Federal Register / Vol. 78, No. 186 / Wednesday, September 25, 2013 / Proposed Rules 58975 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

Dassault Aviation: Docket No. FAA–2013– 

0794; Directorate Identifier 2012–NM– 

157–AD. 

(a) Comments Due Date 

We must receive comments by November 

12, 2013. 

(b) Affected ADs 

Certain requirements of this AD terminate 

the requirements of AD 2010–26–05, 

Amendment 39–16544 (75 FR 79952, 

December 21, 2010), for the airplanes 

identified in paragraph (c) of this AD. 

(c) Applicability 

This AD applies to Dassault Aviation 

Model FALCON 2000EX airplanes, 

certificated in any category, all serial 

numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Time Limits/Maintenance 

Checks. 

(e) Reason 

This AD was prompted by a revision to the 

airplane airworthiness limitations to 

introduce the corrosion prevention control 

program, among other changes, to the 

maintenance requirements and airworthiness 

limitations. We are issuing this AD to prevent 

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) Revision of Maintenance or Inspection 

Program 

Within 30 days after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, to incorporate the 

information specified in Chapter 5–40, 

Airworthiness Limitations, DGT 113877, 

Revision 8, dated July 2012, of Chapter 5 of 

the Dassault Falcon 2000EX, Falcon 2000EX 

EASy, Falcon 2000DX, and Falcon 2000LX 

Maintenance Manual, dated July 16, 2012. 

The initial compliance time for 

accomplishing the actions specified in 

Chapter 5–40, Airworthiness Limitations, 

DGT 113877, Revision 8, dated July 2012, of 

Chapter 5 of the Dassault Falcon 2000EX, 

Falcon 2000EX EASy, Falcon 2000DX, and 

Falcon 2000LX Maintenance Manual, dated 

July 16, 2012, is within the times specified 

in that maintenance manual, or 30 days after 

the effective date of this AD, whichever 

occurs later, except as provided by 

paragraphs (g)(1) through (g)(4) of this AD. 

(1) The term ‘‘landings’’ in the ‘‘First 

Inspection’’ column of any table in the 

service information means total airplane 

landings. 

(2) The term ‘‘flight hours’’ in the ‘‘First 

Inspection’’ column of any table in the 

service information means total flight hours. 

(3) The term ‘‘flight cycles’’ in the ‘‘First 

Inspection’’ column of any table in the 

service information means total flight cycles. 

(4) For task number 52–20–00–610–801–01 

52–205 the initial compliance time is within 

24 months after the effective date of this AD. 

(h) Terminating Action 

Accomplishing paragraph (g) of this AD 

terminates the requirements of paragraph (g) 

of AD 2010–26–05, Amendment 39–16544 

(75 FR 79952, December 21, 2010), for 

Dassault Aviation Model FALCON 2000EX 

Airplanes. 

(i) No Alternative Actions and Intervals 

After accomplishing the revision required 

by paragraph (g) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (j) of this 

AD. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) 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, Washington 98057– 

3356; telephone 425–227–1137; fax 425–227– 

1137. Information may be emailed to: 9- 

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

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2012–0157, dated August 23, 2012, 

for related information. The MCAI can be 

found in the AD docket on the Internet at 

http://www.regulations.gov. 

(2) For service information identified in 

this AD, contact Dassault Falcon Jet, P.O. Box 

2000, South Hackensack, NJ 07606; 

telephone 201–440–6700; Internet http:// 

www.dassaultfalcon.com. You may review 

copies of the referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

Issued in Renton, Washington, on 

September 13, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–23333 Filed 9–24–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0791; Directorate 

Identifier 2012–NM–026–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 A318, A319, A320, and 

A321 series airplanes. This proposed 

AD was prompted by a report that an 

investigation showed that when a 

certain combination of a target/

proximity sensor serial number is 

installed on a flap interconnecting strut, 

a ‘‘target FAR’’ signal cannot be detected 

when it reaches the mechanical end 

stop of the interconnecting strut. This 

proposed AD would require an 

inspection to determine the part number 

(P/N) of the interconnecting struts 

installed on the wings, identifying the 

P/N and the serial number (S/N) of the 

associated target and proximity sensor if 

applicable, and replacing or reidentifying the flap interconnecting 

strut if applicable. We are proposing 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
58976 Federal Register / Vol. 78, No. 186 / Wednesday, September 25, 2013 / Proposed Rules 

this AD to detect and correct a latent 

failure of the flap down drive 

disconnection due to an already-failed 

interconnecting strut sensor, which 

could result in asymmetric flap panel 

movement and consequent loss of 

control of the airplane. 

