Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Proposed Rules 52263 

(j) 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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1175; 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) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or BAE Systems (Operations) 

Limited’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0207, dated 

September 9, 2013, 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–2014–0621. 

(2) For service information identified in 

this AD, contact BAE Systems (Operations) 

Limited, Customer Information Department, 

Prestwick International Airport, Ayrshire, 

KA9 2RW, Scotland, United Kingdom; 

telephone +44 1292 675207; fax +44 1292 

675704; email RApublications@

baesystems.com; Internet http://

www.baesystems.com/Businesses/

RegionalAircraft/index.htm. 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 August 

25, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–20943 Filed 9–2–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0618; Directorate 

Identifier 2012–NM–171–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 

Airworthiness Directive (AD) 2008–06– 

18, for all Airbus Model A300 B4–600, 

B4–600R, and F4–600R series airplanes, 

and Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes) and Model 

A300 series airplanes. AD 2008–06–18 

currently requires repetitive inspections 

for any cracking of the wing lower skin 

panel and associated internal support 

structure, and if necessary, corrective 

actions such as modifying the lower 

panel inboard of rib 9 aft of the rear spar 

and repairing cracks. Since we issued 

AD 2008–06–18, we have received a 

report that information from an analysis 

and fleet survey show a need for 

reduced compliance times and intervals. 

This proposed AD would continue to 

require the existing requirements, and 

would reduce some compliance times. 

We are proposing this AD to detect and 

correct cracking, which could lead to 

reduced structural integrity of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by October 20, 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 

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; 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–2014–0618; Directorate Identifier 

2012–NM–171–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 March 7, 2008, we issued AD 

2008–06–18, Amendment 39–15430 (73 

FR 14670, March 19, 2008). AD 2008– 

06–18 requires actions intended to 

address an unsafe condition on all 

Airbus Model A300 B4–600, B4–600R, 

and F4–600R series airplanes, and 

Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes) and Model 

A300 series airplanes. 


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Since we issued AD 2008–06–18, 

Amendment 39–15430 (73 FR 14670, 

March 19, 2008), we have received a 

report that information from an analysis 

and fleet survey show a need for 

reduced compliance times and intervals. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0203, 

dated October 1, 2012 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus Model A300 B4–600, B4– 

600R, and F4–600R series airplanes, and 

Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes) and Model 

A300 series airplanes. The MCAI states: 

During routine maintenance, cracks were 

found in the wing bottom skin and in the 

associated internal support structure on an 

A300 aeroplane aft of the rear spar and 

inboard of rib 9. Initially, cracks were found 

in the skin only, starting from a fastener close 

to the forward outboard corner of access 

panel 575FB/675FB. Subsequently, cases 

were reported of cracks being found in the 

skin support strap and the stiffener. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

To address this unsafe condition, EASA 

issued AD 2006–0282 [http://

ad.easa.europa.eu/ad/2006-0282] [which 

corresponds with FAA AD 2008–06–18, 

Amendment 39–15430 (73 FR 14670, March 

19, 2008)] to require repetitive inspections of 

the wing lower skin panel and associated 

internal support structure aft of the rear spar 

and inboard of rib 9. 

Since that [EASA] AD was issued, the 

results of a fleet survey and updated Fatigue 

and Damage Tolerance analysis, which were 

performed in order to substantiate the second 

A300 and A300–600 Extended Service Goal 

(ESG2) exercise, revealed that the inspection 

threshold and interval had to be reduced to 

allow timely detection of cracks and the 

accomplishment of an applicable corrective 

action. 

Prompted by these findings, Airbus issued 

Revision 05 of Airbus Service Bulletin (SB) 

A300–57–0177 and Revision 07 of Airbus SB 

A300–57–6029. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2006–0282, which is superseded, but 

requires the accomplishment of those actions 

within reduced thresholds and intervals. 

