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
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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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1138; 

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–2013–0828; Directorate Identifier 

2012–NM–036–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 July 2, 2009, we issued AD 2009– 

15–17, Amendment 39–15980 (74 FR 

37523, July 29, 2009). That AD required 

actions intended to address an unsafe 

condition on the products listed above. 

Since we issued AD 2009–15–17, 

Amendment 39–15980 (74 FR 37523, 

July 29, 2009), we received reports of 

thin paint coats and paint degradation 

on enhanced MLG bogie beams. The 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0015, 

dated January 23, 2012 (referred to after 

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

condition for the specified products. 

The MCAI states: 

The operator of an A330 aeroplane (which 

has a common bogie beam with the A340) 

reported a fracture of the right-hand (RH) 

main landing gear (MLG) bogie beam, which 

occurred while turning during low speed taxi 

maneuvers. The bogie fractured aft of the 

pivot point and remained attached to the 

sliding tube by the brake torque reaction 

rods. After this RH bogie failure, the 

aeroplane continued for approximately 40 

meters on the forks of the sliding member 

before coming to rest on the taxiway. 

The preliminary investigations revealed 

that his event was due to corrosion pitting 

occurring on the bore of the bogie beam. 

Investigations are ongoing to determine why 

bogie beam internal paint has been degraded, 

leading to a loss of cadmium plating, thereby 

allowing development of corrosion pitting. 

This condition if not detected and 

corrected, could lead to a runway excursion 

event or to detachment of the bogie from the 

aeroplane, or to MLG collapse, possibly 

resulting in damage to the aeroplane and 

injury to the occupants. 

To enable early detection and repair of 

corrosion of the internal surfaces, EASA 

issued EASA AD 2007–0314 to require a onetime inspection of all MLG bogie beams, 

except Enhanced MLG bogie beams, and the 

reporting of the results to Airbus. EASA AD 

2007–0314 was revised and later superseded 

by EASA AD 2008–0093, reducing the 

inspection threshold. 

The results of subsequent investigations 

showed thin paint coats and paint 

degradation, confirmed as well on Enhanced 

MLG bogie beams. To address this additional 

concern, EASA issued EASA AD 2011–0141 

[which was not mandated by the FAA], 

retaining the requirements of EASA AD 

2008–0093, which was superseded, to require 

a one-time visual inspection of all MLG bogie 

beams, including a visual examination of the 

internal diameter for corrosion or damage to 

protective treatments of the bogie beam and 

measurement of the paint thickness on the 

internal bore, accomplishment of the 

applicable corrective actions and a 

modification of the MLG bogie beam to 

improve the coat paint application method, 

and application of corrosion protection. 

Prompted by in-service requests, this 

[EASA] AD retains the requirements of EASA 

AD 2011–0141, which is superseded, and 

introduces repetitive inspections [for damage 

to protective treatments or corrosion] of the 

MLG bogie beams, which allows extension of 

the compliance time for the MLG bogie beam 

modification [for improved protection from 

corrosion] from 15 years to 21 years. 

Modification of a MLG bogie beam 

constitutes terminating action for the 

repetitive inspections for that MLG bogie 

beam. 

This proposed AD also provides 

optional methods of compliance for 

inspections for corrosion, damage of the 

protective treatment, repair, and 

modification, of the MLG bogie beam. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus and Messier-Dowty have 

issued the following service bulletins. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

• Airbus Mandatory Service Bulletins 

A330–32–3237 (for Model A330 series 

airplanes), dated January 18, 2011. 

• Airbus Mandatory Service Bulletin 

A340–32–4279 (for Model A340 series 

airplanes), dated January 18, 2011. 

• Messier-Dowty Service Bulletin 

A33/34–32–272, including Appendices 

A, B, C, and D, Revision 1, dated 

September 22, 2008. 

• Messier-Dowty Service Bulletin 

A33/34–32–278, including Appendices 

A and B, dated February 17, 2010. 

• Messier-Dowty Service Bulletin 

A33/34–32–283, including Appendix A, 

dated May 11, 2010. 

