52260 Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Proposed Rules 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0621; Directorate 

Identifier 2013–NM–201–AD] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited 

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 BAE 

Systems (Operations) Limited Model 

BAe 146 series airplanes, and Model 

Avro 146–RJ series airplanes. This 

proposed AD was prompted by a report 

of a pressurization problem on an 

airplane during climb-out; a subsequent 

investigation showed a crack in the 

fuselage skin. This proposed AD would 

require repetitive external eddy current 

inspections on the aft skin lap joints of 

the rear fuselage for cracking, corrosion, 

and other defects, and repair if 

necessary. We are proposing this AD to 

detect and correct cracking, corrosion, 

and other defects, which could affect 

the 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 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. 

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– 

0621; 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: 

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. 

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–2014–0621; Directorate Identifier 

2013–NM–201–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 2013–0207, 

dated September 9, 2013 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all BAE Systems (Operations) 

Limited Model BAe 146 series airplanes, 

and Model Avro 146–RJ series airplanes. 

The MCAI states: 

In 2012, a pressurisation problem occurred 

on an AVRO 146–RJ100 aeroplane during 

climb-out. Subsequent investigation results 

identified a 42.87 inch (1089 mm) long crack 

in the fuselage skin in the rear fuselage drum, 

near the rear passenger door. The skin crack 

had initiated in the step of the skin land 

adjacent to a lap joint. In addition to the skin 

crack, cracks were found in Frames 41X and 

42. 

This condition, if not detected and 

corrected, could lead to degradation of the 

structural integrity of the aeroplane. 

Prompted by this finding, BAE Systems 

(Operations) Ltd issued Inspection Service 

Bulletin (ISB) 53–239, providing instructions 

to inspect the internal area of the rear 

fuselage drum for cracks, corrosion and any 

other defects and EASA issued AD 2012– 

0178 [http://ad.easa.europa.eu/blob/easa_

ad_2012_0178_Superseded.pdf/AD_2012- 

0178_1] which required accomplishment of a 

one-time inspection of the affected fuselage 

area and, depending on findings, repair of 

cracked structural items. Following the 

issuance of that [EASA] AD, some new 

information on additional damage found on 

the aeroplane that had the pressurisation 

problem resulted in a further review of the 

cracking event. This review concluded that 

the event was more serious than previously 

considered and that the compliance time 

must be reduced in order to mitigate the risk 

of cracking on other aeroplanes. As a result, 

EASA issued AD 2012–0184 [http://

ad.easa.europa.eu/blob/easa_ad_2012_0184_

superseded.pdf/AD_2012-0184_1] which 

superseded EASA AD 2012–0178. 

After analysing the responses to EASA AD 

2012–0184, which covered the initial 

inspection of stringer 30, left hand (LH) and 

right hand (RH), BAE Systems (Operations) 

Ltd also assessed the similar design features 

at other skin lands in the rear fuselage drum, 

namely at stringer 2 right and stringers 11 

and 18, LH and RH. As a result, they 

determined that inspections at the other 

stringers would be required and also that 

repeat inspections of all these stringers 

would be necessary. Consequently, BAE 

Systems (Operations) Ltd ISB.53–239 

Revision 1 and 2 were issued to include these 

new inspections. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2012–0184, which is superseded, and 

requires accomplishment of additional 

inspections of the affected fuselage area, 

including repetitive inspections, and 

depending on findings, repair of cracked 

structural items. 

The required actions include repetitive 

external eddy current inspections on the 

aft skin lap joints of the rear fuselage for 

cracking, corrosion, and other defects, 

and repair if necessary. 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– 

0621. 

Relevant Service Information 

BAE Systems (Operations) Limited 

has issued Inspection Service Bulletin 


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Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Proposed Rules 52261 

53–239, Revision 2, dated July 15, 2013. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

EASA AD 2013–0207, dated 

September 9, 2013, specifies that, if any 

cracking, corrosion, or any other 

irregularity is detected during any 

inspection required by paragraph (1) of 

the EASA AD, owners/operators must 

contact BAE Systems (Operations) 

Limited before further flight for 

approved repair instructions, and 

within the compliance time specified in 

those instructions, must accomplish the 

repair accordingly. This AD requires 

that if any cracking, corrosion, or any 

other irregularity is found during any 

inspection, owners/operators must 

repair before further flight using a 

method approved by the Manager, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or 

EASA; or BAE Systems (Operations) 

Limited’s EASA Design Organization 

Approval (DOA). This difference has 

been coordinated with EASA. 