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– 

0618. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A300–57–6029, Revision 08, dated April 

25, 2013. The compliance times for the 

initial inspections range approximately 

from 160 flight cycles or 270 flight 

hours, whichever occurs first, to 49,300 

flight cycles or 98,700 flight hours, 

whichever occurs first, depending on 

the model and configuration. The 

repetitive intervals range from 30 flight 

cycles or 40 flight hours, whichever 

occurs first, to 3,800 flight cycles or 

7,700 flight hours, whichever occurs 

first, depending on the model and 

configuration. 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. 

Changes to AD 2008–06–18, 

Amendment 39–15430 (73 FR 14670, 

March 19, 2008) 

This proposed AD would retain all 

requirements of AD 2008–06–18, 

Amendment 39–15430 (73 FR 14670, 

March 19, 2008). Since AD 2008–06–18 

was issued, the AD format has been 

revised, and certain paragraphs have 

been rearranged. As a result, the 

corresponding paragraph identifiers 

have changed in this proposed AD, as 

listed in the following table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in 

AD 2008–06–18, 

Amendment 39– 

15430 (73 FR 14670, 

March 19, 2008 

Corresponding 

requirement in this 

proposed AD 

paragraph (f) paragraph (g) 

Paragraph (f)(3) of AD 2008–06–18, 

Amendment 39–15430 (73 FR 14670, 

March 19, 2008), contains a 

typographical error. That error resulted 

in a reference to paragraph ‘‘(e)(f)(ii)’’ of 

AD 2008–06–18. The correct reference is 

to paragraph (f)(3)(ii) of AD 2008–06–18. 

Since the AD format has been revised 

and certain paragraphs have been 

rearranged, the reference is now to 

paragraph (g)(3)(ii) of the proposed AD. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This Proposed AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 

FAA develops an AD based on a foreign 

authority’s AD. 

The MCAI or referenced service 

information in an FAA AD often directs 

the owner/operator to contact the 

manufacturer for corrective actions, 

such as a repair. Briefly, the Airworthy 

Product paragraph allowed owners/

operators to use corrective actions 

provided by the manufacturer if those 

actions were FAA-approved. In 

addition, the paragraph stated that any 

actions approved by the State of Design 

Authority (or its delegated agent) are 

considered to be FAA-approved. 

In an NPRM having Directorate 

Identifier 2012–NM–101–AD (78 FR 

78285, December 26, 2013), we 

proposed to prevent the use of repairs 

that were not specifically developed to 

correct the unsafe condition, by 

requiring that the repair approval 

provided by the State of Design 

Authority or its delegated agent 

specifically refer to the FAA AD. This 

change was 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 proposed to 

change the phrase ‘‘its delegated agent’’ 

to include a design approval holder 

(DAH) with State of Design Authority 

design organization approval (DOA), as 

applicable, to refer to a DAH authorized 

to approve required repairs for the 

proposed AD. 

One commenter to the NPRM having 

Directorate Identifier 2012–NM–101–AD 

(78 FR 78285, December 26, 2013) stated 

the following: ‘‘The proposed wording, 

being specific to repairs, eliminates the 

interpretation that Airbus messages are 

acceptable for approving minor 

deviations (corrective actions) needed 

during accomplishment of an AD 

mandated Airbus service bulletin.’’ 

This comment has made the FAA 

aware that some operators have 

misunderstood or misinterpreted the 

Airworthy Product paragraph to allow 

the owner/operator to use messages 

provided by the manufacturer as 

approval of deviations during the 

accomplishment of an AD-mandated 

action. The Airworthy Product 

paragraph does not approve messages or 

other information provided by the 

manufacturer for deviations to the 

requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 


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requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed the 

paragraph and retitled it ‘‘Contacting the 

Manufacturer.’’ This paragraph now 

clarifies that for any requirement in this 

proposed AD to obtain corrective 

actions from a manufacturer, the actions 

must be accomplished using a method 

approved by the FAA, the European 

Aviation Safety Agency (EASA), or 

Airbus’s EASA DOA. 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DOA, the approval must include 

the DOA-authorized signature. The DOA 

signature indicates that the data and 

information contained in the document 

are EASA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that do not contain the 

DOA-authorized signature approval are 

not EASA-approved, unless EASA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

We also have decided not to include 

a generic reference to either the 

‘‘delegated agent’’ or ‘‘design approval 

holder (DAH) with State of Design 

Authority design organization 

approval,’’ but instead we have 

provided the specific delegation 

approval granted by the State of Design 

Authority for the DAH throughout this 

proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 162 airplanes of U.S. registry. 

The actions that are required by AD 

2008–06–18, Amendment 39–15430 (73 

FR 14670, March 19, 2008), and retained 

in this proposed AD take about 2 workhours per product, at an average labor 

rate of $85 per work-hour. Based on 

these figures, the estimated cost of the 

actions that are required by AD 2008– 

06–18 is $170 per product. 

We also estimate that it would take 

about 2 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $27,540, or $170 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 12 work-hours and require parts 

costing $10,000, for a cost of $11,020 

per product. We have no way of 

determining the number of aircraft that 

might need these actions. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to 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 control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is 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. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2008–06–18, Amendment 39–15430 (73 

FR 14670, March 19, 2008), and adding 

the following new AD: 

Airbus: Docket No. FAA–2014–0618; 

Directorate Identifier 2012–NM–171–AD. 

(a) Comments Due Date 

We must receive comments by October 20, 

2014. 


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(b) Affected ADs 

This AD replaces AD 2008–06–18, 

Amendment 39–15430 (73 FR 14670, March 

19, 2008). 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) through (c)(5) of this AD, 

certificated in any category, all certified 

models, all serial numbers. 

(1) Airbus Model A300 B2–1A, B2–1C, 

B2K–3C, B2–203, B4–2C, B4–103, and B4– 

203 airplanes. 

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

B4–620, and B4–622 airplanes. 

(3) Airbus Model A300 B4–605R and B4– 

622R airplanes. 

(4) Airbus Model A300 F4–605R and F4– 

622R airplanes. 

(5) Airbus Model A300 C4–605R Variant F 

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by a report that 

information from an analysis and fleet survey 

show a need for reduced compliance times 

and intervals. We are issuing this AD to 

detect and correct cracking, which could lead 

to 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) Retained Actions and Compliance Times 

With Revised Service Information 

This paragraph restates the requirements of 

paragraph (f) of AD 2008–06–18, Amendment 

39–15430 (73 FR 14670, March 19, 2008), 

with revised service information. Unless 

already done, do the following actions. 

(1) Except as provided by paragraphs 

(g)(1)(i), (g)(1)(ii), (g)(1)(iii), (g)(1)(iv), and (h) 

of this AD: At the threshold specified in 

paragraph 1.E.(2) of Airbus Service Bulletin 

A300–57–0177, Revision 05, dated March 23, 

2007 (for Model A300 series airplanes); 

Airbus Service Bulletin A300–57–6029, 

Revision 06, dated March 23, 2007 (for Model 

A300–600 series airplanes); or Airbus Service 

Bulletin A300–57–6029, Revision 08, dated 

April 25, 2013 (for Model A300–600 series 

airplanes); as applicable; perform the 

inspection of the wing lower skin panel and 

associated internal support structure aft of 

the rear spar and inboard of rib 9 and apply 

applicable corrective measures in accordance 

with Airbus Service Bulletin A300–57–0177, 

Revision 05, dated March 23, 2007 (for Model 

A300 series airplanes); or Airbus Service 

Bulletin A300–57–6029, Revision 06, dated 

March 23, 2007 (for Model A300–600 series 

airplanes); or Airbus Service Bulletin A300– 

57–6029, Revision 08, dated April 25, 2013 

(for Model A300–600 series airplanes); as 

applicable. All applicable corrective 

measures must be done at the applicable 

times specified in paragraph 1.E.(2) and the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–0177, Revision 05, 

dated March 23, 2007 (for Model A300 series 

airplanes); Airbus Service Bulletin A300–57– 

6029, Revision 06, dated March 23, 2007 (for 

Model A300–600 series airplanes); or Airbus 

Service Bulletin A300–57–6029, Revision 08, 

dated April 25, 2013 (for Model A300–600 

series airplanes); as applicable. 