• Messier-Dowty Service Bulletin 

A33/34–32–284, including Appendix A, 

dated May 11, 2010. 

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 

This AD differs from the MCAI and/ 

or service information as follows: The 

MCAI specifies repair and corrective 

actions in accordance with Airbus 

Mandatory Service Bulletin A330–32– 

3225, Revision 1, dated October 30, 

2008; or A340–32–4268, Revision 1, 

dated October 30, 2008. However, 

Airbus Mandatory Service Bulletins 

A330–32–3225, Revision 1, dated 

October 30, 2008; and A340–32–4268, 

Revision 1, dated October 30, 2008; do 

not describe those actions. Paragraphs 

(g)(1)(i) and (g)(1)(ii) of this proposed 

AD specify repair and corrective actions 

in accordance with Messier-Dowty 

Service Bulletin A33/34–32–272, 

Revision 1, including Appendices A, B, 

C, and D, dated September 22, 2008. 

Costs of Compliance 

We estimate that this proposed AD 

affects 51 airplanes of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD: 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
58980 Federal Register / Vol. 78, No. 186 / Wednesday, September 25, 2013 / Proposed Rules 

ESTIMATED COSTS

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

Inspection and actions retained from AD 2009–15– 

17 (74 FR 37523, July 29, 

2009).

22 work-hours × $85 per hour 

= $1,870 per inspection 

cycle.

$0 $1,870 per inspection cycle ... $95,370 per inspection cycle. 

Inspection and modification 

[new proposed actions].

44 work-hours × $85 per hour 

= $3,740 per inspection 

cycle.

0 3,740 per inspection cycle ..... 190,740 per inspection cycle. 

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 proposed AD is 2120– 

0056. The paperwork cost associated 

with this proposed 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 proposed 

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. 

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 

removing airworthiness directive (AD) 

2009–15–17, Amendment 39–15980 (74 

FR 37523, July 29, 2009), and adding the 

following new AD: 

Airbus: Docket No. FAA–2012–0828; 

Directorate Identifier 2012–NM–036–AD. 

(a) Comments Due Date 

We must receive comments by November 

12, 2013. 

(b) Affected ADs 

This AD supersedes AD 2009–15–17, 

Amendment 39–15980 (74 FR 37523, July 29, 

2009). 

(c) Applicability 

This AD applies to Airbus Model A330– 

201, –202, –203, –223, –223F, –243, –243F, 

–301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes; and Model A340– 

211, –212, –213, –311, –312, and –313 

airplanes; certificated in any category; all 

manufacturer serial numbers, except those 

airplanes on which Airbus modification 

58896 has been embodied in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing gear. 

(e) Reason 

This AD was prompted by reports of thin 

paint coats and paint degradation on 

enhanced main landing gear (MLG) bogie 

beams. We are issuing 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 main landing gear 

collapse, which could in result damage to the 

airplane and injury to the occupants. 

(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 

This paragraph restates the requirements of 

paragraph (f) of AD 2009–15–17, Amendment 

39–15980 (74 FR 37523, July 29, 2009). For 

Airbus Model A330–200, A330–300, A340– 

200, and A340–300 series airplanes, all serial 

numbers, except those on which Airbus 

modification 54500 has been embodied in 

production or Airbus Service Bulletin A330– 

32–3212 has been embodied in service: 

Unless already done, do the following 

actions. 

(1) At the applicable compliance time 

specified in paragraph (g)(2) or (g)(3) of this 

AD: Clean the internal bore and perform a 

detailed visual inspection of internal surfaces 

of the MLG bogie beam (right-hand and lefthand) for any damage to the protective 

treatments or any corrosion, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–32– 

3225 or A340–32–4268, both Revision 01, 

both dated October 30, 2008; as applicable. 

(i) If no damage and corrosion is found, 

before further flight, apply the protective 


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Federal Register / Vol. 78, No. 186 / Wednesday, September 25, 2013 / Proposed Rules 58981 

treatments of the bogie beam, in accordance 

with the Accomplishment Instructions of 

Messier-Dowty Service Bulletin A33/34–32– 

272, Revision 1, including Appendices A, B, 

C, and D, dated September 22, 2008. 

(ii) If any damage or corrosion is found, 

before further flight, do all applicable 

corrective actions and apply the protective 

treatments of the bogie beam, in accordance 

with the Accomplishment Instructions of 

Messier-Dowty Service Bulletin A33/34–32– 

272, Revision 1, including Appendices A, B, 

C, and D, dated September 22, 2008. 

(2) For airplanes with 54 months or less 

time-in-service since the date of issuance of 

the original French airworthiness certificate 

or the date of issuance of the original French 

or EASA export certificate of airworthiness as 

of September 2, 2009 (the effective date of 

AD 2009–15–17, Amendment 39–15980 (74 

FR 37523, July 29, 2009): At the latest of the 

applicable times specified in paragraphs 

(g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD, do 

the actions required by paragraph (g)(1) of 

this AD. 

(i) Not before 54 months since the date of 

issuance of the original French airworthiness 

certificate or the date of issuance of the 

original French or EASA export certificate of 

airworthiness, but no later than 72 months 

since the date of issuance of the original 

French airworthiness certificate or the date of 

issuance of the original French or EASA 

export certificate of airworthiness. 

(ii) Not before 54 months since the 

installation of a new bogie beam in-service 

before September 2, 2009 (the effective date 

of AD 2009–15–17, Amendment 39–15980 

(74 FR 37523, July 29, 2009)), but no later 

than 72 months since the installation of a 

new bogie beam in-service before September 

2, 2009 (the effective date of AD 2009–15– 

17). 

(iii) Not before 54 months since the last 

overhaul of a bogie beam before September 

2, 2009 (the effective date of AD 2009–15–17, 

Amendment 39–15980 (74 FR 37523, July 29, 

2009), but no later than 72 months since the 

last overhaul of a bogie beam before 

September 2, 2009 (the effective date of AD 

2009–15–17). 

(3) For airplanes with more than 54 months 

time-in-service since the date of issuance of 

the original French airworthiness certificate 

or the date of issuance of the original French 

or EASA export certificate of airworthiness as 

of September 2, 2009 (the effective date of 

AD 2009–15–17, Amendment 39–15980 (74 

FR 37523, July 29, 2009): At the applicable 

time specified in paragraph (g)(3)(i), (g)(3)(ii), 

(g)(3)(iii), (g)(3)(iv), or (g)(3)(v) of this AD, do 

the actions required by paragraph (g)(1) of 

this AD. 

(i) For airplanes on which the bogie beam 

has not been replaced or overhauled since 

the date of issuance of the original French 

airworthiness certificate or the date of 

issuance of the original French or EASA 

export certificate of airworthiness as of 

September 2, 2009 (the effective date of AD 

2009–15–17, Amendment 39–15980 (74 FR 

37523, July 29, 2009): Within 18 months after 

September 2, 2009 (the effective date of AD 

2009–15–17). 

(ii) For airplanes on which the bogie beam 

has been replaced in-service with a new 

bogie beam and the new bogie beam has more 

than 54 months time-in-service as of 

September 2, 2009 (the effective date of AD 

2009–15–17, Amendment 39–15980 (74 FR 

37523, July 29, 2009): Within 18 months after 

September 2, 2009 (the effective date of AD 

2009–15–17). 

(iii) For airplanes on which the bogie beam 

has been replaced in-service with a new 

bogie beam and the new bogie beam has 54 

months or less time-in-service as of 

September 2, 2009 (the effective date of AD 

2009–15–17, Amendment 39–15980 (74 FR 

37523, July 29, 2009): Not before 54 months 

since the installation of a new bogie beam inservice before September 2, 2009 (the 

effective date of AD 2009–15–17), but no 

later than 72 months since the installation of 

a new bogie beam in-service before 

September 2, 2009 (the effective date of AD 

2009–15–17). 

