Federal Register / Vol. 77, No. 62 / Friday, March 30, 2012 / Rules and Regulations 19067 

(h) Parts Installation 

As of the effective date of this AD, no 

person may install any off-wing ramp slide 

having part number 4A3931–X on any 

airplane, unless the check required by 

paragraph (g) of this AD has been done and 

none of the conditions specified in paragraph 

(g) of this AD are found. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1138; 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 FAAapproved 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) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Airworthiness Directive 

2011–0017, dated February 3, 2011; and 

Airbus AOT A340–25A5191, dated January 

18, 2011; for related information. 

(k) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) of the 

following service information under 5 U.S.C. 

552(a) and 1 CFR part 51: 

(i) Airbus All Operators Telex A340– 

25A5191, dated January 18, 2011. The 

document number and date are identified 

only on the first page of the document. 

(2) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(3) You may review copies of the 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. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/

code_of_federal_regulations/ibr_locations.

html. 

Issued in Renton, Washington, on March 9, 

2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–7004 Filed 3–29–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0294; Directorate 

Identifier 2011–NM–047–AD; Amendment 

39–16992; AD 2012–06–11] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A321–131, –211, –212, 

and –231 airplanes. This AD requires a 

rotating probe inspection for cracking of 

the lower panel bore holes of the center 

wing box (CWB), and corrective actions 

if necessary. This AD was prompted by 

reports of incorrect installation of rib 

pads of the lower aft panel of the CWB 

due to poor clamping during drilling, 

and reports that metal chips trapped 

between panels and stiffeners could 

impact the fatigue life of CWB panels. 

We are issuing this AD to detect and 

correct cracking and damage in the bore 

holes of the rib pads of the lower 

forward and aft panels of the CWB 

which could result in reduced structural 

integrity of the wings. 

DATES: This AD becomes effective April 

16, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of April 16, 2012. 

We must receive comments on this 

AD by May 14, 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. 

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 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: 

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 2011–0035, 

dated March 2, 2011 (referred to after 

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

condition for the specified products. 

The MCAI states: 

During removal of one centre wing box 

(CWB) lower aft panel [due to reports of 

defects] during production, the following 

defects were found: 

—An excessive layer of sealant in between 

the lower panel and the rib pads, and 

—Small metal chips between the panel and 

rib pads. 

Investigations revealed that the metal chips 

trapped between parts (panels and stiffeners) 

have a possible impact on fatigue life of CWB 

panels. 

Consequently, cracks in the bore holes of 

the CWB lower panel may occur in service, 

thereby reducing the structural integrity of 

the aeroplane. 

For the reasons describe above, this AD 

requires a special detailed [rotating probe] 

inspection of CWB lower panel bore holes to 

detect any defect [damage] or crack and, 


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19068 Federal Register / Vol. 77, No. 62 / Friday, March 30, 2012 / Rules and Regulations 

depending on findings, associated corrective 

actions. 

The unsafe condition is potential 

cracking and damage in the bore holes 

of the rib pads of the lower forward and 

aft panels of the CWB which could 

result in reduced structural integrity of 

the wings. Required actions include a 

rotating probe inspection for cracking of 

the lower panel bore holes of the CWB, 

and corrective actions if necessary. The 

corrective actions include reinstalling 

new nominal fasteners or oversize 

fasteners. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A320–57–1120, Revision 01, 

including Appendices 01, 02, and 03, 

dated November 15, 2006. 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 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 issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

There are no products of this type 

currently registered in the United States. 

However, this rule is necessary to 

ensure that the described unsafe 

condition is addressed if any of these 

products are placed on the U.S. Register 

in the future. 

FAA’s Determination of the Effective 

Date 

Since there are currently no domestic 

operators of this product, notice and 

opportunity for public comment before 

issuing this AD are unnecessary. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2012–0294; 

Directorate Identifier 2011–NM–047– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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 adding 

the following new AD: 

2012–06–11 Airbus: Amendment 39–16992. 

Docket No. FAA–2012–0294; Directorate 

Identifier 2011–NM–047–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective April 16, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A321– 

131, –211, –212, and –231 airplanes; 

certificated in any category; manufacturer 

serial numbers 1293, 1299, 1307, 1333, 1356, 

and 1366. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57: Wings. 