Accomplishing the requirements of 

paragraph (h) of this AD terminates the 

requirements of this paragraph for Model 

A300–600 airplanes. 

(i) Where the tables in paragraph 1.E.(2), 

‘‘Accomplishment Timescale,’’ of Airbus 

Service Bulletin A300–57–0177, Revision 05, 

dated March 23, 2007; A300–57–6029, 

Revision 06, dated March 23, 2007; specify 

a grace period for doing the actions, this AD 

requires that the actions be done within the 

specified grace period relative to April 23, 

2008 (the effective date of AD 2008–06–18, 

Amendment 39–15430 (73 FR 14670, March 

19, 2008)). 

(ii) Where the tables in paragraph 

1.E.(2)(e), ‘‘Config 04,’’ of Airbus Service 

Bulletin A300–57–0177, Revision 05, dated 

March 23, 2007, specify an inspection 

interval but not an initial threshold, this AD 

requires that the actions be done within the 

specified interval after inspecting in 

accordance with Table 1A or 1B, as 

applicable, for Configuration 01 airplanes 

described in the service bulletin and 

thereafter at the inspection interval specified 

in the tables in paragraph 1.E.(2)(e), ‘‘Config 

04,’’ of Airbus Service Bulletin A300–57– 

0177, Revision 05, dated March 23, 2007. 

(iii) Where the tables in paragraph 

1.E.(2)(f), ‘‘Config 05,’’ of Airbus Service 

Bulletin A300–57–6029, Revision 06, dated 

March 23, 2007, specify an inspection 

interval but not an initial threshold, this AD 

requires that the actions be done within the 

specified interval after inspecting in 

accordance with Table 1A, or 1B, as 

applicable, for configuration 01 of Airbus 

Service Bulletin A300–57–6029, Revision 06, 

dated March 23, 2007, and thereafter at the 

inspection interval specified in the tables in 

paragraph 1.E.(2)(f), ‘‘Config 05,’’ of Airbus 

Service Bulletin A300–57–6029, Revision 06, 

dated March 23, 2007. 

(iv) All crack lengths specified in Airbus 

Service Bulletin A300–57–0177, Revision 05, 

dated March 23, 2007; and A300–57–6029, 

Revision 06, dated March 23, 2007, are 

considered ‘‘not to exceed’’ lengths. 

(2) Repeat the inspection at the intervals 

in, and according to the instructions defined 

in, Airbus Service Bulletin A300–57–0177, 

Revision 05, dated March 23, 2007 (for Model 

A300 series airplanes); Airbus Service 

Bulletin A300–57–6029, Revision 06, dated 

March 23, 2007 (for Model A300–600 series 

airplanes); or Airbus Service Bulletin A300– 

57–6029, Revision 08, dated April 25, 2013 

(for Model A300–600 series airplanes); as 

applicable; except where Airbus Service 

Bulletin A300–57–0177, Revision 05, dated 

March 23, 2007, specifies repetitive 

inspections for cracking if Airbus Service 

Bulletin A300–57–022 has not been 

embodied, this AD requires doing repetitive 

inspections for cracking if Airbus Service 

Bulletin A300–57–0222 (modification 

11178H5410) has not been embodied. 

(3) Report to Airbus the first inspection 

results, whatever they may be, at the 

applicable time specified in paragraph 

(g)(3)(i) or (g)(3)(ii) of this AD. 

(i) If the inspection was done after April 

23, 2008 (the effective date of AD 2008–06– 

18, Amendment 39–15430 (73 FR 14670, 

March 19, 2008)), submit the report within 30 

days after the inspection. 

(ii) If the inspection was accomplished 

prior to April 23, 2008 (the effective date of 

AD 2008–06–18, Amendment 39–15430 (73 

FR 14670, March 19, 2008)), submit the 

report within 30 days after April 23, 2008. 

(h) New Requirement of This AD: New 

Compliance Times for Model A300–600 

Airplanes 

For Model A300–600 airplanes, do the 

actions specified in paragraphs (h)(1) through 

(h)(3) of this AD at the applicable times 

specified in those paragraphs. 