(iv) For airplanes on which the bogie beam 

has been overhauled and the overhauled 

bogie beam has more than 54 months timein-service as of September 2, 2009 (the 

effective date of AD 2009–15–17, 

Amendment 39–15980 (74 FR 37523, July 29, 

2009): Within 18 months after September 2, 

2009 (the effective date of AD 2009–15–17), 

or at the next scheduled bogie beam 

overhaul, whichever occurs first. 

(v) For airplanes on which the bogie beam 

has been overhauled and the overhauled 

bogie beam has 54 months or less time-inservice as of September 2, 2009 (the effective 

date of AD 2009–15–17, Amendment 39– 

15980 (74 FR 37523, July 29, 2009): Not 

before 54 months since the last overhaul of 

a bogie beam before September 2, 2009 (the 

effective date of AD 2009–15–17), but no 

later than 72 months since the last overhaul 

of a bogie beam before September 2, 2009 

(the effective date of AD 2009–15–17). 

(4) Within 30 days after accomplishment of 

the inspection required by paragraph (g)(1) of 

this AD, or within 30 days after September 

2, 2009 (the effective date of AD 2009–15–17, 

Amendment 39–15980 (74 FR 37523, July 29, 

2009), whichever occurs later: Report the 

results, including no findings, to Airbus, 1 

Rond Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; email airworthiness.A330- 

A340@airbus.com. 

(5) Actions accomplished in accordance 

with Messier-Dowty Service Bulletin A33/

34–32–271, Revision 1, including 

Appendices A and B, dated November 16, 

2007, are considered acceptable for 

compliance with the corresponding 

requirements of this AD. 

(6) Actions accomplished before September 

2, 2009 (the effective date of AD 2009–15–17, 

Amendment 39–15980 (74 FR 37523, July 29, 

2009), in accordance with the service 

bulletins specified in paragraphs (g)(6)(i) 

through (g)(6)(iv) of this AD are considered 

acceptable for compliance with the 

corresponding requirements of this AD. 

(i) Airbus Mandatory Service Bulletin 

A330–32–3225, dated November 21, 2007. 

(ii) Airbus Mandatory Service Bulletin 

A340–32–4268, dated November 21, 2007. 

(iii) Messier-Dowty Service Bulletin A33/

34–32–271, including Appendix A, dated 

September 13, 2007. 

(iv) Messier-Dowty Service Bulletin A33/

34–32–272, including Appendices A, B, C, 

and D, dated November 16, 2007. 

(h) New Requirement of This AD: Repetitive 

Inspections 

For Airbus Model A330–201, –202, –203, 

–223, –223F, –243, –243F, –301, –302, –303, 

–321, –322, –323, –341, –342, and –343 

airplanes; and Model A340–211, –212, –213, 

–311, –312, and –313 airplanes; all 

manufacturer serial numbers, except those 

airplanes on which Airbus modification 

58896 has been embodied in production: 

Repeat the inspection required by paragraph 

(g)(1) of this AD at intervals not to exceed 72 

months, but not before 48 months since first 

flight after the most recent MLG bogie beam 

overhaul done after the most recent 

inspection, until the modification specified 

in paragraph (i) of this AD is done. 

(i) New Inspection and Modification 

For Airbus Model A330–201, –202, –203, 

–223, –223F, –243, –243F, –301, –302, –303, 

–321, –322, –323, –341, –342, and –343 

airplanes; and Model A340–211, –212, –213, 

–311, –312, and –313 airplanes; all 

manufacturer serial numbers, except those 

airplanes on which Airbus modification 

58896 has been embodied in production: 

Before the accumulation of 252 months on a 

MLG bogie beam, or within 90 days after the 

effective date of this AD, whichever occurs 

later, do the actions specified in paragraphs 

(i)(1) and (i)(2) of this AD. 

(1) Do a detailed inspection for damage and 

corrosion of the internal bores of the MLG 

bogie beam, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–32–3237 

or A340–32–4279, both dated January 18, 

2011, as applicable. If any damage or 

corrosion is found, repair, as applicable, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–32–3237 or A340–32–4279, 

both dated January 18, 2011, as applicable. 

(2) Modify and re-identify, as applicable, 

the MLG bogie beam, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–32–3237 or A340–32– 

4279, both dated January 18, 2011, as 

applicable. 

(j) New Optional Terminating Action 

For Airbus Model A330–201, –202, –203, 

–223, –223F, –243, –243F, –301, –302, –303, 

–321, –322, –323, –341, –342, and –343 

airplanes; and Model A340–211, –212, –213, 

–311, –312, and –313 airplanes; all 

manufacturer serial numbers, except those 

airplanes on which Airbus modification 

58896 has been embodied in production: 

Modification of a MLG bogie beam done in 

accordance with paragraph (i) of this AD, 

terminates the repetitive inspections required 

by paragraphs (g) and (h) of this AD for that 

modified MLG bogie beam. 

(k) New Exception to Service Information 

Specifications 

The inspection requirement of paragraph 

(i)(1) of this AD and the modification 

requirement of paragraph (i)(2) of this AD do 

not apply to any MLG bogie beam having any 

serial number listed in Appendix A of 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
58982 Federal Register / Vol. 78, No. 186 / Wednesday, September 25, 2013 / Proposed Rules 

Messier-Dowty Service Bulletin A33/34–32– 

283 or A33/34–32–284, both including 

Appendix A, both dated May 11, 2010, as 

applicable. 

(l) New Optional Methods of Compliance 

(1) Inspections for corrosion and damage to 

the protective treatment of the bogie beam, 

and repairs, done in accordance with 

Messier-Dowty Service Bulletin A33/34–32– 

278, including appendices A and B, dated 

February 17, 2010, are acceptable methods of 

compliance with the requirements of 

paragraph (i)(1) of this AD. 

(2) Modification of a MLG bogie beam, 

done in accordance with Messier-Dowty 

Service Bulletins A33/34–32–283 and A33/

34–32–284, both including Appendix A, both 

dated May 11, 2010, as applicable, is an 

acceptable method of compliance with the 

requirements of paragraph (i)(2) of this AD. 

(m) New Parts Installation Limitation 

As of the effective date of this AD, no 

person may install a MLG bogie beam on any 

airplane unless it is in compliance with the 

requirements and compliance times of 

paragraphs (g), (h), and (i) of this AD. 

(n) New Reporting Requirement 

Submit a report of the findings (both 

positive and negative) of the inspection 

required by paragraph (g) or (i) of this AD to 

Airbus, Customer Service Directorate, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France, using the applicable reporting 

sheet in Airbus Service Bulletin A330–32– 

3237 or A340–32–4279, both dated January 

18, 2011, at the applicable time specified in 

paragraph (n)(1) or (n)(2) of this AD. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 90 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 90 days after the effective date of this 

AD. 

(o) 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

were approved by the State of Design 

Authority (or its delegated agent). For a 

repair method to be approved, the repair 

approval must specifically refer to this AD. 

You are required to ensure the product is 

airworthy before it is returned to service. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(p) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2012–0015, dated January 23, 2012, for 

related information, which can be found in 

the AD docket on the internet at http://

www.regulations.gov. 

Issued in Renton, Washington, on 

September 17, 2013. 

Ross Landes, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–23324 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–2013–0796; Directorate 

Identifier 2013–NM–111–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2013–07– 

07, which applies to all The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and –900ER series 

airplanes. AD 2013–07–07 requires 

inspecting to determine the part number 

of the attach pins of the horizontal 

stabilizer rear spar, and replacing 

certain attach pins. Since we issued AD 

2013–07–07, we received inquiries from 

affected operators regarding the parts 

installation limitation and prohibition, 

and re-installation of certain attach pins 

that were removed for inspection. This 

proposed AD would clarify the parts 

installation limitation and prohibition, 

and would add a new requirement for 

certain airplanes on which certain 

attach pins were installed. We are 

proposing this AD to prevent premature 

failure of the attach pins, which could 

cause reduced structural integrity of the 

horizontal stabilizer to fuselage 

attachment, resulting in loss of control 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by November 12, 

2013. 

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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206– 

766–5680; Internet https://

www.myboeingfleet.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 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 Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS