Federal Register / Vol. 77, No. 193 / Thursday, October 4, 2012 / Proposed Rules 60655 

causing damage to the fire protection system, 

hydraulic system, electrical wiring, or other 

equipment located in the forward and aft 

cargo compartments. This damage could 

adversely affect the continued safe flight 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 Spacer Assembly Installation 

This paragraph restates the requirements of 

paragraph (f) of AD 2007–05–13, Amendment 

39–14974 (72 FR 10348, March 8, 2007). For 

Airbus Model A319, A320, and A321 

airplanes identified in paragraphs (g)(1) and 

(g)(2) of this AD: Within 36 months after 

April 12, 2007 (the effective date of AD 

2007–05–13), install spacer assemblies at the 

attachment points of the YZ-latches of the 

CLS in the forward and aft cargo 

compartments, as applicable, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–25–1294, 

Revision 2, dated September 5, 2006. 

Accomplishing the actions in paragraph (i) of 

this AD terminates the requirements of 

paragraph (g) of this AD. 

(1) Airplanes on which one of the 

following has been incorporated in 

production: Airbus Modification 20065, 

20040, 24495, 24848, 24496, 21895, 21896, 

25905, 25907, 22601, 22602, 27187, 28319, 

28322, 28330, 28335, or 31797. 

(2) Airplanes on which one of the 

following has been incorporated in service: 

Airbus Service Bulletin A320–25–1132, 

A320–25–1133, A320–25–1145, A320–25– 

1175, A320–25–1177, A320–25–1276, A320– 

25–1278, A320–28–1134, or A320–28–1141. 

(h) New Modification 

Except for Model A319, A320, and A321 

airplanes on which both Airbus 

Modifications 32244 and 32245, or both 

Airbus Modifications 32316 and 32317, have 

been incorporated in production, and on 

which no YZ-latch replacements have been 

made since first flight: Within 20 months 

after the effective date of this AD, modify the 

attachment points of fixed YZ-latches of the 

CLS, having a part number (P/N) listed in 

table 1 to paragraph (h) of this AD, in both 

forward and aft lower deck cargo holds by 

adding spacer assemblies having P/N 

D2557232700000, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–25–1294, 

Revision 6, dated July 23, 2010. 

Accomplishing the actions in paragraph (h) 

of this AD terminates the requirements of 

paragraph (g) of this AD. 

TABLE 1 TO PARAGRAPH (h) OF THIS

AD—AFFECTED CLD YZ-LATCHES

Part No. 

D 255 7 2380 000 

D 255 7 2380 002 

D 255 7 2380 006 

D 255 7 2380 008 

D 255 7 2350 002 

TABLE 1 TO PARAGRAPH (h) OF THIS

AD—AFFECTED CLD YZLATCHES—Continued 

D 255 7 2350 004 

D 255 7 2350 006 

(i) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install, on the CLS of any 

airplane, a YZ-latch having a part number 

listed in table 1 to paragraph (h) of this AD, 

unless it has been modified in accordance 

with the requirements of paragraph (h) of this 

AD. 

(j) Credit for Previous Actions 

(1) This paragraph provides credit for the 

installation required by paragraph (g) of this 

AD, if the installation was performed before 

April 12, 2007 (the effective date of AD 

2007–05–13, Amendment 39–14974 (72 FR 

10348, March 8, 2007), using Airbus Service 

Bulletin A320–25–1294, dated March 14, 

2003; or Revision 1, dated March 27, 2006; 

which are not incorporated by reference in 

this AD. 

(2) This paragraph provides credit for the 

modification required by paragraph (h) of 

this AD, if the modification was performed 

before the effective date of this AD, using one 

of the following service information and the 

additional work is done, in accordance with 

the applicable instructions referenced as 

‘‘ADDITIONAL WORK’’ in the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–25–1294, 

Revision 6, dated July 23, 2010. 

(i) Airbus Service Bulletin A320–25–1294, 

dated March 14, 2003. 

(ii) Airbus Service Bulletin A320–25–1294, 

Revision 1, dated March 27, 2006. 

(iii) Airbus Service Bulletin A320–25– 

1294, Revision 2, dated September 5, 2006. 

(iv) Airbus Mandatory Service Bulletin 

A320–25–1294, Revision 3, dated January 22, 

2007. 

(v) Airbus Mandatory Service Bulletin 

A320–25–1294, Revision 4, dated March 13, 

2008. 

(vi) Airbus Mandatory Service Bulletin 

A320–25–1294, Revision 5, dated January 22, 

2009. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

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

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(l) Related Information 

(1) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2011– 

0077, dated May 5, 2011; and the following 

service information; for related information. 

(i)Airbus Service Bulletin A320–25–1294, 

Revision 06, dated July 23, 2010. 

(ii) Airbus Service Bulletin A320–25–1294, 

Revision 02, dated September 5, 2006. 

(2) For service information identified in 

this AD, contact Airbus SAS–EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. You may review copies of 

the referenced service information at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on 

September 26, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–24405 Filed 10–3–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1038; Directorate 

Identifier 2011–NM–166–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain Airbus Model 

A319 and A320 airplanes. The existing 

AD currently requires repetitive detailed 

inspections to detect cracks in the keel 

beam side panels, and repair if 


emcdonald on DSK67QTVN1PROD with PROPOSALS
60656 Federal Register / Vol. 77, No. 193 / Thursday, October 4, 2012 / Proposed Rules 

necessary. Since we issued that AD, we 

have received reports of access 

difficulties. Additionally, we have 

determined that the detailed inspection 

is not sufficient to mitigate the unsafe 

condition. This proposed AD would 

require repetitive eddy current 

inspections for cracking in the keel 

beam side panels, and corrective actions 

if necessary. We are proposing this AD 

to detect and correct fatigue cracks on 

the side panels of the keel beams, which 

could result in reduced structural 

integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by November 19, 

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, 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 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, WA 

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–2012–1038; Directorate Identifier 

2011–NM–166–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 June 16, 2004, we issued AD 

2004–13–06, Amendment 39–13688 (69 

FR 38818, June 29, 2004). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2004–13–06, 

Amendment 39–13688 (69 FR 38818, 

June 29, 2004), we have determined that 

the detailed inspection required by AD 

2004–13–06 is not sufficient to mitigate 

the unsafe condition. The European 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Community, has 

issued EASA Airworthiness Directive 

2011–0134, dated July 15, 2011 (referred 

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

an unsafe condition for the specified 

products. The MCAI states: 

During certification structural fatigue tests, 

several cases of structural damage (cracks) 

have been found on keel beam side panels. 

Cracks were observed on both sides of the 

keel beam around the rivets below the center 

wing box between frame (FR) 40 and FR 42, 

and in part of the area of the upper elliptical 

cut out forward of FR 41. 

This type of damage, if not detected and 

repaired, would adversely affect the 

structural integrity of the aeroplane. 

To address this unsafe condition, DGAC 

[Direction Ge ́ne ́rale de l’Aviation Civile] 

France issued AD 2003–146 [which 

corresponds to FAA AD 2004–13–06, 

Amendment 39–13688 (69 FR 38818, June 

29, 2004)] to require repetitive detailed 

inspections of those two areas and corrective 

actions, depending on findings. 

Prompted by reported access difficulties 

and to allow extension of the interval 

between two consecutive inspections, Airbus 

validated an Eddy current Non-Destructive 

Test (NDT) inspection to replace the detailed 

inspection. 

For the reasons described above, this 

[EASA] AD, which supersedes DGAC France 

AD 2003–146, requires repetitive Eddycurrent NDT inspections for cracks in the 

affected areas of the keel beam side panel 

below the center wing box and corrective 

actions [repair], depending on findings. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A320–53–1060, Revision 02, 

dated November 30, 2010. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This AD and the 

MCAI or Service Information 

Although the MCAI and Airbus 

Mandatory Service Bulletin A320–53– 

1060, Revision 02, dated November 30, 

2010, allow further flight after cracks are 

found during compliance with the 

proposed actions, this proposed AD 

would require repair before further 

flight if cracks are detected in the keel 

beam side panels. We have determined 

that, because of the safety implications 

and consequences associated with that 

cracking, any cracking in the keel beam 

side panels must be repaired before 

further flight. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 351 products of U.S. 

registry. 

We estimate that it would take about 

29 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 

$865,215, or $2,465 per product. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
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We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. We have 

no way of determining the number of 

products that may need these actions. 

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) 

2004–13–06, Amendment 39–13688 (69 

FR 38818, June 29, 2004), and adding 

the following new AD: 

Airbus: Docket No. FAA–2012–1038; 

Directorate Identifier 2011–NM–166–AD. 

(a) Comments Due Date 

We must receive comments by November 

19, 2012. 

(b) Affected ADs 

This AD supersedes AD 2004–13–06, 

Amendment 39–13688 (69 FR 38818, June 

29, 2004). 

(c) Applicability 

This AD applies to Airbus Model A319– 

111, –112, –113, –114, –115, –131, –132, and 

–133 airplanes; and Model A320–111, –211, 

–212, –214, –231, –232, and –233 airplanes; 

certificated in any category; all manufacturer 

serial numbers, except those having 

embodied Airbus modification 30355 in 

production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by reports of cracks 

on the side panels of the keel beams. We are 

issuing this AD to detect and correct fatigue 

cracks on the side panels of the keel beams, 

which could result in reduced structural 

integrity of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Repetitive Eddy Current Inspection 

At the applicable compliance time in 

paragraph (k)(1) or (k)(2) of this AD: Do an 

eddy current non-destructive test (NDT) 

inspection to detect cracks in the keel beam 

side panels at Area A and Area B, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–53–1060, Revision 02, dated 

November 30, 2010. Repeat the inspection 

thereafter at intervals not to exceed 12,000 

flight cycles or 26,700 flight hours, 

whichever occurs first. Area A is part of the 

area of the upper elliptical cut-out stringer 

(STGR) 42 on the left-hand (LH) and righthand (RH) side forward of Frame (FR) 41, and 

Area B is the area around the rivets on both 

sides of the keel beam side panel below the 

center wing box at STGR 42 on the LH and 

RH side between FR 40 and FR 42. 

(1) For airplanes that have been inspected 

as specified in Airworthiness Limitations 

Item (ALI) Task 533142–01–1, which was 

specified in the Airbus A319/A320/A321 ALI 

document up to Revision 05 inclusive; or as 

specified in Airbus A319/A320/A321 

Maintenance Review Board (MRB) Report up 

to Revision 08 inclusive; or as specified in 

the instructions of Airbus Service Bulletin 

A320–53–1060, dated June 19, 2002, or 

Revision 01, dated April 2, 2004: At the later 

of the times specified in paragraphs (g)(1)(i) 

and (g)(1)(ii) of this AD. 

(i) Within 4,300 flight cycles or 9,600 flight 

hours after the last inspection, whichever 

occurs first. 

(ii) Within 30 days after the effective date 

of this AD. 

(2) For airplanes other than those 

identified in paragraph (g)(1) of this AD: At 

the later of the times specified in paragraphs 

(g)(2)(i) and (g)(2)(ii) of this AD. 

(i) Prior to the accumulation of 24,200 total 

flight cycles, or 48,400 total flight hours, 

whichever occurs first. 

(ii) Within 30 days after the effective date 

of this AD. 

(h) Corrective Action for Cracking 

(1) If any crack is found in Area A during 

any inspection required by paragraph (g) of 

this AD: Before further flight, repair the 

affected area, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–53–1060, 

Revision 02, dated November 30, 2010. 

Accomplishing a repair terminates the 

repetitive inspections of Area A required by 

paragraph (g) of this AD for that side of the 

keel beam. 

(2) If any crack is found in Area B during 

any inspection required by this AD: Before 

further flight, repair the affected area 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). 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, 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, WA 

98057–3356; telephone (425) 227–1405; fax 

(425) 227–1149. Information may be emailed 

to: 9–ANM–116–AMOC–REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 


emcdonald on DSK67QTVN1PROD with PROPOSALS
60658 Federal Register / Vol. 77, No. 193 / Thursday, October 4, 2012 / Proposed Rules 

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. 

(j) Special Flight Permits 

Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the airplane can be repaired 

(if the operator elects to do so), provided the 

conditions in paragraph (n)(1), (n)(2), or 

(n)(3) of this AD are met. Areas A and B are 

defined in Airbus Mandatory Service 

Bulletin A320–53–1060, Revision 02, dated 

November 30, 2010. 

(1) No multiple cracks in Area A. 

(2) If there is a single crack in Area A, the 

length must be less than 20.0 millimeters 

(0.79 inch). 

(3) No cracking in Area B. 

(k) Related Information 

(1) Refer to MCAI EASA Airworthiness 

Directive 2011–0134, dated July 15, 2011; 

and Airbus Mandatory Service Bulletin 

A320–53–1060, Revision 02, dated November 

30, 2010; for related information. 

(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, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on 

September 26, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–24404 Filed 10–3–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1039; Directorate 

Identifier 2011–NM–275–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A319–112, –113, and 

–132 airplanes; Model A320–211, –212, 

–214, –231, and –232 airplanes; and 

Model A321–111 and –131 airplanes. 

This proposed AD was prompted by a 

report of two fatigue cracks on the lefthand and right-hand sides of the 

continuity fittings at the front 

windshield lower framing on a Model 

A319 airplane. This proposed AD would 

require a high frequency eddy current 

(HFEC) inspection for any cracking on 

the left-hand and right-hand sides of the 

windshield central lower node 

continuity fittings, and repair if 

necessary. We are proposing this AD to 

detect and correct cracking of the 

windshield central lower node 

continuity fittings, which could reduce 

the structural integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by November 19, 

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–2012–1039; Directorate Identifier 

2011–NM–275–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 2011–0231, 

dated December 9, 2011 (referred to 

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

unsafe condition for the specified 

products. The MCAI states: 

One operator reported finding two fatigue 

cracks on continuity fittings at left-hand (LH) 

and right-hand (RH) sides at the front 

windshield lower framing on an A319 

aeroplane on which Airbus modification 

(mod.) 22058 had been embodied in 

production. Airbus mod. 22058 (which is 

included in Airbus mod. 21999) was 

introduced to improve the fatigue strength of 

the windshield front framing by increasing 

the thickness of framing flanges adjacent to 

the concerned fittings. 

Further analyses have demonstrated that 

the damage tolerance and fatigue 

requirements of JAR 25.571 (b) are not met 

on aeroplanes in post-mod. 22058 

configuration. 

This condition, if not detected and 

corrected, could reduce the structural 

integrity of the affected aeroplanes. 

Required actions include an HFEC 

inspection for any cracking on the lefthand and right-hand sides of the 

windshield central lower node 

continuity fittings, and repair if 


emcdonald on DSK67QTVN1PROD with PROPOSALS