32060 Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules 

777–53A0054, Revision 1, dated November 4, 

2010; specify to contact Boeing for 

appropriate action, accomplish applicable 

actions using a method approved in 

accordance with the procedures specified in 

paragraph (q) of this AD. 

(j) Retained Exception to Service Bulletin 

Specifications, Contact for Inspection 

Requirements 

This paragraph restates the requirements of 

paragraph (j) of AD 2009–24–08, Amendment 

39–16096 (74 FR 62217, November 27, 2009). 

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

Boeing Alert Service Bulletin 777–53A0054, 

dated August 7, 2008, specifies to ‘‘contact 

Boeing for inspection requirements for 

operation beyond 60,000 total flight-cycles 

after first repaint,’’ for those airplanes, this 

AD requires contacting the Manager, Seattle 

Aircraft Certification Office (ACO), for all 

inspection requirements of this AD and doing 

the requirements. 

(k) Retained Reporting 

This paragraph restates the requirements of 

paragraph (k) of AD 2009–24–08, 

Amendment 39–16096 (74 FR 62217, 

November 27, 2009). At the applicable time 

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

AD: Submit a report of positive findings of 

cracks found during the inspection required 

by paragraphs (g) and (m) of this AD to the 

Boeing Commercial Airplane Group, P.O. 

Box 3707, Seattle, Washington 98124–2207. 

Alternatively, operators may submit reports 

to their Boeing field service representatives. 

The report must contain, at a minimum, the 

inspection results, a description of any 

discrepancies found, the airplane serial 

number, and the number of flight cycles and 

flight hours on the airplane. Under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements contained in this AD and has 

assigned OMB Control Number 2120–0056. 

(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. 

(l) New Inspection for External Decals 

Within 24 months after the effective date 

of this AD: Inspect to determine the locations 

where external decals have been applied or 

removed across affected lap joints, large 

cargo door hinges, and external doublers, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 777– 

53A0054, Revision 1, dated November 4, 

2010. 

(m) New Inspection for Scribe Lines and 

Related Investigative and Corrective Actions 

If, during the inspection required by 

paragraph (l) of this AD, any location is 

found where external decals have been 

applied or removed across lap joints, large 

cargo door hinges, or external doublers: 

Before further flight, do a detailed 

exploratory inspection for scribe lines at all 

affected locations, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–53A0054, Revision 1, 

dated November 4, 2010. Do all applicable 

related investigative and corrective actions at 

the times specified in Boeing Service Bulletin 

777–53A0054, Revision 1, dated November 4, 

2010, by accomplishing all actions specified 

in the Accomplishment Instructions of 

Boeing Service Bulletin 777–53A0054, 

Revision 1, dated November 4, 2010, except 

as provided by paragraph (i) of this AD. 

(n) Exceptions to Service Information 

(1) Where Boeing Service Bulletin 777– 

53A0054, Revision 1, dated November 4, 

2010, specifies a compliance time after the 

date on that service bulletin, paragraphs (l) 

and (m) of this AD require compliance within 

the specified compliance time after the 

effective date of this AD. 

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

Boeing Service Bulletin 777–53A0054, 

Revision 1, dated November 4, 2010, 

specifies to ‘‘contact Boeing for inspection 

requirements for operation beyond 60,000 

total flight-cycles after first repaint,’’ for 

those airplanes, this AD requires contacting 

the Manager, Seattle ACO, for all inspection 

requirements of this AD and doing the 

requirements. 

(o) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (m) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 777–53A0054, dated August 

7, 2008. 

(p) Paperwork Reduction Act Burden 

Statement 

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. 

(q) Alternative Methods of Compliance 

(AMOCs) 

(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 emailed to: 9–ANM– 

Seattle–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 AD 2009–24–08, 

Amendment 39–16096 (74 FR 62217, 

November 27, 2009), are approved as AMOCs 

for the corresponding provisions of this AD, 

except that AMOCs approved for AD 2009– 

24–08 are not approved for fuselage areas 

where any decals may have been installed or 

removed on airplanes that have never been 

stripped or repainted since they left the 

factory. 

(r) Related Information 

(1) For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425–917– 

6577; fax: 425–917–6590; email: 

Berhane.Alazar@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, Washington 98124–2207; phone: 

206–544–5000, extension 1; fax: 206–766– 

5680; email: me.boecom@boeing.com; 

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, Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on May 21, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–13169 Filed 5–30–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0493; Directorate 

Identifier 2011–NM–180–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules 32061 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) for 

all Airbus Model A318–111 and –112 

airplanes; and all Model A319, A320, 

and A321 series airplanes. The existing 

AD currently requires revising the 

Airworthiness Limitations Section 

(ALS) of the Instructions for Continued 

Airworthiness to incorporate new 

limitations for fuel tank systems. Since 

we issued that AD, Airbus has issued 

more restrictive maintenance 

requirements and/or airworthiness 

limitations. This proposed AD would 

revise the maintenance program to 

incorporate revised fuel maintenance 

and inspection tasks, and add airplanes 

to the applicability. We are proposing 

this AD to prevent the potential of 

ignition sources inside fuel tanks, 

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 July 16, 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, 

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; 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1405; 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–2012–0493; Directorate Identifier 

2011–NM–180–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 November 16, 2009, we issued AD 

2007–15–06 R1, Amendment 39–16097 

(74 FR 62219, November 27, 2009). That 

AD required actions intended to address 

an unsafe condition on the products 

listed above. 

Since we issued AD 2007–15–06 R1, 

Amendment 39–16097 (74 FR 62219, 

November 27, 2009), Airbus has issued 

A318/A319/A320/A321 Fuel 

Airworthiness Limitations, Document 

95A.1931/05, Issue 4, dated August 26, 

2010. The European Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Community, has issued EASA 

Airworthiness Directive 2011–0155, 

dated August 25, 2011 (referred to after 

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

condition for the specified products. 

The MCAI states: 

The airworthiness limitations are currently 

published in the Airbus A318/A319/A320/ 

A321 Airworthiness Limitations Section 

(ALS). 

The Fuel Airworthiness Limitations (FAL) 

are specified in Airbus A318/A319/A320/ 

A321 FAL Document reference 95A.1931/05, 

which is approved by the European Aviation 

Safety Agency (EASA) and referenced in the 

Airbus A318/A319/A320/A321 ALS Part 5. 

The issue 4 of Airbus A318/A319/A320/ 

A321 FAL Document introduces more 

restrictive maintenance requirements and/or 

airworthiness limitations. Failure to comply 

with these more restrictive maintenance 

requirements and airworthiness limitations 

contained in this document constitutes an 

unsafe condition. 

This [EASA] AD retains the requirement of 

EASA AD 2006–0203, which is superseded, 

and requires the implementation of the new 

or more restrictive maintenance requirements 

and/or airworthiness limitations as specified 

in Airbus A318/A319/A320/A321 FAL 

Document issue 4. 

We are proposing this AD to prevent the 

potential of ignition sources inside fuel 

tanks, which, in combination with 

flammable fuel vapors, could result in a 

fuel tank explosion and consequent loss 

of the airplane. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Airbus has issued A318/A319/A320/ 

A321 Fuel Airworthiness Limitations, 

Document 95A.1931/05, Issue 4, dated 

August 26, 2010. The actions described 

in this service information are intended 

to correct the unsafe condition 

identified in the MCAI. 

Explanation of Changes Made to This 

NPRM 

We have changed Note 1 and Note 2 

of the restated requirements of AD 

2007–15–06 R1, Amendment 39–16097 

(74 FR 62219, November 27, 2009), to 

lettered paragraphs (i) and (j), 

respectively, in this NPRM. These 

changes do not add any additional 

burden upon the public than was 

required in the existing AD. 

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 

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32062 Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules 

affect about 745 products of U.S. 

registry. 

The actions that are required by AD 

2007–15–06 R1, Amendment 39–16097 

(74 FR 62219, November 27, 2009), and 

retained in this proposed AD take about 

2 work-hours per product, at an average 

labor rate of $85 per work hour. 

Required parts cost about $0 per 

product. Based on these figures, the 

estimated cost of the currently required 

actions is $170 per product. 

We estimate that it would take about 

2 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 

$126,650, or $170 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) 

2007–15–06 R1, Amendment 39–16097 

(74 FR 62219, November 27, 2009), and 

adding the following new AD: 

Airbus: Docket No. FAA–2012–0493; 

Directorate Identifier 2011–NM–180–AD. 

(a) Comments Due Date 

We must receive comments by July 16, 

2012. 

(b) Affected ADs 

This AD supersedes AD 2007–15–06 R1, 

Amendment 39–16097 (74 FR 62219, 

November 27, 2009). 

(c) Applicability 

(1) This AD applies to Airbus Model A318– 

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

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

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

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

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

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

certificated in any category; all serial 

numbers. 

(2) This AD requires revisions to certain 

operator maintenance documents to include 

new actions (e.g., inspections and/or Critical 

Design Configuration Control Limitations 

(CDCCLs). Compliance with these actions 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 (AMOC) according to paragraph 

(l)(1) of this AD. The request should include 

a description of changes to the required 

actions that will ensure the continued 

operational safety of the airplane. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Periodic Inspections. 