DATES: We must receive comments on 

this proposed AD by November 12, 

2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

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

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus, 

Airworthiness Office—EAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1405; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2013–0791; Directorate Identifier 

2012–NM–026–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 2012–0012, 

dated January 23, 2012 (referred to after 

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

condition for the specified products. 

The MCAI states: 

The flap interconnecting strut is a safety 

device of the High Lift System which acts as 

an alternative load path from one flap surface 

to another in case of a flap drive system 

disconnection. In such a failure case, the 

installed proximity provide information to 

the slat flap control computer (SFCC) and the 

operation of the flap drive system is 

inhibited. 

A recent engineering investigation has 

shown that, when a certain combination of 

target/sensor serial number (s/n) is installed 

on a flap interconnecting strut, a ‘‘target 

FAR’’ signal cannot be detected when 

reaching the mechanical end stop of the 

interconnecting strut. 

This condition, if not corrected, could 

cause a flap down drive disconnection to 

remain undetected, due to an already-failed 

interconnecting strut sensor, potentially 

resulting in asymmetric flap panel movement 

and consequent loss of control of the 

aeroplane. 

For the reason described above, this 

[EASA] AD requires the identification and 

replacement [or re-identifying] of struts that 

have a certain target/sensor s/n combination 

installed. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A320–27–1206, Revision 01, dated 

October 10, 2011. The actions described 

in this service information are intended 

to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This AD and the 

MCAI or Service Information 

Although note 1 of the EASA 

Airworthiness Directive 2012–0012, 

dated January 23, 2012, allows flight for 

50 flight cycles after the inspection of 

the flap down drive if an 

interconnecting strut cannot be 

replaced, this proposed AD does not 

include this exception. 

Costs of Compliance 

We estimate that this proposed AD 

affects 755 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection and Reidentification.8 work-hours × $85 per hour = $680 per inspection cycle.$0 ............................... $680 per inspection 

cycle.

$513,400 per inspection cycle. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 186 / Wednesday, September 25, 2013 / Proposed Rules 58977 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement ..................................... 10 work-hours × $85 per hour = $850 ......................................................... $0 $850 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

Airbus: Docket No. FAA–2013–0791; 

Directorate Identifier 2012–NM–026–AD. 

(a) Comments Due Date 

We must receive comments by November 

12, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Airbus Model A318– 

111, –112, –121, and –122 airplanes; Model 

A319–111, –112, –113, –114, –115, –131, 

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

–211, –212, –214, –231, –232, and –233 

airplanes; and Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes; 

certificated in any category; all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls. 

(e) Reason 

This AD was prompted by a report that an 

investigation showed that when a certain 

combination of a target/proximity sensor 

serial number is installed on a flap 

interconnecting strut, a ‘‘target FAR’’ signal 

cannot be detected when reaching the 

mechanical end stop of the interconnecting 

strut. We are issuing this AD to detect and 

correct a latent failure of the flap down drive 

disconnection due to an already-failed 

interconnecting strut sensor, which could 

result in asymmetric flap panel movement 

and consequent loss of control 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) Inspection To Determine the Part Number 

of the Interconnecting Struts 

Within 8,000 flight hours after the effective 

date of this AD, inspect to determine the part 

number of the interconnecting struts 

installed on both the left-hand (LH) and 

right-hand (RH) wings of the airplane, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

27–1206, Revision 01, dated October 10, 

2011. A review of the airplane maintenance 

records is acceptable for determining the part 

number of the installed interconnecting 

struts, in lieu of the inspection, if the part 

number of the installed interconnecting 

struts, and the part number and the serial 

number of the associated target and 

proximity sensor, can be conclusively 

determined from that review. 

(1) Airplanes on which Airbus 

modification 27956 has been embodied in 

production, on which no interconnecting 

strut having a part number specified in figure 

1 to paragraph (g) of this AD, and has been 

replaced since the airplane’s first flight: No 

further work is required by paragraph (g) of 

this AD. 

(2) If, during the inspection required by 

paragraph (g) of this AD, any interconnecting 

strut is installed with a part number specified 

in figure 1 to paragraph (g) of this AD: Within 

8,000 flight hours after the effective date of 

this AD, determine the part number and the 

serial number of the associated target and 

proximity sensor. 

