31386 Federal Register / Vol. 78, No. 101 / Friday, May 24, 2013 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1163; Directorate 

Identifier 2011–NM–246–AD; Amendment 

39–17456; AD 2013–10–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

all Airbus Model A330–200 and –300 

series airplanes; and Model A340–200, 

–300, –500, and –600 series airplanes. 

That AD currently requires a one-time 

detailed inspection of both main 

landing gear (MLG) bogie beams in the 

region of the bogie stop pad for 

detection of deformation and damage, 

and corrective actions if necessary. This 

new AD adds Model A330–200 

Freighter series airplanes to the 

applicability. For certain airplanes, this 

new AD also adds repetitive inspections 

for damage and corrosion of the sliding 

piston sub-assembly, with new related 

investigative and corrective actions. 

This AD was prompted by reports of 

corroded bogie stop pads, including 

some with cracking. We are issuing this 

AD to detect and correct deformation or 

damage under the bogie stop pad of both 

MLG bogie beams, which could result in 

a damaged bogie beam and consequent 

detachment of the beam from the 

airplane or collapse of the MLG and 

departure of the airplane from the 

runway. 

DATES: This AD becomes effective June 

28, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 28, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of March 4, 2010 (75 FR 

4477, January 28, 2010). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on November 16, 2012 (77 FR 

68711), and proposed to supersede AD 

2010–02–10, Amendment 39–16181 (75 

FR 4477, January 28, 2010). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community has issued EASA 

Airworthiness Directive 2011–0211, 

dated October 31, 2011 (referred to after 

this as ‘‘the MCAI’’), to supersede EASA 

AD 2008–0223, dated December 15, 

2008 (referred to in the existing AD), 

and correct an unsafe condition for the 

specified products. The MCAI states: 

During a scheduled maintenance 

inspection on the MLG [main landing gear], 

the bogie stop pad was found deformed and 

cracked. Upon removal of the bogie stop pad 

for replacement, the bogie beam was also 

found cracked. 

Laboratory investigation indicates that an 

overload event has occurred and no fatigue 

propagation of the crack was evident. 

A second bogie beam crack has 

subsequently been found on another 

aeroplane, located under a bogie stop pad 

which only had superficial paint damage. 

This condition, if not detected and 

corrected, could result in the aeroplane 

departing the runway or to the bogie 

detaching from the aeroplane or gear 

collapses, which would all constitute unsafe 

conditions at speeds above 30 knots. 

As a precautionary measure, EASA AD 

2008–0223 [which corresponds to FAA AD 

2010–02–10, Amendment 39–16181 (75 FR 

4477, January 28, 2010] required one-time 

detailed inspections under the bogie stop pad 

of both MLG bogie beams and, in case 

deformation or damage is detected, to apply 

the associated repair. 

Numerous bogie stop pad were found 

corroded and a few cracked as a result of the 

one-time inspection required by EASA AD 

2008–0223 on A330, A340–200 and A340– 

300 aeroplanes. 

For the reasons describe above, this 

[EASA] AD, which supersedes EASA AD 

2008–0223: 

—retains the initial inspection requirement 

of EASA AD 2008–0223 for A330, A340– 

200 and A340–300 aeroplanes. 

—introduces a repetitive detailed visual 

inspection for A330, A340–200 and A340– 

300 aeroplanes. 

—retains the requirement of EASA AD 2008– 

0223 for A340–500 and A340–600 

aeroplanes, for which further mandatory 

requirements might follow in future 

depending on the results of the one-time 

mandatory inspection in place. 

The required actions include repetitive 

detailed inspections for damage and 

corrosion of the sliding piston subassembly, with new related investigative 

and corrective actions. Related 

investigative actions include a test for 

indications of corrosion and damage to 

the bogie assembly base material, and a 

magnetic particle inspection for cracks, 

corrosion, and damage of the bogie 

beam. Corrective actions include 

repairing affected parts. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Revised Service Information 

Since we issued the NPRM (77 FR 

68711, November 16, 2012), we have 

reviewed the following revised service 

information. No additional work is 

specified by these revisions. 

• Airbus Mandatory Service Bulletin 

A330–32–3220, Revision 02, dated 

December 13, 2012 (for Model A330– 

200 and –300 series airplanes). 