(e) Reason 

This AD was prompted by Airbus issuing 

more restrictive maintenance requirements 

and/or airworthiness limitations. We are 

issuing this AD to prevent the potential of 

ignition sources inside fuel tanks, which, in 

combination with flammable fuel vapors, 

could result in a fuel tank explosion and 

consequent loss of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Revision of the Airworthiness 

Limitations Section (ALS) To Incorporate 

Fuel Maintenance and Inspection Tasks 

This paragraph restates the requirements of 

paragraph (f) of AD 2007–15–06 R1, 

Amendment 39–16097 (74 FR 62219, 

November 27, 2009). For Model A318–111 

and –112 airplanes, and Model A319, A320, 

and A321 airplanes: Within 3 months after 

August 28, 2007 (the effective date of AD 

2007–15–06), revise the ALS of the 

Instructions for Continued Airworthiness to 

incorporate Airbus A318/A319/A320/A321 

ALS Part 5—Fuel Airworthiness Limitations, 

dated February 28, 2006, as defined in Airbus 

A318/A319/A320/A321 Fuel Airworthiness 

Limitations, Document 95A.1931/05, Issue 1, 

dated December 19, 2005 (approved by the 

European Aviation Safety Agency (EASA) on 

March 14, 2006), Section 1, ‘‘Maintenance/ 

Inspection Tasks;’’ or Airbus A318/A319/ 

A320/A321 Fuel Airworthiness Limitations, 

Document 95A.1931/05, Issue 2, dated July 8, 

2008 (approved by the EASA on December 

19, 2008), Section 1, ’’Maintenance/ 

Inspection Tasks.’’ For all tasks identified in 

Section 1 of Airbus A318/A319/A320/A321 

Fuel Airworthiness Limitations, Document 

95A.1931/05, Issue 1, dated December 19, 

2005; or Issue 2, dated July 8, 2008; the 

initial compliance times start from August 

28, 2007, and the repetitive inspections must 

be accomplished thereafter at the intervals 

specified in Section 1, ’’Maintenance/ 

Inspection Tasks,’’ of Airbus A318/A319/ 

A320/A321 Fuel Airworthiness Limitations, 

Document 95A.1931/05, Issue 1, dated 

December 19, 2005; or Issue 2, dated July 8, 

2008. 

Note 1 to paragraph (g) of this AD: Airbus 

Operator Information Telex (OIT) SE 

999.0076/06, dated June 20, 2006, provides 

guidance on identifying the applicable 

sections of the Airbus A318/A319/A320/ 

A321 Airplane Maintenance Manual 

necessary for accomplishing the tasks 

specified in Section 1 ’’Maintenance/ 

Inspection Tasks,’’ of Airbus A318/A319/ 

A320/A321 Fuel Airworthiness Limitations, 

Document 95A.1931/05, Issue 1, dated 

December 19, 2005; or Issue 2, dated July 8, 

2008. 

(h) Retained Revision of the ALS To 

Incorporate CDCCLs 

This paragraph restates the requirements of 

paragraph (g) of AD 2007–15–06 R1, 

Amendment 39–16097 (74 FR 62219, 

November 27, 2009). For Airbus Model 

A318–111 and –112 airplanes, and Model 

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Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules 32063 

A319, A320, and A321 airplanes: Within 12 

months after August 28, 2007 (the effective 

date of AD 2007–15–06), revise the ALS of 

the Instructions for Continued Airworthiness 

to incorporate Airbus A318/A319/A320/ 

A321 ALS Part 5–Fuel Airworthiness 

Limitations, dated February 28, 2006, as 

defined in Airbus A318/A319/A320/A321 

Fuel Airworthiness Limitations, Document 

95A.1931/05, Issue 1, dated December 19, 

2005 (approved by the EASA on March 14, 

2006), Section 2, ‘‘Critical Design 

Configuration Control Limitations;’’ or 

Airbus A318/A319/A320/A321 Fuel 

Airworthiness Limitations, Document 

95A.1931/05, Issue 2, dated July 8, 2008 

(approved by EASA on December 19, 2008), 

Section 2, ’’Critical Design Configuration 

Control Limitations.’’ 

(i) Retained No Alternative Inspections, 

Inspection Intervals, or CDCCLs 

(1) This paragraph restates the 

requirements of paragraph (h) of AD 2007– 

15–06 R1, Amendment 39–16097 (74 FR 

62219, November 27, 2009). Except as 

provided by paragraph (l) of this AD: After 

accomplishing the actions specified in 

paragraphs (g) and (h) of this AD, no 

alternative inspections, inspection intervals, 

or CDCCLs may be used. 

