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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46938 Federal Register / Vol. 77, No. 152 / Tuesday, August 7, 2012 / Rules and Regulations 

and F4 and A300–600 aeroplane series (not 

to A300B2 aeroplane series). 

For these reasons, this new [EASA] AD 

* * * adds new inspection program 

requirements [a revised detailed inspection, 

optional ultrasonic inspections, and repair if 

necessary]. 

As an option, a modification, which 

includes installing bushings with an 

increased interference fit in the aft 

bearing forward lugs, terminates the 

repetitive inspections. 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 

considered the comments received. 

Request To Refer to Revised Service 

Bulletin 

UPS requested that we revise the 

NPRM (77 FR 11793, February 28, 2012) 

to refer to Airbus Mandatory Service 

Bulletin A300–57–6106, Revision 03, 

dated January 26, 2012. UPS pointed out 

that this revised service bulletin 

provides a new repair drawing that 

supersedes a previous repair drawing. 

We agree. We have changed 

paragraphs (j) and (o) of this AD to refer 

to Airbus Mandatory Service Bulletin 

A300–57–6106, Revision 03, dated 

January 26, 2012. We have also added 

paragraph (m)(5) to this AD to give 

credit for actions done before the 

effective date of this AD using Airbus 

Service Bulletin A300–57–6106, 

Revision 02, dated June 18, 2010. 

Request To Change Paragraph 

Reference for Terminating Action 

UPS stated that paragraph (k) of the 

NPRM (77 FR 11793, February 28, 2012) 

provides terminating action to AD 

2007–03–18, Amendment 39–14929 (72 

FR 5919, February 8, 2007), by doing the 

inspections called out in paragraph (g) 

of the NPRM. UPS stated that the 

reference for the terminating action for 

the repetitive inspections of this NPRM 

and for AD 2007–03–18 should be 

paragraph (j) of the NPRM. 

We agree that paragraph (k) of this AD 

should refer to paragraph (j), not 

paragraph (g), of this AD for the 

terminating modification. Paragraph (k) 

of this AD has been changed to refer to 

paragraph (j) of this AD. 

Request To Specify Terminating Action 

for Related AD 

UPS requested that we refer to Airbus 

Mandatory Service Bulletin A300–57– 

6106, Revision 03, dated January 26, 

2012, which clarifies that the 

terminating action for the repetitive 

inspections includes replacing the 

bushings. UPS also requested that the 

same reference be included in a related 

NPRM (Docket No. FAA–2011–1225, 

Directorate Identifier 2010–NM–269– 

AD). 

We agree that the terminating action 

should include replacing the bushings, 

which is clarified in Airbus Mandatory 

Service Bulletin A300–57–6106, 

Revision 03, dated January 26, 2012. As 

stated previously, we have changed 

paragraph (j) of this AD to refer to 

Airbus Mandatory Service Bulletin 

A300–57–6106, Revision 03, dated 

January 26, 2012. No further change to 

this AD is necessary. 

Directorate Identifier 2010–NM–269– 

AD, has been issued as AD 2012–08–03, 

Amendment 39–17019 (77 FR 24367, 

April 24, 2012), and refers to Airbus 

Mandatory Service Bulletin A300–57– 

6106, Revision 03, dated January 26, 

2012, for the terminating action. 

Other Change Made To This AD 

We have revised paragraph (m) of this 

AD to refer to paragraph (j) of this AD 

instead of paragraph (g) of this AD. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

11793, February 28, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 11793, 

February 28, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

165 products of U.S. registry. We also 

estimate that it will take about 3 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $42,075, or $255 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 52 work-hours and require parts 

costing $4,590, for a cost of $9,010 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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 11793, 

February 28, 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. 


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Federal Register / Vol. 77, No. 152 / Tuesday, August 7, 2012 / Rules and Regulations 46939 

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: 

2012–15–14 Airbus: Amendment 39–17143. 

Docket No. FAA–2012–0185; Directorate 

Identifier 2011–NM–001–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective September 11, 2012. 

(b) Affected ADs 

This AD affects AD 2007–03–18, 

Amendment 39–14929 (72 FR 5919, February 

8, 2007). 

(c) Applicability 

This AD applies to Airbus Model A300 B4– 

2C, B4–103, and B4–203 airplanes; Model 

B4–601, B4–603, B4–620, B4–622, B4–605R, 

B4–622R, F4–605R, and F4–622R airplanes; 

and Model A300 C4–605R Variant F 

airplanes; certificated in any category; all 

serial numbers except for airplanes identified 

in paragraphs (c)(1), (c)(2), and (c)(3) of this 

AD. 

(1) Airplanes on which LH (left-hand) and 

RH (right-hand) wing main landing gear 

(MLG) rib 5 forward lugs have oversized 

interference fit bushings installed per Airbus 

Repair Instruction R57240221. 

(2) Model A300 B4–103, B4–203, and B4– 

2C airplanes on which Airbus Mandatory 

Service Bulletin A300–57–0249 has been 

done in service on the LH and RH wing. 

(3) Model A300–600 series airplanes on 

which Airbus Mandatory Service Bulletin 

A300–57–6106 has been done in service on 

the LH and RH wing. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57: Wings. 

(e) Reason 

This AD was prompted by reports of 

cracking in the forward lug of the MLG rib 

5 aft bearing attachment. 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. 

(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) Inspections 

Except as provided by paragraph (h) of this 

AD, before the accumulation of 12,000 total 

flight cycles since new, or within 12,000 

flight cycles since the most recent MLG rib 

5 replacement, if applicable, or within 10 

days after the effective date of this AD, 

whichever occurs latest: Do a detailed 

inspection or an ultrasonic inspection for 

cracking of the LH and RH MLG rib 5 aft 

bearing forward lugs, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–57–0251, 

including Appendix 01, dated August 8, 2007 

(for Model A300 B4–103, B4–203, and B4–2C 

airplanes); or Airbus Mandatory Service 

Bulletin A300–57–6107, including Appendix 

01, dated August 8, 2007 (for Model A300– 

600 series airplanes). Repeat the applicable 

inspections thereafter at the applicable 

interval specified in paragraph (g)(1) or (g)(2) 

of this AD, until the modification specified 

in paragraph (j) of this AD is accomplished. 

(1) Repeat the detailed inspections at 

intervals not to exceed 100 flight cycles. 

(2) Repeat the ultrasonic inspections at 

intervals not to exceed 675 flight cycles. 

(h) Exception 

For airplanes on which an inspection 

required by AD 2007–03–18, Amendment 

39–14929 (72 FR 5919, February 8, 2007), has 

been done as of the effective date of this AD: 

Within 100 flight cycles after doing the most 

recent inspection required by AD 2007–03– 

18, or within 10 days after the effective date 

of this AD, whichever occurs later, do a 

detailed or ultrasonic inspection as specified 

in paragraph (g) of this AD. Repeat the 

applicable inspection thereafter at the times 

specified in paragraph (g) of this AD. 

(i) Repair 

If any cracking is detected during any 

detailed or ultrasonic inspection of the LH 

and RH MLG rib 5 aft bearing forward lugs 

required by paragraph (g) 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). 

(j) Optional Terminating Modification 

Performing the applicable actions specified 

in paragraphs (j)(1), (j)(2), (j)(3) and (j)(4) of 

this AD, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–57–0249, 

Revision 02, dated June 18, 2010 (for Model 

A300 B4–103, B4–203, and B4–2C airplanes); 

or Airbus Mandatory Service Bulletin A300– 

57–6106, Revision 03, dated January 26, 2012 

(for Model A300–600 series airplanes); 

terminates the repetitive inspections required 

by this AD. 

(1) Perform a general visual inspection and 

dye penetrant flaw detection inspection for 

corrosion and damage of the bore and 

spotfaces of the lug. 

(2) Determine that the diameter of the bore 

of the lug (dimension Y) is within the 

tolerance specified in the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A300–57–0249, Revision 02, dated 

June 18, 2010 (for Model A300 B4–103, B4– 

203, and B4–2C airplanes); or Airbus 

Mandatory Service Bulletin A300–57–6106, 

Revision 03, dated January 26, 2012 (for 

Model A300–600 series airplanes). 

(3) If damage or corrosion is detected 

during any inspection specified in paragraph 

(j)(1) of this AD, or if dimension Y is outside 

the tolerance specified in the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–57–0249, 

Revision 02, dated June 18, 2010 (for Model 

A300 B4–103, B4–203, and B4–2C airplanes); 

or Airbus Mandatory Service Bulletin A300– 

57–6106, Revision 03, dated January 26, 2012 

(for Model A300–600 series airplanes); repair 

using a method approved by either the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

EASA (or its delegated agent). 

(4) Install bushings with an increased 

interference fit in the aft bearing forward 

lugs, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–57–0249, 

Revision 02, dated June 18, 2010 (for Model 

A300 B4–103, B4–203, and B4–2C airplanes); 

or Airbus Mandatory Service Bulletin A300– 

57–6106, Revision 03, dated January 26, 2012 

(for Model A300–600 series airplanes). 

(k) Terminating Action for AD 2007–03–18, 

Amendment 39–14929 (72 FR 5919, 

February 8, 2007) 

Doing the actions required by paragraph (j) 

of this AD terminates the requirements of AD 

2007–03–18, Amendment 39–14929 (72 FR 

5919, February 8, 2007), for that airplane. 

(l) Reporting 

Submit a report (including both positive 

and negative findings), using the applicable 

report sheet attached to Airbus Mandatory 

Service Bulletin A300–57–0251, including 

Appendix 01, dated August 8, 2007 (for 

Model A300 B4–103, B4–203, and B4–2C 

airplanes); or Airbus Mandatory Service 

Bulletin A300–57–6107, including Appendix 

01, August 8, 2007 (for Model A300–600 

series airplanes); of the first inspection 

required by paragraph (g) of this AD. Submit 

the report 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 (l)(1) or (l)(2) of 

this AD. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(m) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified by paragraph (j) of this AD, 

if those actions were performed before the 

effective date of this AD using the applicable 

service bulletins specified in paragraphs 

(m)(1), (m)(2), (m)(3), (m)(4), and (m)(5) of 

this AD. 


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46940 Federal Register / Vol. 77, No. 152 / Tuesday, August 7, 2012 / Rules and Regulations 

(1) Airbus Service Bulletin A300–57–0249, 

dated May 22, 2007 (for Model A300 B4–2C, 

B4–103, and B4–203 airplanes). 

(2) Airbus Service Bulletin A300–57–0249, 

Revision 01, dated December 19, 2007 (for 

Model A300 B4–2C, B4–103, and B4–203 

airplanes). 

(3) Airbus Service Bulletin A300–57–6106, 

dated May 22, 2007 (Model A300 B4–601, 

B4–603, B4–605R, B4–620, B4–622, B4– 

622R, F4–605R, F4–622R, and C4–605R 

Variant F airplanes). 

(4) Airbus Service Bulletin A300–57–6106, 

Revision 01, dated January 28, 2008 (Model 

A300 B4–601, B4–603, B4–605R, B4–620, 

B4–622, B4–622R, F4–605R, F4–622R, and 

C4–605R Variant F airplanes). 

(5) Airbus Service Bulletin A300–57–6106, 

Revision 02, dated June 18, 2010 (Model 

A300 B4–601, B4–603, B4–605R, B4–620, 

B4–622, B4–622R, F4–605R, F4–622R, and 

C4–605R Variant F airplanes). 

(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: 

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-AMO-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. 

(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) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2010–0250, dated November 29, 

2010, and the service information specified 

in paragraphs (o)(1), (o)(2), (o)(3), and (o)(4) 

of this AD, for related information. 

(1) Airbus Mandatory Service Bulletin 

A300–57–0249, Revision 02, dated June 18, 

2010. 

(2) Airbus Mandatory Service Bulletin 

A300–57–0251, including Appendix 01, 

dated August 8, 2007. 

(3) Airbus Mandatory Service Bulletin 

A300–57–6106, Revision 03, dated January 

26, 2012. 

(4) Airbus Mandatory Service Bulletin 

A300–57–6107, including Appendix 01, 

August 8, 2007. 

(p) 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) Airbus Mandatory Service Bulletin 

A300–57–0249, Revision 02, dated June 18, 

2010. 

(ii) Airbus Mandatory Service Bulletin 

A300–57–0251, including Appendix 01, 

dated August 8, 2007. 

(iii) Airbus Mandatory Service Bulletin 

A300–57–6106, Revision 03, dated January 

26, 2012. 

(iv) Airbus Mandatory Service Bulletin 

A300–57–6107, including Appendix 01, 

August 8, 2007. 

(3) For service information identified in 

this AD, contact 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, 

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 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 23, 

2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–18621 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–2012–0046; Directorate 

Identifier 2011–CE–040–AD; Amendment 

39–17136; AD 2012–15–07] 

RIN 2120–AA64 

Airworthiness Directives; Glasflugel 

Gliders 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Glasflugel Models Standard Libelle201B, Club Libelle 205, Mosquito, and 

Kestrel gliders. This AD results from 

mandatory continuing airworthiness 

information (MCAI) issued by an 

aviation authority of another country to 

identify and correct an unsafe condition 

on an aviation product. The MCAI 

describes the unsafe condition as 

corrosion damage to the elevator control 

rod that could lead to failure of the 

elevator control rod, possibly resulting 

in loss of control of the glider. We are 

issuing this AD to require actions to 

address the unsafe condition on these 

products. 

DATES: This AD is effective September 

11, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the 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 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

For service information identified in 

this AD, contact Glasfaser FlugzeugService Hansjo ̈rg Streifeneder GmbH, D– 

72582 Grabenstetten, Germany; phone: 

+49(0)73821032, fax: +49(0)73821629; 

email: info@streifly.de; Internet: 

www.streifly.de/. You may review 

copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

FOR FURTHER INFORMATION CONTACT: Jim 

Rutherford, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 


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