• Airbus Mandatory Service Bulletin 

A330–32–3248, Revision 01, including 

Appendix 1, dated December 13, 2012 

(for Model A330–200, –200 Freighter, 

and –300 series airplanes). 

We have revised paragraphs (i) and (j) 

of this AD to refer to the revised service 

information, added a new paragraph (l) 

to give credit for earlier revisions of this 

service information, and re-identified 

subsequent paragraphs accordingly. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Request To Remove or Revise Reporting 

Requirement 

Delta Air Lines, Inc. (Delta) asked that 

the compliance time for the reporting 

requirement specified in the NPRM (77 

FR 68711, November 16, 2012) be 

extended from 30 to 180 days. Delta 

stated that, unless we plan to rescind or 

revise this AD in the near future based 

on the findings, paragraph (l)(1) of the 

NPRM (paragraph (m)(1) of the final 

rule) should be removed. Delta also 

recommended that the reporting be 

mandated only for positive findings— 

not positive and negative findings—and 

specifically for those findings that are 

beyond the repair limits identified in 

the applicable component maintenance 

manual. Delta stated that this would 

allow findings to be batched together for 

a grouped report and would preclude 

undue compliance issues related to late 

reporting. 

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Federal Register / Vol. 78, No. 101 / Friday, May 24, 2013 / Rules and Regulations 31387 

We do not agree to remove the 

reporting requirement in paragraph (m) 

of this AD. The reporting requirement is 

included in the requirements in the 

EASA AD, and our AD follows those 

requirements in order to ensure that the 

unsafe condition is adequately 

addressed. Reporting of both positive 

and negative findings is necessary to 

determine the scope of the problem. 

Reporting all findings will allow the 

manufacturer to conduct statistical 

analyses and apply the results to 

calculate more accurate life limits for 

the affected parts. We have made no 

change to the AD in this regard. 

In addition, we do not agree to extend 

the compliance time for the reporting 

requirement to 180 days; however, we 

will extend it to 90 days to be consistent 

with the compliance time for the 

reporting requirement in the EASA AD 

referred to in this AD. We have changed 

the compliance time for the reporting 

requirement in paragraph (m) of this AD 

accordingly. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We also determined that these changes 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD affects about 67 

products of U.S. registry. 

The actions that are required by AD 

2010–02–10, Amendment 39–16181 (75 

FR 4477, January 28, 2010), and retained 

in this AD take about 2 work-hours per 

product, at an average labor rate of $85 

per work hour. Based on these figures, 

the estimated cost of the currently 

required actions is $170 per product. 

We estimate that it will take about 16 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Based on these figures, we 

estimate the cost of the AD on U.S. 

operators to be $91,120, or $1,360 per 

product. 

We have received no definitive data 

that will enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

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 that this AD: 

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 AD and placed it in the AD docket. 

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 the NPRM (77 FR 68711, 

November 16, 2012), 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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) 

2010–02–10, Amendment 39–16181 (75 

FR 4477, January 28, 2010), and adding 

the following new AD: 

2013–10–03 Airbus: Amendment 39–17456. 

Docket No. FAA–2012–1163; Directorate 

Identifier 2011–NM–246–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective June 28, 2013. 

(b) Affected ADs 

This AD supersedes AD 2010–02–10, 

Amendment 39–16181 (75 FR 4477, January 

28, 2010). 

(c) Applicability 

This AD applies to all Airbus Model A330– 

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

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

–342, and –343 airplanes; Model A340–211, 

–212, –213, –311, –312, –313 airplanes; and 

Model A340–541 and –642 airplanes; 

certificated in any category; all serial 

numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32: Landing gear. 

(e) Reason 

This AD was prompted by reports of 

corroded bogie stop pads, some with 

cracking. We are issuing this AD to detect 

and correct deformation or damage under the 

bogie stop pad of both main landing gear 

(MLG) bogie beams, which could result in a 

damaged bogie beam and consequent 

detachment of the beam from the airplane or 

collapse of the MLG and departure of the 

airplane from the runway. 

(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 One-Time Inspection and 

Corrective Actions, With Revised Service 

Information 

This paragraph restates the requirements of 

paragraph (f)(1) of AD 2010–02–10, 

Amendment 39–16181 (75 FR 4477, January 

28, 2010), with revised service information. 

For Model A330–200 and –300 series 

airplanes, and Model A340–200, –300, –500, 

and –600 series airplanes, except as required 

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31388 Federal Register / Vol. 78, No. 101 / Friday, May 24, 2013 / Rules and Regulations 

by paragraph (i) of this AD: At the applicable 

compliance time specified in paragraph 

(g)(1), (g)(2), (g)(3), (g)(4), (g)(5), or (g)(6) of 

this AD, perform one-time detailed 

inspections of both MLG bogie beams in the 

region of the bogie stop pad for detection of 

deformation and damage, and apply the 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of the 

applicable service bulletin specified in 

paragraph (g)(7) of this AD. Do all applicable 

corrective actions before further flight. 

(1) Airplanes with 22 months or less and 

2,500 flight cycles or less from the first flight 

with the original bogie beam as of March 4, 

2010 (the effective date of AD 2010–02–10, 

Amendment 39–16181 (75 FR 4477, January 

28, 2010)): Not earlier than 2,500 flight cycles 

or 22 months on the original bogie beam, 

whichever occurs first, but not later than 40 

months from first flight. 

(2) Airplanes with 22 months or less and 

2,500 flight cycles or less from the 

installation date of a new bogie beam in 

service as of March 4, 2010 (the effective date 

of AD 2010–02–10, Amendment 39–16181 

(75 FR 4477, January 28, 2010)): Not earlier 

than 2,500 flight cycles or 22 months from 

the installation date of the new bogie beam, 

whichever occurs first, but not later than 40 

months from the installation date of a new 

bogie beam in service. 

(3) Airplanes with 22 months or less and 

2,500 flight cycles or less from the 

installation date of an overhauled bogie beam 

in service as of March 4, 2010 (the effective 

date of AD 2010–02–10, Amendment 39– 

16181 (75 FR 4477, January 28, 2010)): Not 

earlier than 2,500 flight cycles or 22 months 

from the installation date of the overhauled 

bogie beam in service, whichever occurs first, 

but not later than 40 months from the 

installation date of the overhauled bogie 

beam in service. 

(4) Airplanes with more than 22 months or 

more than 2,500 flight cycles from the first 

flight with the original bogie beam, as of 

March 4, 2010 (the effective date of AD 2010– 

02–10, Amendment 39–16181 (75 FR 4477, 

January 28, 2010)): Within 18 months after 

March 4, 2010 (the effective date of AD 2010– 

02–10). 

(5) Airplanes with more than 22 months or 

more than 2,500 flight cycles from the 

installation date of a new bogie beam in 

service, as of March 4, 2010 (the effective 

date of AD 2010–02–10, Amendment 39– 

16181 (75 FR 4477, January 28, 2010)): 

Within 18 months after March 4, 2010 (the 

effective date of AD 2010–02–10). 

(6) Airplanes with more than 22 months or 

more than 2,500 flight cycles from the 

installation date of an overhauled bogie beam 

in service, as of March 4, 2010 (the effective 

date of AD 2010–02–10, Amendment 39– 

16181 (75 FR 4477, January 28, 2010)): 

Within 18 months after March 4, 2010 (the 

effective date of AD 2010–02–10). 

(7) Use the applicable service information 

to accomplish the actions required by 

paragraph (g) of this AD. 

(i) For Model A330–200 and –300 series 

airplanes: Airbus Mandatory Service Bulletin 

A330–32–3220, dated October 10, 2008; 

Revision 01, dated October 5, 2011; or 

Revision 02, dated December 13, 2012. 

(ii) For Model A340–200 and –300 series 

airplanes: Airbus Mandatory Service Bulletin 

A340–32–4264, dated October 10, 2008. 

(iii) For Model A340–500 and –600 series 

airplanes: Airbus Mandatory Service Bulletin 

A340–32–5087, dated October 10, 2008. 

(h) Retained Reporting Requirement 

This paragraph restates the requirements of 

paragraph (f)(2) of AD 2010–02–10, 

Amendment 39–16181 (75 FR 4477, January 

28, 2010). Report the results of the inspection 

required by paragraph (g) of this AD, 

including no findings, to Airbus, Customer 

Services Directorate, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex France; Attn: 

SEDCC1 Technical Data and Documentation 

Services; fax (+33) 5 61 93 28 06; email 

sb.reporting@airbus.com; at the applicable 

time specified in paragraph (h)(1) or (h)(2) of 

this AD. 

(1) If the inspection is done on or after 

March 4, 2010 (the effective date of AD 2010– 

02–10, Amendment 39–16181 (75 FR 4477, 

January 28, 2010)): Submit the report within 

30 days after doing the inspection. 

(2) If the inspection was done prior to 

March 4, 2010 (the effective date of AD 2010– 

02–10, Amendment 39–16181 (75 FR 4477, 

January 28, 2010)): Submit the report within 

30 days after March 4, 2010 (the effective 

date of AD 2010–02–10). 

(i) New Inspections of Beams That Have Not 

Been Inspected As of the Effective Date of 

This AD 

For bogie beams on which the inspection 

required by paragraph (g) of this AD has not 

been accomplished as of the effective date of 

this AD: At the later of the times specified 

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

perform one-time detailed inspections of 

both MLG bogie beams in the region of the 

bogie stop pad for detection of deformation 

and damage, and apply the applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of the 

applicable service information specified in 

paragraph (i)(3) of this AD. Do all applicable 

corrective actions before further flight. 

(1) At the applicable time specified in 

paragraph (i)(1)(i) or (i)(1)(ii) of this AD. 

(i) For bogie beams that have not been 

overhauled: Not earlier than 2,500 flight 

cycles or 22 months, whichever occurs first, 

on a bogie beam since its first flight on an 

airplane since new, but not later than 40 

months since its first flight on an airplane 

since new. 

(ii) For bogie beams that have been 

overhauled: Not earlier than 2,500 flight 

cycles or 22 months, whichever occurs first, 

on a bogie beam since its first flight on an 

airplane after its most recent overhaul, but 

not later than 40 months since its first flight 

on an airplane after its most recent overhaul. 

(2) Within 90 days after the effective date 

of this AD. 

(3) Use the applicable service information 

specified in paragraph (i)(3)(i), (i)(3)(ii), or 

(i)(3)(iii) of this AD, to accomplish the 

actions required by paragraph (i) of this AD. 

(i) For Model A330–200 and –300 series 

airplanes: Airbus Mandatory Service Bulletin 

A330–32–3220, Revision 02, dated December 

13, 2012. 

(ii) For Model A340–200 and –300 series 

airplanes: Airbus Mandatory Service Bulletin 

A340–32–4264, dated October 10, 2008. 

(iii) For Model A340–500 and –600 series 

airplanes: Airbus Mandatory Service Bulletin 

A340–32–5087, dated October 10, 2008. 

(j) New Repetitive Inspections 

Except for bogie beams that have been 

inspected as specified in Airbus Mandatory 

Service Bulletin A340–32–5087: At the later 

of the times specified in paragraphs (j)(1) and 

(j)(2) of this AD, do the detailed inspection 

of both MLG bogie beams in the bogie stop 

pad area for damage and corrosion, and all 

applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–32–3248, 

Revision 01, dated December 13, 2012 (for 

Model A330–200, –200 Freighter, and –300 

series airplanes); or Airbus Mandatory 

Service Bulletin A340–32–4286, dated 

October 5, 2011 (for Model A340–200 and 

–300 series airplanes); except as required by 

paragraph (k) of this AD. Do all applicable 

related investigative and corrective actions 

before further flight. Repeat the inspection 

thereafter at intervals not to exceed 2,500 

flight cycles or 24 months, whichever is first. 

(1) Within 2,500 flight cycles or 24 months, 

whichever occurs first, accumulated by a 

MLG bogie beam since its first flight after the 

most recent accomplishment of Airbus 

Mandatory Service Bulletin A330–32–3220 

or A340–32–4264, as applicable. 

(2) Within 3 months after the effective date 

of this AD. 

(k) Service Information Exception 

If any cracking of the bogie beam is 

detected during any inspection or repair 

required by paragraph (j) of this AD, or any 

repair required by paragraph (j) of this AD is 

beyond the maximum repair allowance 

specified in the applicable service 

information required by paragraph (j) of this 

AD: Before further flight, repair using a 

method approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent). 

(l) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraphs (i) and (j) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Airbus Mandatory Service Bulletin A330–32– 

3220, dated October 10, 2008, or Airbus 

Mandatory Service Bulletin A330–32–3220, 

Revision 01, dated October 5, 2011; or Airbus 

Mandatory Service Bulletin A330–32–3248, 

dated October 5, 2011; as applicable; which 

are not incorporated by reference in this AD. 

(m) New Reporting Requirement 

Report the results of the initial inspection 

required by paragraph (j) of this AD, 

including both positive and negative 

findings, to Airbus, Customer Services 

Directorate, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex France; Attn: SEDCC1 

Technical Data and Documentation Services; 

fax (+33) 5 61 93 28 06; email 

sb.reporting@airbus.com; at the applicable 

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Federal Register / Vol. 78, No. 101 / Friday, May 24, 2013 / Rules and Regulations 31389 

time specified in paragraph (m)(1) or (m)(2) 

of this AD. 

(1) If the inspection is done on or after the 

effective date of this AD: Submit the report 

within 90 days after doing the inspection. 

(2) If the inspection was done prior to the 

effective date of this AD: Submit the report 

within 90 days after the effective date of this 

AD. 

(n) 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 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. AMOCs approved previously in 

accordance with AD 2010–02–10, 

Amendment 39–16181 (75 FR 4477, January 

28, 2010), are approved as AMOCs for the 

corresponding provisions of 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. 

(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. 

(o) Special Flight Permits 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed if any crack is 

found during any inspection required by this 

AD. 

(p) Related Information 

(1) Refer to mandatory continued 

airworthiness information (MCAI) EASA 

Airworthiness Directive 2011–0211, dated 

October 31, 2011, and the service information 

specified in paragraphs (p)(1)(i) through 

(p)(1)(vii) of this AD, for related information. 

(i) Airbus Mandatory Service Bulletin 

A330–32–3220, dated October 10, 2008. 

(ii) Airbus Mandatory Service Bulletin 

A330–32–3220, Revision 01, dated October 5, 

2011. 

(iii) Airbus Mandatory Service Bulletin 

A330–32–3220, Revision 02, dated December 

13, 2012. 

(iv) Airbus Mandatory Service Bulletin 

A330–32–3248, Revision 01, including 

Appendix 01, dated December 13, 2012. 

(v) Airbus Mandatory Service Bulletin 

A340–32–4264, dated October 10, 2008. 

(vi) Airbus Mandatory Service Bulletin 

A340–32–4286, dated October 5, 2011. 

(vii) Airbus Mandatory Service Bulletin 

A340–32–5087, dated October 10, 2008. 

(2) For service information identified in 

this 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. 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. 

(q) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on June 28, 2013. 

(i) Airbus Mandatory Service Bulletin 

A330–32–3220, Revision 01, dated October 5, 

2011. 

(ii) Airbus Mandatory Service Bulletin 

A330–32–3220, Revision 02, dated December 

13, 2012. 

(iii) Airbus Mandatory Service Bulletin 

A330–32–3248, Revision 01, including 

Appendix 01, dated December 13, 2012. 

(iv) Airbus Mandatory Service Bulletin 

A340–32–4286, dated October 5, 2011. 

(4) The following service information was 

approved for IBR on March 4, 2010 (75 FR 

4477, January 28, 2010). 

(i) Airbus Mandatory Service Bulletin 

A330–32–3220, dated October 10, 2008. 

(ii) Airbus Mandatory Service Bulletin 

A340–32–4264, dated October 10, 2008. 

(iii) Airbus Mandatory Service Bulletin 

A340–32–5087, dated October 10, 2008. 

(5) For service information identified in 

this 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. 

(6) You may review copies of the 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. 

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on May 13, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–11903 Filed 5–23–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0855; Directorate 

Identifier 2011–NM–136–AD; Amendment 

39–17452; AD 2013–09–10] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

all The Boeing Company Model 737– 

100, –200, –200C, –300, –400, and –500 

series airplanes. That AD currently 

requires repetitive inspections to detect 

cracking of the lower corners of the door 

frame and cross beam of the forward 

cargo door, and corrective actions if 

necessary. That AD also requires 

eventual modification of the outboard 

radius of the lower corners of the door 

frame and reinforcement of the cross 

beam of the forward cargo door, which 

terminates the existing repetitive 

inspections. This new AD revises the 

compliance times for the preventive 

modification; adds certain inspections 

for cracks in the number 5 cross beam 

of the forward cargo door; and adds 

inspections of the number 4 cross beam 

if cracks are found in the number 5 

cross beam, and corrective actions if 

necessary. For certain airplanes, this 

mstockstill on DSK4VPTVN1PROD with RULES