(2) Notwithstanding any other maintenance 

or operational requirements, components that 

have been identified as airworthy or installed 

on the affected airplanes before the revision 

of the ALS, as required by paragraphs (g) and 

(h) of this AD, do not need to be reworked 

in accordance with the CDCCLs. However, 

once the ALS has been revised, future 

maintenance actions on these components 

must be done in accordance with the 

CDCCLs. 

(j) Revise Maintenance Program 

Within 6 months after the effective date of 

this AD: Revise the maintenance program to 

incorporate the new or revised tasks, life 

limits, and CDCCLs specified in Airbus 

A318/A319/A320/A321 Fuel Airworthiness 

Limitations, Document 95A.1931/05, Issue 4, 

dated August 26, 2010, except as required in 

paragraph (j)(4) of this AD. The initial 

compliance times and intervals are stated in 

these documents, except as required in 

paragraphs (j)(1) through (j)(4) of this AD, or 

within 6 months after the effective date of 

this AD, whichever occurs later. For certain 

tasks, the compliance times depend on the 

pre-modification and post-modification 

status of the airplane. Incorporating the 

requirements of this paragraph terminates the 

corresponding requirements of paragraphs (g) 

and (h) of this AD. 

(1) For airplanes whose first flight occurred 

before August 28, 2007 (the effective date of 

AD 2007–15–06 R1, Amendment 39–16097 

(74 FR 62219, November 27, 2009)), the first 

accomplishment of tasks 281800–01–1, 

Functional Check of Tank Vapour Seal and 

Vent Drain System; and 281800–02–1, 

Detailed Inspection of Vapour Seal; must be 

performed no later than 11 months after the 

effective date of this AD. 

(2) The first accomplishment of Tasks 

470000–01–1, Operational Check of DFSOV, 

Dual Flapper Check Valves and NEA Line for 

Leaks; 470000–02–1, Operational Check of 

both Dual Flapper Check Valves for Leaks; 

470000–03–1, Operational Check of Dual 

Flapper Check Valves for Reverse Flow and 

NEA Line for Leaks; 470000–04–1, 

Operational Check of Dual Flapper Check 

Valves for Reverse Flow; and 470000–05–1, 

Remove Air Separation Module (ASM) and 

Return to Vendor for Workshop Check; must 

be calculated, in accordance with paragraphs 

(j)(2)(i) or (j)(2)(ii) of this AD. 

(i) From the airplane first flight for 

airplanes on which Airbus modification 

38062 or 38195 has been embodied in 

production, or 

(ii) From the in-service installation of the 

fuel tank inerting system specified in Airbus 

Service Bulletin A320–47–1001, Airbus 

Service Bulletin A320–47–1002, Airbus 

Service Bulletin A320–47–1003, Airbus 

Service Bulletin A320–47–1004, Airbus 

Service Bulletin A320–47–1006, or Airbus 

Service Bulletin A320–47–1007. 

(3) Although Airbus A318/A319/A320/ 

A321 Fuel Airworthiness Limitations, 

Document 95A.1931/05, Issue 4, dated 

August 26, 2010, does not refer to Airbus 

Service Bulletin A320–47–1006 and Airbus 

Service Bulletin A320–47–1007, the tasks 

apply as follows: 

(i) Tasks 470000–01–1, Operational Check 

of DFSOV, Dual Flapper Check Valves and 

NEA Line for Leaks; and 470000–02–1, 

Operational Check of both Dual Flapper 

Check Valves for leaks; apply to airplanes 

that have previously accomplished the 

actions specified in Airbus Service Bulletin 

A320–47–1007. 

(ii) Task 470000–03–1, Operational Check 

of Dual Flapper Check Valves for Reverse 

Flow and NEA Line for Leaks; applies to 

airplanes that have previously accomplished 

the actions specified in Airbus Service 

Bulletin A320–47–1006, and that have not 

accomplished the actions specified in Airbus 

Service Bulletin A320–47–1007. 

(iii) Task 470000–04–1, Operational Check 

of Dual Flapper Check Valves for Reverse 

Flow; applies to airplanes in postmodification 38195 configuration and that 

have not accomplished the actions specified 

in Airbus Service Bulletin A320–47–1007. 

(iv) Task 470000–05–1, Remove ASM and 

return to Vendor for workshop check; applies 

to airplanes that have previously 

accomplished the actions specified in Airbus 

Service Bulletin A320–47–1007, and are in 

pre-modification 151529 configuration. 

(4) Replace each ASM identified in table 1 

of this AD in accordance with a method 

approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent). The compliance time for the 

replacement is before the accumulation of 

27,000 flight hours (component time)—i.e., 

the life limitation. 

Note 2 to paragraph (g)(4) of this AD: 

Airbus A318/A319/A320/A321 Maintenance 

Manual Task 47–10–43–920–001–A, Air 

Separation Module Replacement, is an 

additional source of guidance for 

accomplishment of the removal and 

replacement of the ASM. 

TABLE 1—ASM REPLACEMENT

ASM Part No. Affected airplane configuration 

2060017–101 .............................................................................................................................. Post-modification 38062, or 

Post-Airbus Service Bulletin A320–47–1002, or 

Post-Airbus Service Bulletin A320–47–1004, or 

Post-Airbus Service Bulletin A320–47–1007 

2060017–102 .............................................................................................................................. Post-modification 152033, or 

Post-Airbus Service Bulletin A320–47–1011 

(k) No Alternative Actions Intervals, and/or 

CDCCLs 

After accomplishing the revisions required 

by paragraph (j) of this AD, no alternative 

actions (e.g., inspections), intervals, and/or 

CDCCLs may be used other than those 

specified in Airbus A318/A319/A320/A321 

ALS Part 5—Fuel Airworthiness Limitations, 

dated February 28, 2006, as defined in Airbus 

A318/A319/A320/A321 Fuel Airworthiness 

Limitations, Document 95A.1931/05, Issue 4, 

dated August 26, 2010, unless the actions, 

intervals, and/or CDCCLs are approved as an 

AMOC in accordance with the procedures 

specified in paragraph (l)(1) of this AD. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1405; fax (425) 

227–1149. Information may be emailed to: 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

32064 Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules 

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. 

(m) Related Information 

(1) Refer to MCAI EASA Airworthiness 

Directive 2011–0155, dated August 25, 2011, 

and the following service information, for 

related information. 

(i) Airbus A318/A319/A320/A321 ALS Part 

5—Fuel Airworthiness Limitations, dated 

February 28, 2006. 

(ii) Airbus A318/A319/A320/A321 Fuel 

Airworthiness Limitations, Document 

95A.1931/05, Issue 1, dated December 19, 

2005. 

(iii) A318/A319/A320/A321 Fuel 

Airworthiness Limitations, Document 

95A.1931/05, Issue 2, dated July 8, 2008. 

(iv) Airbus A318/A319/A320/A321 Fuel 

Airworthiness Limitations, Document 

95A.1931/05, Issue 4, dated August 26, 2010. 

(2) For service information identified in 

this 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; 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. 

Issued in Renton, Washington, on May 18, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–13191 Filed 5–30–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0492; Directorate 

Identifier 2010–NM–126–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (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 747 airplanes. The 

existing AD currently requires repetitive 

visual inspections around the bushings 

of the wing landing gear (WLG) beam 

outboard end fittings for corrosion, and 

rework if necessary; and ultrasonic 

inspections for cracks of the outboard 

end fittings of the WLG support beams, 

and rework if necessary. Since we 

issued that AD, there have been new 

reports of corrosion damage to the end 

fittings of the WLG support beams, and 

one report of subsequent cracking in the 

end fittings. This proposed AD would 

add airplanes and repetitive inspections 

of the outboard end fitting of the left 

and right WLG support beams for cracks 

and corrosion, and corrective actions if 

necessary. We are proposing this AD to 

detect and correct corrosion and 

subsequent cracking in the outboard end 

fittings, which could result in 

separation of the fitting and damage to 

adjacent flight control cables and 

hydraulic systems and consequent 

reduced controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by July 16, 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 20590, 

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; email 

me.boecom@boeing.com; 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, 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 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 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Bill 

Ashforth, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 

98057–3356; phone: (425) 917–6432; 

fax: (425) 917–6590; email: 

bill.ashforth@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–2012–0492; Directorate Identifier 

2010–NM–126–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 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 July 7, 1989, we issued AD 89–15– 

07, amendment 39–6267 (54 FR 30009, 

July 18, 1989), for certain Model 747 

airplanes. That AD requires visual 

inspections around the bushings of the 

wing landing gear for corrosion, and 

repair if necessary, and ultrasonic 

inspections for cracks of the outboard 

end fittings of the WLG support beams, 

and overhaul if necessary. That AD 

resulted from a report of a fracture of the 

outboard end fitting of a left WLG beam. 

We issued that AD to prevent failure of 

the outboard end fitting of a WLG beam 

with possible damage to control cables 

or hydraulic lines in the area of the 

landing gear beam. 

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