(e) Reason 

This AD was prompted by reports of 

incorrect installation of rib pads of the lower 

aft panel of the center wing box (CWB) due 

to poor clamping during drilling, and reports 

that metal chips trapped between panels and 

stiffeners could impact the fatigue life of 

CWB panels. We are issuing this AD to detect 

and correct cracking and damage in the bore 

holes of the rib pads of the lower forward and 

aft panels of the CWB which could result in 

reduced structural integrity of the wings. 

(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) Rotating Probe Inspection 

Before the accumulation of 24,000 total 

flight cycles or 40,000 total flight hours, 

whichever occurs first, since first flight of the 

airplane: Do a rotating probe inspection for 

cracking of the bore holes of the rib pads in 

the lower forward and aft panels of the CWB, 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–57–1120, Revision 01, 

excluding Appendices 01 and 02, and 

including Appendix 03, dated November 15, 

2006. 


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Federal Register / Vol. 77, No. 62 / Friday, March 30, 2012 / Rules and Regulations 19069 

(h) Repair of Cracking 

If any cracking is found during any 

inspection required by paragraph (g) of this 

AD, before further flight, repair the crack 

according to a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, or 

EASA (or its delegated agent). 

(i) Oversizing Bore Holes and Installing 

Fasteners 

If no cracking is found during any 

inspection required by paragraph (g) of this 

AD, before further flight, oversize the holes 

to the next nominal diameter and install the 

rib pads with the new next nominal diameter 

fasteners, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–57–1120, 

Revision 01, excluding Appendices 01 and 

02, and including Appendix 03, dated 

November 15, 2006. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, ANM–116, 

International Branch, 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, Washington 98057– 

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

227–1149. 

Information may be emailed to: 9-ANM116-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. 

(k) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2011–0035, dated 

March 2, 2011; and Airbus Mandatory 

Service Bulletin A320–57–1120, Revision 01, 

dated November 15, 2006; for related 

information. 

(l) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) of the 

following service information under 5 U.S.C. 

552(a) and 1 CFR part 51: 

(i) Airbus Mandatory Service Bulletin 

A320–57–1120, Revision 01, excluding 

Appendices 01 and 02, and including 

Appendix 03, dated November 15, 2006. 

(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. 

(3) You may review copies of the 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. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/

code_of_federal_regulations/ibr_locations.

html. 

Issued in Renton, Washington, on March 8, 

2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–7007 Filed 3–29–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0223; Directorate 

Identifier 2010–NM–161–AD; Amendment 

39–17006; AD 2012–06–25] 

RIN 2120–AA64 

Airworthiness Directives; Goodrich 

Evacuation Systems Approved Under 

Technical Standard Order (TSO) TSO– 

C69b and Installed on Airbus Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

Goodrich Evacuation Systems approved 

under TSO TSO–C69b and installed on 

Model A330–200 and –300 series 

airplanes, Model A340–200 and –300 

series airplanes, and Model A340–500 

and –600 series airplanes. That AD 

currently requires inspecting to 

determine the part number of the 

pressure relief valves on the affected 

Goodrich evacuation systems, and 

corrective action if necessary. This new 

AD requires inspecting to determine the 

part number of the pressure relief valves 

on the affected Goodrich evacuation 

systems and replacing certain pressure 

relief valves, and adds airplanes to the 

applicability. This AD was prompted by 

reports that during workshop testing, 

certain pressure relief valves, which 

were required by the existing AD, did 

not seal and allowed the pressure in 

certain slides/rafts to fall below the 

minimum raft mode pressure for the 

unit. We are issuing this AD to prevent 

loss of pressure in the escape slides/ 

rafts after an emergency evacuation, 

which could result in inadequate 

buoyancy to support the raft’s passenger 

capacity during ditching and increase 

the chance for injury to raft passengers. 

DATES: This AD is effective May 4, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of May 4, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Goodrich 

Corporation, Aircraft Interior Products, 

ATTN: Technical Publications, 3414 

South Fifth Street, Phoenix, Arizona 

85040; phone: 602–243–2270; email: 

george.yribarren@goodrich.com; 

Internet: http://www.goodrich.com/ 

TechPubs. 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Tracy Ton, Aerospace Engineer, Cabin 

Safety/Mechanical and Environmental 

Systems Branch, ANM–150L, FAA, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; phone: 562– 

627–5352; fax: 562–627–5210; email: 

Tracy.Ton@faa.gov. 

SUPPLEMENTARY INFORMATION: 


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