‘‘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 

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 BAE 

Systems (Operations) Limited’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 1 airplane of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 


emcdonald on DSK67QTVN1PROD with PROPOSALS
52262 Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Proposed Rules 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspection ................... 8 work-hours × $85 per hour = 

$680 per inspection cycle.

$0 $680 per inspection cycle .......... $680 per inspection cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates 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 proposed 

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 adding 

the following new airworthiness 

directive (AD): 

BAE Systems (Operations) Limited: Docket 

No. FAA–2014–0621; Directorate 

Identifier 2013–NM–201–AD. 

(a) Comments Due Date 

We must receive comments by October 20, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all BAE Systems 

(Operations) Limited Model BAe 146–100A, 

–200A, and –300A airplanes; and Model 

Avro 146–RJ70A, 146–RJ85A, and 146– 

RJ100A airplanes; certificated in any 

category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report of a 

pressurization problem on an airplane during 

climb-out; a subsequent investigation showed 

a crack in the fuselage skin. We are issuing 

this AD to detect and correct cracking, 

corrosion, and other defects, which could 

affect the structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

(1) Within the compliance times specified 

in paragraphs (g)(1)(i) and (g)(1)(ii) of this 

AD, as applicable: Do an external eddy 

current inspection on the aft skin lap joints 

of the rear fuselage for cracking, corrosion, 

and other defects (i.e. surface damage and 

spot displacement), in accordance with 

paragraph 2.C. of the Accomplishment 

Instructions of BAE Systems (Operations) 

Limited Inspection Service Bulletin 53–239, 

Revision 2, dated July 15, 2013. 

(i) For any airplane which has accumulated 

9,000 flight cycles or more since the 

airplane’s first flight as of the effective date 

of this AD: Do the inspection within 1,000 

flight cycles or 6 months after of the effective 

date of this AD, whichever occurs first. 

(ii) For any airplane which has 

accumulated less than 9,000 flight cycles 

since the airplane’s first flight as the effective 

date of this AD: Do the inspection before 

accumulating 10,000 flight cycles since the 

airplane’s first flight. 

(2) Repeat the inspection required by 

paragraph (g)(1) of this AD thereafter at 

intervals not to exceed the times specified in 

paragraphs (g)(2)(i) and (g)(2)(ii) of this AD, 

as applicable to the airplane’s modification 

status. 

(i) For Model BAe 146 series airplanes and 

Model Avro 146–RJ series airplanes post 

modification HCM50070E, or post 

modification HCM50070F, or post 

modification HCM50259A, repeat the 

inspection at intervals not to exceed 4,000 

flight cycles. 

(ii) For Model BAe 146 series airplanes and 

Model Avro 146–RJ series airplanes premodification HCM50070E, and premodification HCM50070F, and premodification HCM50259A, repeat the 

inspection at intervals not to exceed 7,500 

flight cycles. 

(h) Corrective Action 

If any cracking, corrosion, or other defect 

is found during any inspection required by 

this AD: Before further flight, repair 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 

DOA-authorized signature. Accomplishment 

of the repair does not constitute a terminating 

action for the inspections required by 

paragraph (g) of this AD. 

(i) Credit for Previous Actions 

(1) This paragraph provides credit for the 

initial inspection and corrective action on 

stringer 30, left hand (LH) and right hand 

(RH), as required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using BAE Systems 

(Operations) Limited Inspection Service 

Bulletin 53–239, dated June 13, 2012, which 

is not incorporated by reference in this AD. 

(2) This paragraph provides credit for the 

initial inspection and corrective action, as 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using BAE Systems 

(Operations) Limited Inspection Service 

Bulletin 53–239, Revision 1, dated June 18, 

2013, which is not incorporated by reference 

in this AD. 


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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. 


emcdonald on DSK67QTVN1PROD with PROPOSALS