FIGURE 1 TO PARAGRAPH (G) OF THIS

AD—Interconnecting Strut Part 

Numbers 

Interconnecting strut part numbers 

D5757030500000 

D5757030500100 

D5757030500200 

D5757030500600 

D5757030500800 

D5757030501000 

D5757030501200 

D5757032200000 

(i) For airplanes having conditions 

specified in paragraphs (g)(2)(i)(A), 

(g)(2)(i)(B), (g)(2)(i)(C), and (g)(2)(i)(D) of this 

AD: Before further flight, replace the 

interconnecting strut with a serviceable unit, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
58978 Federal Register / Vol. 78, No. 186 / Wednesday, September 25, 2013 / Proposed Rules 

27–1206, Revision 01, dated October 10, 

2011. For the purpose of this AD, a 

serviceable interconnecting strut is a unit 

which has been determined to be in 

compliance with the requirements of this AD. 

(A) A target part number (P/N) ABS0121– 

13 or P/N 8–536–01, and 

(B) A target serial number lower than 1600, 

or a target serial number that is unreadable, 

and 

(C) A proximity sensor having P/N 

ABS0121–31 or P/N 8–372–04, and 

(D) A proximity sensor having a serial 

number between C59198 and C59435, or a 

serial number (S/N) C500000 or higher. 

(ii) For a target having S/N 1600 or higher 

and target P/N ABS0121–13 or P/N 8–536– 

01: Within 8,000 flight hours after the 

effective date of this AD, re-identify the 

interconnecting strut, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–27–1206, Revision 01, 

dated October 10, 2011. 

(h) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install an interconnecting strut 

with a part number specified in figure 1 to 

paragraph (g) of this AD, on any airplane, 

except for parts identified in paragraph 

(g)(2)(ii) of this AD, provided that the actions 

in paragraph (g)(2)(ii) are done. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–27–1206, dated January 28, 

2011, and if additional work has been 

accomplished using Airbus Service Bulletin 

A320–27–1206, Revision 01, dated October 

10, 2011. 

(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, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

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

227–1149. Information may be emailed to: 9- 

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

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer or other source, 

use these actions if they are FAA-approved. 

Corrective actions are considered FAAapproved if they are approved by the State 

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2012–0012, dated 

January 23, 2012, 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, Airworthiness 

Office—EAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; Internet 

http://www.airbus.com. You may review 

copies of the referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

Issued in Renton, Washington, on 

September 13, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–23269 Filed 9–24–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0828; Directorate 

Identifier 2012–NM–036–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) 2009–15– 

17, which applied to certain Airbus 

Model A330–200 and –300; and Model 

A340–200 and –300 series airplanes. AD 

2009–15–17 required an inspection for 

damage to the protective treatments or 

any corrosion of all main landing gear 

(MLG) bogie beams, and application of 

protective treatments if no damage or 

corrosion was found. If any damage or 

corrosion was found, corrective action 

followed by the application of 

protective treatments was required. 

Since we issued AD 2009–15–17, we 

received reports of thin paint coats and 

paint degradation on enhanced MLG 

bogie beams. This proposed AD would 

add repetitive detailed inspections of 

the MLG bogie beams. This proposed 

AD would also require modification of 

the MLG bogie beams, which would 

terminate the repetitive inspections for 

any modified bogie beam. This 

proposed AD would also provide 

optional methods of compliance for 

inspections for corrosion, damage of the 

protective treatment, repair, and 

modification, of the MLG bogie beam. 

This proposed AD would also revise the 

applicability. We are proposing this AD 

to detect and correct damage or 

corrosion of the MLG bogie beams, 

which could cause a runway excursion 

event, bogie beam detachment from the 

airplane, or MLG collapse, which could 

result in damage to the airplane and 

injury to the occupants. 

DATES: We must receive comments on 

this proposed AD by November 12, 

2013. 

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 Airbus service information 

identified in this proposed AD, contact 

Airbus SAS—Airworthiness Office— 

EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone 

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

80; email airworthiness.A330-A340@

airbus.com; Internet http://

www.airbus.com. For Messier-Dowty 

service information identified in this 

AD, contact Messier-Dowty: Messier 

Services Americas, Customer Support 

Center, 45360 Severn Way, Sterling, VA 

20166–8910; telephone 703–450–8233; 

fax 703–404–1621; Internet https://

techpubs.services/messier-dowty.com. 

You may review copies of the 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS