16582 Federal Register / Vol. 76, No. 57 / Thursday, March 24, 2011 / Proposed Rules 

AFM by doing the actions specified in 

paragraphs (h)(2)(i), (h)(2)(ii), (h)(2)(iii), 

and (h)(2)(iv) of this AD. 

(i) Delete the procedure ‘‘WARNING 

HORN—CABIN ALTITUDE OR 

CONFIGURATION’’ added by AD 2006– 

13–13, Amendment 39–14666. If the 

title of this procedure has been changed 

according to FAA alternative method of 

compliance (AMOC) letter 130S–09– 

134a, dated April 28, 2009, delete the 

procedure that was approved according 

to this AMOC letter. 

(ii) Delete the procedure entitled 

‘‘CABIN ALTITUDE WARNING OR 

RAPID DEPRESSURIZATION’’ added by 

AD 2003–14–08, Amendment 39–13227. 

(iii) If the procedure entitled ‘‘CABIN 

ALTITUDE (Airplanes with the CABIN 

ALTITUDE lights installed)’’ is currently 

contained in the applicable Boeing 737 

AFM, delete the procedure entitled 

‘‘CABIN ALTITUDE (Airplanes with the 

CABIN ALTITUDE lights installed).’’ 

(iv) Add the following statement. This 

may be done by inserting a copy of this 

AD into the applicable AFM. 

‘‘CABIN ALTITUDE WARNING OR RAPID DEPRESSURIZATION 

Condition: The CABIN ALTITUDE warning light illuminates or the intermittent warning horn sounds in flight above 10,000 ft MSL. 

RECALL 

Oxygen Masks and Regulators ...................................................................................................... ON, 100%. 

Crew Communications ................................................................................................................... ESTABLISH. 

REFERENCE 

Pressurization Mode Selector ........................................................................................................ MANUAL. 

Outflow Valve Switch .................................................................................................................... CLOSE. 

If Cabin Altitude is uncontrollable: 

Emergency Descent (If Required) .................................................................................................. INITIATE. 

Passenger Oxygen Switch .............................................................................................................. ON. 

Thrust Levers .................................................................................................................................. CLOSE. 

Speed Brakes .................................................................................................................................. FLIGHT DETENT. 

Target Speed ................................................................................................................................... VMO/MMO.’’ 

(3) Revise the Normal Procedures 

Section of the applicable Boeing 737 

AFM by doing the actions specified in 

paragraphs (h)(3)(i) and (h)(3)(ii) of this 

AD. 

(i) Delete the ‘‘CABIN ALTITUDE 

WARNING TAKEOFF BRIEFING’’ 

procedure added by AD 2008–23–07. 

(ii) Add the following statement. This 

may be done by inserting a copy of this 

AD into the applicable AFM. 

‘‘For normal operations, the pressurization 

mode selector should be in AUTO prior to 

takeoff. 

Note 1: When statements identical to those 

specified in paragraphs (h)(2)(iv) and 

(h)(3)(ii) of this AD have been included in the 

general revisions of the AFM, the general 

revisions may be inserted into the AFM, and 

the copies of this AD may be removed from 

the AFM. 

Terminating Action for Affected ADs 

(i) Accomplishment of the 

requirements of this AD terminates the 

requirements of the ADs identified in 

paragraphs (i)(1), (i)(2), and (i)(3) of this 

AD for only the airplanes identified in 

paragraph (c) of this AD. 

(1) AD 2003–14–08: The requirements 

specified in Table 1 and Figure 1 of that 

AD. 

(2) AD 2008–23–07: All requirements 

of that AD. 

(3) AD 2006–13–13: All requirements 

of that AD. 

Special Flight Permit 

(j) Special flight permits, as described 

in Section 21.197 and Section 21.199 of 

the Federal Aviation Regulations (14 

CFR 21.197 and 21.199), are not 

allowed. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Seattle 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 

e-mailed to: 9-ANM-Seattle-ACOAMOC-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. 

Related Information 

(l) For more information about this 

AD, contact Jeffrey W. Palmer, 

Aerospace Engineer, Systems and 

Equipment Branch, ANM–130S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; phone: (425) 

917–6472; fax: (425) 917–6590; e-mail: 

jeffrey.w.palmer@faa.gov. 

(m) For service information identified 

in this 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; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, the 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

Issued in Renton, Washington, on March 

14, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–6931 Filed 3–23–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0257; Directorate 

Identifier 2010–NM–122–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318, A319, A320, and A321 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above that would 

supersede an existing AD. This 

proposed AD results from mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 


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aviation product. The MCAI describes 

the unsafe condition as: 

* * * * * 

The issue 10 of Airbus A318/A319/A320/ 

A321 ALI [Airworthiness Limitation Items] 

Document and issue 2 of Airbus A319 

Corporate Jet ALI Document introduce more 

restrictive maintenance requirements/ 

airworthiness limitations. Failure to comply 

with this issue 10 constitutes an unsafe 

condition. * * * 

* * * * * 

The unsafe condition is fatigue 

cracking, accidental damage, or 

corrosion in principal structural 

elements and possible failure of certain 

life limited parts, which could result in 

reduced structural integrity of the 

airplane. The proposed AD would 

require actions that are intended to 

address the unsafe condition described 

in the MCAI. 

DATES: We must receive comments on 

this proposed AD by May 9, 2011. 

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 W12–40, 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, 

Airworthiness Office—EAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; e-mail 

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: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2141; fax (425) 227–1149; 

tim.dulin@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–2011–0257; Directorate Identifier 

2010–NM–122–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 September 21, 2007, we issued AD 

2007–20–05, Amendment 39–15215 

(72 FR 56262, October 3, 2007). That AD 

required operators of Airbus Model 

A318, A319, A320, and A321 series 

airplanes to revise the Airworthiness 

Limitations Section (ALS) of the 

Instructions for Continued 

Airworthiness to incorporate Sub-part 

1–2, ‘‘Life Limits,’’ and Sub-part 1–3, 

‘‘Demonstrated Fatigue Lives,’’ of Airbus 

A318/A319/A320/A321 ALS Part 1— 

Safe Life Airworthiness Limitation 

Items, dated February 28, 2006, and for 

certain airplanes, Airbus A318/A319/ 

A320/A321 Airworthiness Limitation 

Items, Document AI/SE–M4/95A.0252/ 

96, Issue 7, dated December 2005; Issue 

08, dated March 2006; or Issue 09, dated 

November 2006. These actions were 

intended to address an unsafe condition 

on the products listed above. 

Since we issued AD 2007–20–05, we 

have determined that more restrictive 

limitations are necessary. We have also 

added Model A318–121 and –122 

airplanes to the applicability. The 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0071R1, 

dated May 28, 2010 (referred to after 

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

condition for the specified products. 

The MCAI states: 

The airworthiness limitations are currently 

included in Airbus A318/A319/A320/A321 

Airworthiness Limitations Section (ALS). 

The airworthiness limitations applicable to 

the Damage Tolerant Airworthiness 

Limitation Items (DT ALI) are currently given 

in Airbus A318/A319/A320/A321 ALI 

Document reference AI/SE–M4/95A.0252/96 

and Airbus A319 Corporate Jet ALI 

Document reference AI/SE–M2/95A.1038/99, 

which are approved by the European 

Aviation Safety Agency (EASA) and 

referenced in Airbus Airworthiness 

Limitations Section (ALS) Part 2. 

The issue 10 of Airbus A318/A319/A320/ 

A321 ALI Document and issue 2 of Airbus 

A319 Corporate Jet ALI Document introduce 

more restrictive maintenance requirements/ 

airworthiness limitations. Failure to comply 

with this issue 10 constitutes an unsafe 

condition. 

EASA AD 2010–0071 retains the 

requirements of EASA AD 2006–0165, which 

is superseded, and requires the 

implementation of more restrictive 

maintenance requirements/airworthiness 

limitations as specified in Airbus A318/ 

A319/A320/A321 ALI Document reference 

AI/SE–M4/95A.0252/96 issue 10 and Airbus 

A319 Corporate Jet ALI Document reference 

AI/SE–M2/95A.1038/99. 

This AD has been revised to clarify the 

special compliance times defined in Table 1 

of this AD. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Airbus has issued A318/A319/A320/ 

A321 Airworthiness Limitation Items, 

Document AI/SE–M4/95A.0252/96, 

Issue 10, dated October 2009; and A319 

Corporate Jet Airworthiness Limitation 

Items, Document reference AI/SE–M2/ 

95A.1038/99, Issue 02, dated March 

2009. A319 Corporate Jet Airworthiness 

Limitation Items, Document AI/SE–M2/ 

95A.1038/99, Issue 02, dated March 

2009, states that the limitations for the 

Model A319 corporate jets are specified 

in Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, 

Document AI/SE–M4/95A.0252/96, 

Issue 10, dated October 2009. 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 


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country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a NOTE within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 729 products of U.S. 

registry. 

The actions that are required by AD 

2007–20–05 and retained in this 

proposed AD take about 1 work-hour 

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 $85 per 

product. 

We estimate that it would take about 

1 work-hour 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 

$61,965, or $85 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. 

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 Amendment 39–15215 (72 FR 

56262, October 3, 2007) and adding the 

following new AD: 

Airbus: Docket No. FAA–2011–0257; 

Directorate Identifier 2010–NM–122–AD. 

Comments Due Date 

(a) We must receive comments by May 9, 

2011. 

Affected ADs 

(b) This AD supersedes AD 2007–20–05, 

Amendment 39–15215. 

Applicability 

(c) This AD applies to all Airbus Model 

A318–111, –112, –121, and –122 airplanes; 

A319–111, –112, –113, –114, –115, –131, 

–132, and –133 airplanes; Model A320–111, 

–211, –212, –214, –231, –232, and –233 

airplanes; and Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes; 

certificated in any category. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance according 

to paragraph (n) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued damage tolerance of the affected 

structure. The FAA has provided guidance 

for this determination in Advisory Circular 

(AC) 25.1529–1. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 05: Wings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

* * * * * 

The issue 10 of Airbus A318/A319/A320/ 

A321 ALI [Airworthiness Limitation Items] 

Document and issue 2 of Airbus A319 

Corporate Jet ALI Document introduce more 

restrictive maintenance requirements/ 

airworthiness limitations. Failure to comply 

with this issue 10 constitutes an unsafe 

condition. * * * 

* * * * * 

The unsafe condition is fatigue cracking, 

accidental damage, or corrosion in principal 

structural elements and possible failure of 

certain life limited parts, which could result 

in reduced structural integrity of the 

airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2007– 

20–05 

Revise Airworthiness Limitations Section 

(ALS) To Incorporate Safe Life ALIs 

(g) For Airbus Model A318–111, and –112 

airplanes; A319–111, –112, –113, –114, –115, 

–131, –132, and –133 airplanes; Model 

A320–111, –211, –212, –214, –231, –232, and 

–233 airplanes; and Model A321–111, –112, 

–131, –211, –212, –213, –231, and –232 

airplanes: Within 3 months after November 7, 

2007 (the effective date of AD 2007–20–05), 

revise the ALS of the Instructions for 

Continued Airworthiness to incorporate Subpart 1–2, ‘‘Life Limits,’’ and Sub-part 1–3, 

‘‘Demonstrated Fatigue Lives,’’ of Airbus 


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A318/A319/A320/A321 ALS Part 1—Safe 

Life Airworthiness Limitation Items, dated 

February 28, 2006. Accomplish the actions in 

Sub-part 1–2, ‘‘Life Limits,’’ and Sub-part 1– 

3, ‘‘Demonstrated Fatigue Lives,’’ of Airbus 

A318/A319/A320/A321 ALS Part 1—Safe 

Life Airworthiness Limitation Items, dated 

February 28, 2006, at the times specified in 

Sub-part 1–2, ‘‘Life Limits,’’ and Sub-part 1– 

3, ‘‘Demonstrated Fatigue Lives,’’ of Airbus 

A318/A319/A320/A321 ALS Part 1—Safe 

Life Airworthiness Limitation Items, dated 

February 28, 2006, except as provided by 

paragraph (i) of this AD. 

Revise ALS To Incorporate Damage-Tolerant 

ALIs 

(h) For Airbus Model A318–111, and –112 

airplanes; A319–111, –112, –113, –114, –115, 

–131, –132, and –133 airplanes; Model 

A320–111, –211, –212, –214, –231, –232, and 

–233 airplanes; and Model A321–111, –112, 

–131, –211, –212, –213, –231, and –232 

airplanes, except Model A319 airplanes on 

which Airbus Modifications 28238, 28162, 

and 28342 have been incorporated in 

production: Within 14 days after November 

7, 2007, revise the ALS of the Instructions for 

Continued Airworthiness to incorporate 

Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 7, dated 

December 2005 (approved by the EASA on 

February 7, 2006); Issue 08, dated March 

2006 (approved by the EASA on January 4, 

2007); or Issue 09, dated November 2006 

(approved by the EASA on May 21, 2007). 

Accomplish the actions in Airbus A318/ 

A319/A320/A321 Airworthiness Limitation 

Items, Document AI/SE–M4/95A.0252/96, 

Issue 7, dated December 2005; Issue 08, dated 

March 2006; or Issue 09, dated November 

2006; at the times specified in Airbus A318/ 

A319/A320/A321 Airworthiness Limitation 

Items, Document AI/SE–M4/95A.0252/96, 

Issue 7, dated December 2005; Issue 08, dated 

March 2006; or Issue 09, dated November 

2006; as applicable; except as provided by 

paragraph (i) of this AD. Doing the actions 

required by paragraph (j) of this AD 

terminates the requirements of this 

paragraph. 

Grace Period for New or More Restrictive 

Actions 

(i) For Airbus Model A318–111, and –112 

airplanes; A319–111, –112, –113, –114, –115, 

–131, –132, and –133 airplanes; Model 

A320–111, –211, –212, –214, –231, –232, and 

–233 airplanes; and Model A321–111, –112, 

–131, –211, –212, –213, –231, and –232 

airplanes: For any new of more restrictive life 

limit introduced with Sub-part 1–2, ‘‘Life 

Limits,’’ and Sub-part 1–3, ‘‘Demonstrated 

Fatigue Lives,’’ of Airbus A318/A319/A320/ 

A321 ALS Part 1—Safe Life Airworthiness 

Limitation Items, dated February 28, 2006, 

replace the part at the time specified in Subpart 1–2, ‘‘Life Limits,’’ and Sub-part 1–3, 

‘‘Demonstrated Fatigue Lives,’’ of Airbus 

A318/A319/A320/A321 ALS Part 1—Safe 

Life Airworthiness Limitation Items, dated 

February 28, 2006, or within 6 months after 

November 7, 2007, whichever is later. For 

any new or more restrictive inspection 

introduced with Airbus A318/A319/A320/ 

A321 Airworthiness Limitation Items, 

Document AI/SE–M4/95A.0252/96, Issue 7, 

dated December 2005; Issue 08, dated March 

2006; or Issue 09, dated November 2006; do 

the inspection at the time specified Airbus 

A318/A319/A320/A321 Airworthiness 

Limitation Items, Document AI/SE–M4/ 

95A.0252/96, Issue 7, dated December 2005; 

Issue 08, dated March 2006; or Issue 09, 

dated November 2006; as applicable; or 

within 6 months after November 7, 2007, 

whichever is later. 

New Requirements of This AD 

Revise ALS To Incorporate Damage-Tolerant 

ALIs With Revised Compliance Times 

(j) Within 9 months after the effective date 

of this AD: Revise the maintenance program 

by incorporating all maintenance 

requirements and associated airworthiness 

limitations specified in the Airbus A318/ 

A319/A320/A321 Airworthiness Limitation 

Items, Document AI/SE–M4/95A.0252/96, 

Issue 10, dated October 2009. Comply with 

all applicable maintenance requirements and 

associated airworthiness limitations included 

in Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 10, dated 

October 2009, except as provided by 

paragraph (k) of this AD. Doing the actions 

required by this paragraph terminates the 

requirements of paragraph (h) of this AD. 

Special Compliance Times for Certain Tasks 

(k) For new and more restrictive tasks 

introduced with Airbus A318/A319/A320/ 

A321 Airworthiness Limitation Items, 

Document AI/SE–M4/95A.0252/96, Issue 10, 

dated October 2009, as specified in Table 1 

of this AD: The initial compliance time for 

doing the tasks is specified in Table 1 of this 

AD. 

TABLE 1—COMPLIANCE TIMES FOR NEW TASKS

Task Applicability (as specified in the 

applicability column of the task) 

Compliance time, whichever occurs later 

545102–01–6 ................................. Group 19–1A CFM, Group 19–1B 

CFM, and A320–200 CFM/IAE.

The threshold as defined in Airbus A318/A319/A320/A321 Airworthiness Limitation Items, 

Document AI/SE–M4/95A.0252/ 

96, Issue 10, dated October 

2009.

Within 2,000 flight cycles or 5,500 

flight hours, after the effective 

date of this AD, whichever occurs first. 

545102–01–7 ................................. A320–100 ..................................... The threshold as defined in Airbus A318/A319/A320/A321 Airworthiness Limitation Items, 

Document AI/SE–M4/95A.0252/ 

96, Issue 10, dated October 

2009.

Within 2,000 flight cycles or 2,000 

flight hours, after the effective 

date of this AD, whichever occurs first. 

572050–01–1 or alternative task 

572050-02–1.

Group 19–1A and Group 19–1B .. At the time of the next due accomplishment of any one of the 

tasks 572004, 572020, or 

572053 as currently described 

in the Airbus A318/A319/A320/ 

A321 Airworthiness Limitation 

Items, Document AI/SE–M4/ 

95A.0252/96, Issue 7, dated 

December 2005; Issue 08, 

dated March 2006; or Issue 09, 

dated November 2006.

Within 6 months after the effective 

date of this AD. 


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TABLE 1—COMPLIANCE TIMES FOR NEW TASKS—Continued 

572050–01–4 or alternative task 

572050-02–4.

A320–200 ..................................... At the time of the next due accomplishment of any one of the 

tasks 572004, 572020, or 

572053 as currently described 

in the Airbus A318/A319/A320/ 

A321 Airworthiness Limitation 

Items, Document AI/SE–M4/ 

95A.0252/96, Issue 7, dated 

December 2005; Issue 08, 

dated March 2006; or Issue 09, 

dated November 2006.

Within 6 months after the effective 

date of this AD. 

572050–01–5 or alternative task 

572050-02–5.

Group 21–1A ................................ At the time of the next due accomplishment of any one of the 

tasks 572004, 572020, or 

572053 as currently described 

in the Airbus A318/A319/A320/ 

A321 Airworthiness Limitation 

Items, Document AI/SE-M4/ 

95A.0252/96, Issue 7, dated 

December 2005; Issue 08, 

dated March 2006; or Issue 09, 

dated November 2006.

Within 6 months after the effective 

date of this AD. 

572050–01–7 or alternative task 

572050-02–7.

A320–100 ..................................... At the time of the next due accomplishment of any one of the 

tasks 572004, 572020, or 

572053 as currently described 

in the Airbus A318/A319/A320/ 

A321 Airworthiness Limitation 

Items, Document AI/SE-M4/ 

95A.0252/96, Issue 7, dated 

December 2005; Issue 08, 

dated March 2006; or Issue 09, 

dated November 2006.

Within 6 months after the effective 

date of this AD. 

534132–01–1 ................................. A320 PRE 30748 .......................... The threshold/interval as defined 

in Airbus A318/A319/A320/ 

A321 Airworthiness Limitation 

Items, Document AI/SE–M4/ 

95A.0252/96, Issue 10, dated 

October 2009.

Within 100 days after the effective 

date of this AD, without exceeding the previous threshold/interval as defined in Airbus A318/ 

A319/A320/A321 Airworthiness 

Limitation Items, Document AI/ 

SE–M4/95A.0252/96, Issue 7, 

dated December 2005; Issue 

08, dated March 2006; or Issue 

09, dated November 2006. 

531118–01–1 ................................. A318 (except (A318–121 and 

–122), Group 19–1A, Group 

19–1B, A320, A321.

The threshold/interval as defined 

in Airbus A318/A319/A320/ 

A321 Airworthiness Limitation 

Items, Document AI/SE–M4/ 

95A.0252/96, Issue 10, dated 

October 2009.

Within 100 days after the effective 

date of this AD, without exceeding the previous threshold/interval as defined in Airbus A318/ 

A319/A320/A321 Airworthiness 

Limitation Items, Document AI/ 

SE–M4/95A.0252/96, Issue 7, 

dated December 2005; Issue 

08, dated March 2006; or Issue 

09, dated November 2006. 

531118–01–1 ................................. A318–121 and –122 ..................... The threshold/interval as defined 

in Airbus A318/A319/A320/ 

A321 Airworthiness Limitation 

Items, Document AI/SE–M4/ 

95A.0252/96, Issue 10, dated 

October 2009.

Within 100 days after the effective 

date of this AD. 

Note 2: New ALI Task 572050 refers to the 

outer wing dry bay and is comprised of 

extracts from three ALI Tasks: 572004, 

572020 and 572053. The threshold of ALI 

Task 572050 for the whole dry bay area is 

that of the lowest threshold of the source ALI 

tasks, i.e., that of ALI Task 572053. 

No Alternative Life Limits, Inspections, or 

Inspection Intervals 

(l) After the actions specified in paragraphs 

(g) and (h) of this AD have been 

accomplished, no alternative life limits, 

inspections, or inspection intervals may be 

used, except as provided by paragraphs (i) 

and (m) of this AD, and except as required 

by paragraph (j) of this AD. 

(m) After the actions specified in paragraph 

(j) of this AD have been accomplished, no 

alternative life limits, inspections, or 

inspection intervals may be used. 

FAA AD Differences 

Note 3: This AD differs from the MCAI 

and/or service information as follows: EASA 

AD requires operators to comply with the 

limitations specified in Airbus A318/A319/ 

A320/A321 Airworthiness Limitation Items, 

Document AI/SE–M4/95A.0252/96, Issue 10, 

dated October 2009; or Airbus A319 

Corporate Jet Airworthiness Limitation Items, 

Document AI/SE–M2/95A.1038/99, Issue 02, 

dated March 2009; as applicable. However, 


jdjones on DSK8KYBLC1PROD with PROPOSALS-1
Federal Register / Vol. 76, No. 57 / Thursday, March 24, 2011 / Proposed Rules 16587 

1Commission regulations referred to herein are 

found at 17 CFR Ch. 1 (2010). They are accessible 

on the Commission’s Web site at http:// 

www.cftc.gov. 

2See Dodd-Frank Wall Street Reform and 

Consumer Protection Act, Public Law 111–203, 124 

Stat. 1376 (2010). The text of the Dodd-Frank Act 

may be accessed at http://www.cftc.gov/ 

LawRegulation/OTCDERIVATIVES/index.htm. 

3Pursuant to section 701 of the Dodd-Frank Act, 

Title VII may be cited as the ‘‘Wall Street 

Transparency and Accountability Act of 2010.’’ 

4 7 U.S.C. 1 et seq. 

5 7 U.S.C. 5b(c)(2). 

6 76 FR 3698, Jan. 20, 2011. 

this AD does not require incorporating 

Airbus A319 Corporate Jet Airworthiness 

Limitation Items, Document AI/SE–M2/ 

95A.1038/99, Issue 02, dated March 2009, 

because that ALI only specifies compliance 

with the limitations specified in Airbus 

A318/A319/A320/A321 Airworthiness 

Limitation Items, Document AI/SE–M4/ 

95A.0252/96, Issue 10, dated October 2009. 

Other FAA AD Provisions 

(n) 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/ACO, send it to 

Attn: Tim Dulin, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–2141; fax (425) 

227–1149. Information may be e-mailed 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. 

Related Information 

(o) Refer to MCAI European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2010–0071R1, dated May 28, 2010; 

Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 7, dated 

December 2005; Airbus A318/A319/A320/ 

A321 Airworthiness Limitation Items, 

Document AI/SE–M4/95A.0252/96, Issue 08, 

dated March 2006; Airbus A318/A319/A320/ 

A321 Airworthiness Limitation Items, 

Document AI/SE–M4/95A.0252/96, Issue 09, 

dated November 2006; and Airbus A318/ 

A319/A320/A321 Airworthiness Limitation 

Items, Document AI/SE–M4/95A.0252/96, 

Issue 10, dated October 2009; for related 

information. 

Issued in Renton, Washington, on March 

15, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–6932 Filed 3–23–11; 8:45 am] 

BILLING CODE 4910–13–P 

COMMODITY FUTURES TRADING 

COMMISSION 

17 CFR Part 39 

RIN 3038–AC98 

Risk Management Requirements for 

Derivatives Clearing Organizations 

AGENCY: Commodity Futures Trading 

Commission. 

ACTION: Reopening of comment period. 

SUMMARY: The Commodity Futures 

Trading Commission (Commission) is 

reopening the comment period for a 

proposed rule that would require 

derivatives clearing organizations 

(DCOs) to report end-of-day positions 

for each clearing member, by customer 

origin and house origin, and for 

customer origin, separately, the gross 

positions of each beneficial owner. 

DATES: Submit comments on or before 

April 25, 2011. 

ADDRESSES: You may submit comments, 

identified by RIN number 3038–AC98, 

by any of the following methods: 

• Agency Web site, via its Comments 

Online process: http:// 

comments.cftc.gov. Follow the 

instructions for submitting comments 

through the Web site. 

• Mail: David A. Stawick, Secretary of 

the Commission, Commodity Futures 

Trading Commission, Three Lafayette 

Centre, 1155 21st Street, NW., 

Washington, DC 20581. 

• Hand Delivery/Courier: Same as 

mail above. 

• Federal eRulemaking Portal: http:// 

www.Regulations.gov. Follow the 

instructions for submitting comments. 

Please submit comments by only one 

method. 

All comments must be submitted in 

English, or if not, accompanied by an 

English translation. Comments will be 

posted as received to http:// 

www.cftc.gov. You should submit only 

information that you wish to make 

available publicly. If you wish the 

Commission to consider information 

that may be exempt from disclosure 

under the Freedom of Information Act 

(FOIA), a petition for confidential 

treatment of the exempt information 

may be submitted according to the 

procedures established in § 145.9 of the 

Commission’s regulations.1 The 

Commission reserves the right, but shall 

have no obligation, to review, prescreen, filter, redact, refuse, or remove 

any or all of your submission from 

http://www.cftc.gov that it may deem to 

be inappropriate for publication, such as 

obscene language. All submissions that 

have been redacted or removed that 

contain comments on the merits of the 

rulemaking will be retained in the 

public comment file and will be 

considered as required under the 

Administrative Procedure Act and other 

applicable laws, and may be accessible 

under FOIA. 

FOR FURTHER INFORMATION CONTACT: 

Phyllis P. Dietz, Associate Director, 

202–418–5449, pdietz@cftc.gov, Jacob 

Preiserowicz, Attorney-Advisor, 202– 

418–5432, jpreiserowicz@cftc.gov, 

Division of Clearing and Intermediary 

Oversight, Commodity Futures Trading 

Commission, Three Lafayette Centre, 

1155 21st Street, NW., Washington, DC 

20581; and Anne C. Polaski, Special 

Counsel, 312–596–0575, 

apolaski@cftc.gov, Division of Clearing 

and Intermediary Oversight, Commodity 

Futures Trading Commission, 525 West 

Monroe Street, Chicago, Illinois 60661. 

SUPPLEMENTARY INFORMATION: On July 

21, 2010, President Obama signed the 

Dodd-Frank Act.2 Title VII of the DoddFrank Act 3 amended the Commodity 

Exchange Act (CEA) 4 to establish a 

comprehensive regulatory framework to 

reduce risk, increase transparency, and 

promote market integrity within the 

financial system. Section 725(c) of the 

Dodd-Frank Act amended Section 

5b(c)(2) of the CEA, which sets forth 

core principles with which a DCO must 

comply to be registered and to maintain 

registration as a DCO.5

On December 16, 2010, the 

Commission approved for publication in 

the Federal Register proposed 

regulations which, among other things, 

would implement DCO Core Principle D 

(Risk Management) and would establish 

a related reporting requirement under 

Core Principle J (Reporting). More 

specifically, the Commission proposed 

§ 39.13(g)(8)(i) to establish customer 

‘‘gross margin’’ requirements, and 

proposed § 39.19(c)(1)(iv) to establish 

related daily reporting requirements. 

The proposed regulations were 

published for comment in the January 

20, 2011 issue of the Federal Register.6

The Federal Register preamble 

explained that proposed § 39.13(g)(8)(i) 


jdjones on DSK8KYBLC1PROD with PROPOSALS-1