 

(o) Related Information 

(1) For more information about this AD, 

contact Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6447; fax: 425–917–6590; 

email: wayne.lockett@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 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 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 

31, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–27141 Filed 11–6–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1162; Directorate 

Identifier 2012–NM–002–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, 

A330–200, A330–300, A340–200, A340– 

300, A340–500, and A340–600 series 

airplanes. This proposed AD was 

prompted by several reports of a 

burning smell and/or smoke in the 

cockpit during cruise phase leading, in 

some cases, to diversion to alternate 

airports. This proposed AD would 

require an inspection to identify the 

installed windshields and replacement 

of any affected windshield. We are 

proposing this AD to prevent 

significantly increased workload for the 

flightcrew, which could, under some 

flight phases and/or circumstances, 

constitute an unsafe condition. 

DATES: We must receive comments on 

this proposed AD by December 24, 

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, 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: 

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. 

FAA–2012–1162; Directorate Identifier 

2012–NM–002–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 2011–0242, 

dated December 19, 2011 (corrected 

February 15, 2012), (referred to after this 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1