Federal Register / Vol. 79, No. 40 / Friday, February 28, 2014 / Proposed Rules 11355 

Revision 1, dated October 25, 2007, including 

Appendix 1, dated December 12, 2006, is 

acceptable for compliance with the 

replacement required by paragraph (l) of this 

AD, provided the installation is 

accomplished within the compliance time 

specified in paragraph (l) of this AD; and, 

except for airplanes that comply with 

paragraph (m) of this AD, provided the 

installation is accomplished within the 

compliance time specified in paragraph (m) 

of this AD. 

(o) New Requirement: Concurrent 

Modification 

Prior to, or concurrently with, the 

installation of the NLG unit required by 

paragraph (l) of this AD or the optional 

installation specified in paragraph (n) of this 

AD, modify the nose landing gear (NLG) 

bracket, in accordance with the 

Accomplishment Instructions of Fokker 

Services Bulletin SBF100–53–074, Revision 

1, dated October 25, 2007. 

(p) New Terminating Actions 

Accomplishing the replacement specified 

in paragraph (l) of this AD or the installation 

specified in paragraph (n) of this AD 

terminates the repetitive eddy current or dye 

penetrant inspections required by paragraphs 

(i) and (m)(1) of this AD. 

(q) New Parts Installation Prohibition 

(1) For airplanes equipped with MessierDowty nose landing gear (NLG) having part 

number (P/N) 201071001 or 201071002, on 

which a main fitting subassembly (MFSA) 

having P/N 201071200, 201071228, 

201071248, or 201071249 is installed: As of 

October 3, 2000 (the effective date of AD 

2000–17–03, Amendment 39–11876 (65 FR 

52298, August 29, 2000), and until the 

effective date of this AD: No person may 

install an NLG having P/N 201071001 or 

201071002 unless the installed MFSA has 

been inspected, by means of an eddy current 

or dye penetrant inspection, and corrected in 

accordance with paragraph (i) of this AD. 

(2) For all airplanes: As of the effective 

date of this AD, no person may install an 

NLG having P/N 201071001 or 201071002 on 

any airplane. 

(r) Credit for Previous Actions 

This paragraph provides credit for the 

replacement required by paragraph (l) of this 

AD, if those actions were performed before 

the effective date of this AD using Fokker 

Services B.V. Service Bulletin SBF 100–32– 

119, dated January 31, 2000, provided part 

number 201071003 or 201071004 nose gear 

has been installed. 

(s) 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: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; 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, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or the DAH with a State 

of Design Authority’s design organization 

approval). You are required to ensure the 

product is airworthy before it is returned to 

service. 

(3) Reporting Requirements: 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. 

(t) Related Information 

(1) Refer to MCAI EASA Airworthiness 

Directive 2012–0002R1, dated March 30, 

2012, for related information. This MCAI 

may be found in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2014–0062. 

(2) For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 1357, 

2130 EL Hoofddorp, the Netherlands; 

telephone +31 (0)88–6280–350; fax +31 

(0)88–6280–111; email technicalservices@

fokker.com; Internet http://

www.myfokkerfleet.com. You may view this 

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 February 

14, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–04499 Filed 2–27–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0123; Directorate 

Identifier 2013–NM–040–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 A300 B4–601, B4–603, 

B4–620, B4–622, -B4–605R, B4–622R, 

-F4–605R, F4–622R, and -C4–605R 

Variant F airplanes; and Model A310– 

203, –204, –221, –222, –304, –322, –324, 

and –325 airplanes. This proposed AD 

was prompted by a report of inner skin 

disbonding damage on a rudder. This 

proposed AD would require repetitive 

ultrasonic inspections for disbonding of 

certain rudders; an elasticity of laminate 

checker inspection; a woodpecker or tap 

test inspection; venting the core, if 

necessary; and repairing, if necessary. 

We are proposing this AD to detect and 

correct rudder disbonding, which could 

affect the structural integrity of the 

rudder. 

DATES: We must receive comments on 

this proposed AD by April 14, 2014. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS, 


emcdonald on DSK67QTVN1PROD with PROPOSALS
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Airworthiness Office—EAW, 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 view this 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 by searching for 

and locating Docket No. FAA–2014– 

0123; 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–2125; 

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–2014–0123; Directorate Identifier 

2013–NM–040–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 2013–0039, 

dated February 26, 2013 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

One A310 operator found substantial inner 

skin disbonding damage on a rudder that was 

previously inspected in accordance with the 

instructions of Airbus Service Bulletin (SB) 

A310–55–2044. The results of the subsequent 

investigation revealed that the most probable 

cause of this damage was a blunt impact with 

no visible damage from outside during the 

rudder handling. Damage like this might 

grow with pressure variation during groundair-ground cycles, and tests performed with 

other rudders showed a rapid propagation of 

damage during artificial pressure cycling. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the rudder. 

To address this potential unsafe condition, 

Airbus issued Alert Operators Transmission 

(AOT) A55W002–12 [dated December 13, 

2012], pending Aircraft Maintenance Manual 

(AMM) 27–21–21 PB401 revision to update 

rudder handling procedures. 

For the reasons described above, this 

[EASA] AD requires ultrasonic test (UT) 

inspections of the affected rudders to detect 

signs of disbonding and, depending on 

findings, accomplishment of applicable 

corrective action(s). 

Required actions also include an 

elasticity of laminate checker inspection 

to detect external and internal 

disbonding, and a woodpecker or tap 

test inspection to detect external 

disbonding. You may examine the 

MCAI in the AD docket on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2014–* * *. 

Relevant Service Information 

Airbus has issued Alert Operators 

Transmission A55W002–12, dated 

December 13, 2012. 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. 

Repair Approvals 

In many FAA transport ADs, when 

the service information specifies to 

contact the manufacturer for further 

instructions if certain discrepancies are 

found, we typically include in the FAA 

AD a requirement to accomplish the 

action using a method approved by 

either the FAA or the State of Design 

Authority (or its delegated agent). 

We have recently been notified that 

certain laws in other countries do not 

allow such delegation of authority, but 

some countries do recognize design 

approval organizations. In addition, we 

have become aware that some U.S. 

operators have used repair instructions 

that were previously approved by a 

State of Design Authority or a Design 

Approval Holder (DAH) as a method of 

compliance with this provision in FAA 

ADs. Frequently, in these cases, the 

previously approved repair instructions 

come from the airplane structural repair 

manual or DAH repair approval 

statements that were not specifically 

developed to address the unsafe 

condition corrected by the AD. Using 

repair instructions that were not 

specifically approved for a particular 

AD creates the potential for doing 

repairs that were not developed to 

address the unsafe condition identified 

by the MCAI AD, the FAA AD, or the 

applicable service information, which 

could result in the unsafe condition not 

being fully corrected. 

To prevent the use of repairs that 

were not specifically developed to 

correct the unsafe condition, certain 

requirements of this proposed AD 

specify that the repair approval 

specifically refer to the FAA AD. This 

change is intended to clarify the method 

of compliance and to provide operators 

with better visibility of repairs that are 

specifically developed and approved to 

correct the unsafe condition. In 

addition, we use the phrase ‘‘its 

delegated agent, or the DAH with the 

State of Design Authority’s design 

organization approval, as applicable’’ in 

this proposed AD to refer to a DAH 

authorized to approve certain required 

repairs for this proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 89 airplanes of U.S. registry. We 

also estimate that it would take about 10 

work-hours per product to comply with 

the basic requirements of this proposed 

AD. The average labor rate is $85 per 

work-hour. Required parts would cost 

about $0 per product. Based on these 

figures, we estimate the cost of this 

proposed AD on U.S. operators to be 

$75,650, or $850 per product. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
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We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this proposed AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. Amend § 39.13 by adding the 

following new AD: 

Airbus: Docket No. FAA–2014–0123; 

Directorate Identifier 2013–NM–040–AD. 

(a) Comments Due Date 

We must receive comments by April 14, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) and (c)(2) of this AD, 

except airplanes on which modification 

08827 has been embodied in production. 

(1) Airbus Model A300 B4–601, B4–603, 

B4–620, B4–622, –B4–605R, B4–622R, –F4– 

605R, F4–622R, and –C4–605R Variant F 

airplanes, certificated in any category, all 

manufacturer serial numbers. 

(2) Airbus Model A310–203, –204, –221, 

–222, –304, –322, –324, and –325 airplanes, 

certificated in any category, all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 55; Stabilizers. 

(e) Reason 

This AD was prompted by a report of inner 

skin disbonding damage on a rudder. We are 

issuing this AD to detect and correct rudder 

disbonding, which could affect the structural 

integrity of the rudder. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Identification of Part Number 

Within 3 months after the effective date of 

this AD, identify the rudder assembly part 

number (P/N) and serial number (S/N), in 

accordance with the Accomplishment 

Instructions of Airbus Alert Operator 

Transmission (AOT) A55W002–12, dated 

December 13, 2012. If the part number or 

serial number cannot be determined, before 

further flight, identify the part number and 

serial number in accordance with a method 

approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA (or its 

delegated agent, or by the Design Approval 

Holder with EASA design organization 

approval, as applicable). For an identification 

method to be approved, the identification 

method approval must specifically refer to 

this AD. 

(h) Inspections 

If a rudder assembly part number starting 

with A55471500 is found during the 

inspection required by paragraph (g) of this 

AD, before further flight, do an ultrasonic 

(UT) inspection for damage (e.g., disbonding 

and liquid ingress) of the rudder side panel 

along the Z-profile and in the booster area, 

in accordance with Airbus Alert Operator 

Transmission (AOT) A55W002–12, dated 

December 13, 2012. If any damage is found, 

before further flight, do the inspections to 

confirm disbonding damage as specified in 

paragraph (h)(1) and (h)(2) of this AD, in 

accordance with Airbus Alert Operator 

Transmission (AOT) A55W002–12, dated 

December 13, 2012. 

(1) Do an elasticity of laminate checker 

inspection to detect external and internal 

disbonding of the rudder side panel along the 

Z-profile and in the booster area. 

(2) Do a woodpecker or tap test inspection 

to detect external disbonding of the rudder 

side panel along the Z-profile and in the 

booster area. 

(i) Repair 

(1) If any disbonding is confirmed during 

any inspection required by paragraphs (h)(1) 

and (h)(2) of this AD, before further flight, 

repair as specified in paragraphs (i)(1)(i) and 

(i)(1)(ii) of this AD, as applicable. 

(i) If disbonding is less than or equal to 50 

millimeters (mm) in width and less than or 

equal to 150 mm in length, before further 

flight, vent the core, using a method 

approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA (or its 

delegated agent, or by the Design Approval 

Holder with EASA design organization 

approval, as applicable). Within 100 flight 

cycles after the UT inspection specified in 

paragraph (h) of this AD is done, repair using 

a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA (or its 

delegated agent, or the Design Approval 

Holder with EASA’s design organization 

approval, as applicable). For a repair method 

to be approved, the repair approval must 

specifically refer to this AD. 

(ii) If disbonding is greater than 50 mm in 

width or greater than 150 mm in length, 

before further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or EASA (or its delegated 

agent, or the Design Approval Holder with 

EASA’s design organization approval, as 

applicable). For a repair method to be 

approved, the repair approval must 

specifically refer to this AD. 

(2) If liquid ingress is confirmed during 

any inspection required by paragraphs (h)(1) 

and (h)(2), before further flight, repair, using 

a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA (or its 

delegated agent, or the Design Approval 

Holder with EASA’s design organization 

approval, as applicable). For a repair method 

to be approved, the repair approval must 

specifically refer to this AD. 

(j) Inspection After Re-installation 

If any rudder has been inspected as 

specified in Airbus Service Bulletin A300– 

55–6043, Revision 01, dated December 3, 

2007; or A310–55–2044, Revision 01, dated 


emcdonald on DSK67QTVN1PROD with PROPOSALS
11358 Federal Register / Vol. 79, No. 40 / Friday, February 28, 2014 / Proposed Rules 

December 3, 2007; as applicable; and has 

been removed and re-installed on any 

airplane after this inspection, that rudder 

must be re-inspected as required by 

paragraph (g) of this AD; and all applicable 

actions required by paragraphs (h) and (i) of 

this AD must be done. 

(k) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install, on any airplane, a rudder 

assembly having a part number starting with 

A55471500, unless it has been inspected as 

required by paragraph (h) of this AD, and all 

applicable actions required by paragraph (i) 

of this AD have been done. 

(l) 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–2125; 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, use these actions if they are 

FAA approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or the Design Approval 

Holder with a State of Design Authority’s 

design organization approval, as applicable). 

You are required to ensure the product is 

airworthy before it is returned to service. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0039, dated 

February 26, 2013; for related information, 

which can be found in the AD docket on the 

Internet at http://www.regulations.gov. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 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 view this 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 February 

14, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–04495 Filed 2–27–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0124; Directorate 

Identifier 2012–NM–197–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Airbus Model A300 series airplanes. 

This proposed AD was prompted by an 

analysis of the impacts of extended 

service goal activities on Airbus Model 

A300 series airplanes. This proposed 

AD would require revising the 

maintenance program. We are proposing 

this AD to prevent failure of flight 

critical systems. 

DATES: We must receive comments on 

this proposed AD by April 14, 2014. 

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 by searching for 

and locating Docket No. FAA–2014– 

0124; or in person at the Docket 

Management Facility 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–2125; 

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–2014–0124; Directorate Identifier 

2012–NM–197–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 2012–0233, 

dated November 7, 2012 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

The results of the Extended Service Goal 

(ESG) exercise for A300 series aeroplanes 

(75,000 flight hours (FH) or 48,000 flight 

cycles (FC), whichever occurs first) identified 

certain operational tests as Airworthiness 

Limitation Items (ALI), necessary to ensure 

the safety objectives for aeroplanes which 

have accumulated or exceeded 60,000 FH. 

These ALI are not fully new, since all nine 

tasks derive from existing Maintenance 

Planning Document (MPD) tasks. 

Consequently, the intervals of those nine 

tasks can no longer be escalated or retained 

at an interval higher than that specified in 

this [EASA] AD for each task. 

Failure to comply with these tasks within 

the established maximum intervals could be 

detrimental to the safety of the affected 

aeroplanes. 


emcdonald on DSK67QTVN1PROD with PROPOSALS