(1) Except as provided by paragraphs 

(h)(1)(i) and (h)(1)(ii) of this AD: Within the 

compliance times specified in Airbus Service 

Bulletin A300–57–6029, Revision 08, dated 

April 25, 2013, perform the inspection of the 

wing lower skin panels and associated 

internal support structures aft of the rear spar 

and inboard of rib 9, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6029, Revision 08, 

dated April 25, 2013. Thereafter, repeat these 

inspections at intervals specified in Airbus 

Service Bulletin A300–57–6029, Revision 08, 

dated April 25, 2013. Accomplishment of the 

actions required by this paragraph terminates 

the requirements of paragraph (g) of this AD 

for Model A300–600 airplanes. 

(i) Where the tables in paragraph 1.E.(2), 

‘‘Accomplishment Timescale,’’ of Airbus 

Service Bulletin A300–57–6029, Revision 08, 

dated April 25, 2013, specify a grace period 

for doing the actions for airplanes that have 

exceeded the thresholds, this AD requires, for 

all airplanes, that the actions be done within 

the specified grace period after the effective 

date of this AD or before the specified 

thresholds, whichever occurs later. 

(ii) Where Airbus Service Bulletin A300– 

57–6029, Revision 08, dated April 25, 2013, 

specifies to ‘‘contact Airbus’’ before further 

flight, this AD requires repairing using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or European 

Aviation Safety Agency (EASA); or Airbus’s 

EASA Design Organization Approval (DOA); 

and accomplishing those actions before 

further flight. If approved by the DOA, the 

approval must include the DOA-authorized 

signature. 

(2) If, during any inspection as required by 

paragraph (h)(1) of this AD, discrepancies are 

detected, before next flight, accomplish the 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A300–57–6029, 

Revision 08, dated April 25, 2013. 

(3) Corrective actions, as required by 

paragraph (h)(2) of this AD, do not constitute 

terminating action for the repetitive 

inspection requirements of paragraph (h)(1) 

of this AD. 

(i) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraph (g) of this AD, 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Proposed Rules 52267 

if those actions were performed before April 

23, 2008 (the effective date of AD 2008–06– 

18, Amendment 39–15430 (73 FR 14670, 

March 19, 2008)), using the applicable 

service information identified in paragraphs 

(i)(1)(i) through (i)(1)(iv) of this AD, which 

are not incorporated by reference by this AD. 

(i) Airbus Service Bulletin A300–57–0177, 

Revision 03, dated May 29, 2006. 

(ii) Airbus Service Bulletin A300–57–0177, 

Revision 04, dated January 5, 2007. 

(iii) Airbus Service Bulletin A300–57– 

6029, Revision 04, dated May 29, 2006. 

(iv) Airbus Service Bulletin A300–57– 

6029, Revision 05, dated October 23, 2006. 

(2) This paragraph provides credit for 

actions required by paragraph (g) or (h) of 

this AD, if those actions were performed 

before the effective date of this AD, using 

Airbus Service Bulletin A300–57–6029, 

Revision 07, dated June 6, 2011, which is not 

incorporated by reference by this AD. 

(j) 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: 

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. AMOCs 

approved previously for AD 2008–06–18, 

Amendment 39–15430 (73 FR 14670, March 

19, 2008) are considered acceptable for this 

AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2012–0203, dated October 1, 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–2014–0618. 

(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 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 August 

23, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–20917 Filed 9–2–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0589; Directorate 

Identifier 2014–NM–069–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 A318–111 and –112 

airplanes, Model A319, A320, and A321 

series airplanes. This proposed AD was 

prompted by reports of cracks on the 

forward corner fittings of engine pylon 

aft secondary structures. This proposed 

AD would require repetitive inspections 

of certain forward corner fittings of the 

pylon aft secondary structures, and 

corrective actions if necessary. This 

proposed AD also provides optional 

terminating action for the repetitive 

inspections. We are proposing this AD 

to detect and correct detachment of the 

lower fairing attachment and/or loss of 

the aft fixed fairing with the movable 

fairing from the airplane in flight, which 

could result in damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by October 20, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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—EIAS, 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– 

0589; 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 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. 


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