Federal Register / Vol. 77, No. 152 / Tuesday, August 7, 2012 / Rules and Regulations 46935 

(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 Boeing Alert 

Service Bulletin 767–57A0126, dated August 

12, 2011, as revised by Boeing Service 

Bulletin 767–57A0126, Revision 1, dated 

November 9, 2011; both of which are not 

incorporated by reference. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(k) Related Information 

For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6577; fax: 425–917– 

6590; email: Berhane.Alazar@faa.gov. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the following service information 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 767– 

57A0126, Revision 2, dated March 12, 2012. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; phone: 

206–544–5000, extension 1; fax: 206–766– 

5680; Internet: https://www.myboeingfleet.

com. 

(4) You may review copies of the 

referenced service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, Washington. For 

information on the availability of this 

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

(5) You may also review copies of the 

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/ibr-locations.html. 

Issued in Renton, Washington, on July 23, 

2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–18578 Filed 8–6–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0414; Directorate 

Identifier 2011–NM–210–AD; Amendment 

39–17138; AD 2012–15–09] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) certain 

Airbus Model A310–203, –221, and 

–222 airplanes. This AD was prompted 

by the manufacturer re-classifying slat 

extension eccentric bolts as principal 

structural elements with replacement 

due at or before their calculated fatigue 

lives. This AD replaces certain slat 

extension eccentric bolts with new 

bolts. We are issuing this AD to prevent 

fatigue cracking, which could result in 

the loss of structural integrity of the 

airplane. 

DATES: This AD becomes effective 

September 11, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 11, 2012. 

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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; 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 May 2, 2012 (77 FR 25930). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Slat extension eccentric bolts have been reclassified as Principal Structural Elements 

(PSE). As a result, associated fatigue lives 

will be published in the Airbus A310 

Airworthiness Limitations Section (ALS) Part 

1 and bolts must be replaced at or before 

their calculated fatigue lives. 

The slat extension eccentric bolt Part 

Number (P/N) A5786451220800 installed at 

slat 2, track 6 of the left hand (LH) and right 

hand (RH) wings is manufactured by 

SONACA, but some bolts with the same P/ 

N, manufactured by FOKKER, may have been 

installed on A310–200 series aeroplanes and 

are identical in appearance. The calculated 

fatigue life of the FOKKER bolt is lower than 

that of the SONACA equivalent bolt. 

The difference between the FOKKER and 

SONACA bolt cannot be distinguished by a 

visual inspection. To remedy this, the 

SONACA bolt part number was changed from 

P/N A5786451220800 to P/N 

A5784307920000. 

Failure to replace the bolts within the new 

fatigue life limits constitutes an unsafe 

condition. 

For the reasons described above, this 

[EASA] AD requires the replacement of all 

slat extension eccentric bolts, P/N 

A5786451220800, with slat extension 

eccentric bolts P/N A5784307920000 at the 

slat 2 tracks 4, 6 and 7 positions, as well as 

at the slat 3 track 8 position, on both LH and 

RH wings. 

In addition, it is required to replace the slat 

extension eccentric bolt P/N A57843624200 

at slat 2 track 5 with a bolt P/N 

A57843624202. 

Required actions also include a 

concurrent inspection of the removed 

bolts for cracking. If cracking is found, 

certain bolts at slat 2 track 5 are 

replaced with new bolts before further 

flight. If cracking is not found, certain 

bolts at slat 2 track 5 are replaced with 

new bolts at 35,900 total flight cycles or 

71,800 total flight hours, whichever 

occurs first. The unsafe condition is 

fatigue cracking, which could result in 

the loss of structural integrity of the 

airplane. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 


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46936 Federal Register / Vol. 77, No. 152 / Tuesday, August 7, 2012 / Rules and Regulations 

FR 25930, May 2, 2012) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD will affect 

48 products of U.S. registry. We also 

estimate that it will take about 12 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $35,365 

per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$1,746,480, or $36,385 per product. 

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 25930, May 

2, 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 adding 

the following new AD: 

2012–15–09 Airbus: Amendment 39–17138. 

Docket No. FAA–2012–0414; Directorate 

Identifier 2011–NM–210–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective September 11, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A310– 

203, –221, and –222 airplanes; certificated in 

any category; all manufacturer serial numbers 

(MSN), except airplanes having MSN 0415, 

0419, 0424, 0427, 0430, 0454, 0468, 0486, 

and 0487. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by the 

manufacturer re-classifying slat extension 

eccentric bolts as principal structural 

elements (PSEs) with replacement due at or 

before their calculated fatigue lives. We are 

issuing this AD to prevent fatigue cracking, 

which could result in the loss of 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) Bolt Replacement at Slat 2 Track 6 and 

Visual Inspection 

(1) At the later of the times specified in 

paragraphs (g)(1)(i) and (g)(1)(ii) of this AD: 

Replace the slat extension eccentric bolts 

having part number (P/N) A5786451220800 

at slat 2 track 6 on both wings with bolts 

having P/N A5784307920000, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A310–57– 

2043, Revision 05, dated September 29, 2010. 

(i) Before the accumulation of 14,000 total 

flight cycles or 19,000 total flight hours, 

whichever occurs first. 

(ii) Within 6 months after the effective date 

of this AD. 

(2) Concurrently with the actions specified 

in paragraph (g)(1) of this AD: Do a general 

visual inspection of the removed slat 

extension eccentric bolts having P/N 

A5786451220800 to detect cracking, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A310–57–2043, Revision 05, dated 

September 29, 2010. 

(i) If any cracking is found during the 

inspection required by paragraph (g)(2) of 

this AD: Before further flight, replace the slat 

extension eccentric bolt having P/N 

A57843624200 at slat 2 track 5, on the right 

or left wing as applicable, with a bolt having 

P/N A57843624202, in accordance with 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–57–2099, 

dated July 22, 2011. 

(ii) If no cracking is found during the 

inspection required by paragraph (g)(2) of 

this AD: Before the accumulation of 35,900 

total flight cycles or 71,800 total flight hours, 

whichever occurs first, replace the slat 

extension eccentric bolt having P/N 

A57843624200 at slat 2 track 5, on the right 

or left wing as applicable, with a bolt having 

P/N A57843624202, in accordance with 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–57–2099, 

dated July 22, 2011. 

(h) Bolt Replacement at Slat 2 Track 4 and 

Track 7, and Slat 3 Track 8 

Within 30 months after the effective date 

of this AD: Replace the slat extension 

eccentric bolts having P/N A5786451220800 

at slat 2 track 4 and track 7, and slat 3 track 

8, on both wings, with bolts having P/N 

A5784307920000, in accordance with the 


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Federal Register / Vol. 77, No. 152 / Tuesday, August 7, 2012 / Rules and Regulations 46937 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–57–2098, 

dated July 22, 2011. 

(i) Parts Installation Prohibition 

After modification of an airplane as 

required by this AD, do not install any slat 

extension eccentric bolt having P/N 

A5786451220800 on any airplane. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to Attn: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–2125; fax (425) 

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

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

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(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 

Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2011–0187, 

dated September 27, 2011, and the following 

service information, for related information. 

(1) Airbus Mandatory Service Bulletin 

A310–57–2043, Revision 05, dated 

September 29, 2010. 

(2) Airbus Mandatory Service Bulletin 

A310–57–2098, dated July 22, 2011. 

(3) Airbus Mandatory Service Bulletin 

A310–57–2099, dated July 22, 2011. 

(l) 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. 

(i) Airbus Mandatory Service Bulletin 

A310–57–2043, Revision 05, dated 

September 29, 2010. 

(ii) Airbus Mandatory Service Bulletin 

A310–57–2098, dated July 22, 2011. 

(iii) Airbus Mandatory Service Bulletin 

A310–57–2099, dated July 22, 2011. 

(3) For Airbus service information 

identified in this AD, Airbus SAS–EAW 

(Airworthiness Office), 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.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(4) 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. 

(5) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on July 20, 

2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–18579 Filed 8–6–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0185; Directorate 

Identifier 2011–NM–001–AD; Amendment 

39–17143; AD 2012–15–14] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A300 B4–103, B4–203, 

and B4–2C airplanes, and Model A300 

B4–600, B4–600R, and F4–600R series 

airplanes, and Model A300 C4–605R 

Variant F airplanes (collectively called 

A300–600 series airplanes). This AD 

was prompted by reports of cracking in 

the forward lug of the main landing gear 

(MLG) rib 5 aft bearing attachment. This 

AD requires repetitive inspections for 

cracking of the left-hand (LH) and righthand (RH) wing MLG rib 5 aft bearing 

forward lugs, and repair if necessary. 

We are issuing this AD to detect and 

correct cracking of the LH and RH wing 

MLG rib 5 aft bearing forward lugs, 

which could affect the structural 

integrity of the MLG attachment, 

resulting in MLG collapse during 

landing or rollout with consequent 

damage to the airplane and injury to 

occupants. 

DATES: This AD becomes effective 

September 11, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 11, 2012. 

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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; 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 February 28, 2012 (77 FR 

11793). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During routine visual inspection, a crack 

has been found in the wing MLG [main 

landing gear] rib 5 aft bearing forward lug on 

two A310 in-service aeroplanes. Laboratory 

examination of cracked ribs confirmed that 

the crack was due to the presence of pitting 

corrosion in the forward lug hole. Also on 

both aeroplanes medium to heavy corrosion 

was found in the forward lugs on the 

opposite wing after removal of the bushes. 

Similarly to A310 aeroplanes, A300 and 

A300–600 aeroplanes are concerned by this 

situation which, if not detected, could affect 

the structural integrity of the MLG 

attachment. 

The aim of the [EASA] Emergency 

Airworthiness Directive (EAD) 2006–0372–E 

[which corresponds to FAA AD 2007–03–18, 

Amendment 39–14929 (72 FR 5919, February 

8, 2007)] was to mandate, for A300 and 

A300–600 aeroplanes, repetitive detailed 

visual inspections (DVI) of wing MLG rib 5 

aft bearing forward lugs for detection of 

through cracks. 

Since then, in order to ensure the detection 

of any crack in the forward lug of the RH 

[right-hand] and LH [left-hand] MLG rib 5 aft 

bearing attachment at an early stage, Airbus 

has developed a new inspection by means of 

ultrasonic method. Due to the early crack 

detection possibility, this new means of 

inspection also enables extension of the 

inspection interval. 

For technical reasons, this new means of 

inspection is only applicable to A300B4, C4, 


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