## 64795 Federal Register / Vol. 76, No. 202 / Wednesday, October 19, 2011 / Rules and Regulations

(g) FAA AD Differences

Note 2: This AD differs from the MCAI and/or service information as follows: No differences.

(h) Other FAA AD Provisions

The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Jim Rutherford, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4165; fax: (816) 329– 4090; email: jim.rutherford@faa.gov. Before using any approved AMOC on any sailplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

(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: For any reporting requirement in this AD, 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.
(i) Related Information

Refer to MCAI European Aviation Safety Agency (EASA) AD No. 2011–0110, dated June 16, 2011; Diamond Aircraft Industries GmbH Service Bulletin No. MSB 36–105/1, dated May 2, 2011; and Diamond Aircraft Industries GmbH Work Instruction WI–MSB 36–105, dated April 21, 2011, for related information.
(j) Material Incorporated by Reference

(1) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference (IBR) under 5 U.S.C. 552(a) and 1 CFR part 51 of the following service information on the date specified: (2) Diamond Aircraft Industries GmbH Service Bulletin No. MSB 36–105/1, dated May 2, 2011; and Diamond Aircraft Industries GmbH Work Instruction WI–MSB 36–105, dated April 21, 2011, approved for IBR on November 23, 2011.

(3) For service information identified in this AD, contact Diamond Aircraft Industries GmbH, N.A. Otto-Stra + e 5, A–2700 Wiener Neustadt, Austria, telephone: +43 2622 26700; fax: +43 2622 26780; E-mail: office@diamond-air.at; Internet: http:// www.diamond-air.at.

(4) You may review copies of the 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.

(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 Kansas City, Missouri, on October 5, 2011. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2011–26300 Filed 10–18–11; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0040; Directorate Identifier 2008–NM–203–AD; Amendment**  **39–16831; AD 2011–21–08]**

**RIN 2120–AA64**



### Airworthiness Directives; Sicma Aero **Seat Passenger Seat Assemblies Installed on Various Transport**  **Category Airplanes**

**AGENCY** 

### : Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for Sicma Aero Seat 88xx, 89xx, 90xx, 91xx, 92xx, 93xx, 95xx, and 96xx series passenger seat assemblies, installed on various transport category airplanes. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: Cracks have been found on seats [with] backrest links P/N (part number) 90–000200– 104–1 and 90–000200–104–2. These cracks can significantly affect the structural integrity of seat backrests.



### Failure of the backrest links could result in injury to an occupant during emergency landing conditions. We are issuing this AD to require actions to correct the unsafe condition on these products.

**DATES** 

### : This AD becomes effective November 23, 2011.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 23, 2011.

**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** 

### : Jeffrey Lee, Aerospace Engineer, Boston Aircraft Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, Massachusetts 01803; telephone (781) 238–7161; fax (781) 238–7170.

**SUPPLEMENTARY INFORMATION** 

### :

Discussion

We issued a supplemental notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That supplemental NPRM was published in the Federal Register on April 25, 2011 (76 FR 22830). That supplemental NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:

Cracks have been found on seats [with] backrest links P/N (part number) 90–000200– 104–1 and 90–000200–104–2. These cracks can significantly affect the structural integrity of seat backrests.



### Failure of the backrest links could result in injury to an occupant during emergency landing conditions. The required actions include a general visual inspection for cracking of backrest links; replacement with new, improved links if cracking is found; and eventual replacement of all links with new, improved links. 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.


## 64796 Federal Register / Vol. 76, No. 202 / Wednesday, October 19, 2011 / Rules and Regulations

Support for the Supplemental NPRM (76 FR 22830, April 25, 2011)

Boeing concurs with content of the supplemental NPRM (76 FR 22830, April 25, 2011). Request to Remove Airplanes From the Proposed Applicability

Airbus stated that the Model A330– 200 and –300 series airplanes that were included in table 1 of the supplemental NPRM (76 FR 22830, April 25, 2011) were delivered with 16G-rated seats, not the 9G-rated seats affected by the proposed AD. Airbus requested that Model A330–200 and –300 series airplanes be removed from the supplemental NPRM applicability.

We agree with the comment because it correctly updates table 1 of this AD by removing airplanes that do not have the affected seats. We have changed table 1 of this AD accordingly.

Clarification of Service Bulletin Citation

We have corrected the issue number and date for Annex 1 of Sicma Aero Seat Service Bulletin 90–25–013, Issue 3, dated December 19, 2001, to be Annex 1, Issue 1, dated June 26, 2001 (referenced in paragraph (f)(6) 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. We determined that these changes will not increase the economic burden on any operator or increase the scope of the AD.

Differences Between This AD and the MCAI or Service Information

We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information.

We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance

We estimate that this AD will affect about 611 seats on 4 products of U.S. registry. We also estimate that it will take about 1 work-hour per seat to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $0 per seat. 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 $51,935, or $85 per seat. 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 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); and

3. 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 (75 FR 2826, January 19, 2010), the supplemental NPRM (76 FR 22830, April 25, 2011), 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:

2011–21–08 SICMA AERO SEAT: Amendment 39–16831. Docket No. FAA–2010–0040; Directorate Identifier 2008–NM–203–AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective November 23, 2011.

Affected ADs

(b) None.
Applicability

(c) This AD applies to Sicma Aero Seat 88xx, 89xx, 90xx, 91xx, 92xx, 93xx, 95xx, and 96xx series passenger seat assemblies identified in Annex 1, Issue 2, dated March 19, 2004, of Sicma Aero Seat Service Bulletin 90–25–013, Issue 4, dated March 19, 2004, that have backrest links having part numbers (P/Ns) 90–000200–104–1 and 90–000200– 104–2; and that are installed on, but not limited to, the airplanes identified in table 1 of this AD, certificated in any category. This AD does not apply to Sicma Aero Seat series 9140, 9166, 9173, 9174, 9184, 9188, 9196, 91B7, 91B8, 91C0, 91C2, 91C4, 91C5, 9301, and 9501 passenger seat assemblies.


## 64797 Federal Register / Vol. 76, No. 202 / Wednesday, October 19, 2011 / Rules and Regulations

T ABLE 

### 1—C ERTAIN 

### A FFECTED 

### A IRPLANE 

### M ODELS

Manufacturer Model

Airbus .................................................................. A300 airplanes. Airbus .................................................................. A310, A318, A319, A320, A321 series airplanes. ATR—GIE Avions de Transport Re  ́ gional .......... ATR42–200, –300, –320, and –500 airplanes. ATR—GIE Avions de Transport Re  ́ gional .......... ATR72–101, –201, –102, –202, –211, –212, and –212A airplanes. The Boeing Company ......................................... 727, 727C, 727–100, 727–100C, 727–200, and 727–200F series airplanes

.The Boeing Company ......................................... 737–100, –200, –200C, –300, –400, –500, –600, –700, –700C, –800, –900, and –900ER series airplanes. The Boeing Company ......................................... 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series airplanes. The Boeing Company ......................................... 757–200, –200PF, –200CB, and –300 series airplanes. The Boeing Company ......................................... 767–200, –300, –300F, and –400ER series airplanes. Bombardier, Inc .................................................. CL–600–1A11 (CL–600), CL–600–2A12 (CL–601), and CL–600–2B16 (CL–601–3A, CL–601– 3R, and CL–604) airplanes. Bombardier, Inc .................................................. CL–600–2B19 (Regional Jet Series 100 & 440) airplanes. Bombardier, Inc .................................................. CL–600–2C10 (Regional Jet Series 700, 701, & 702) airplanes. Bombardier, Inc .................................................. CL–600–2D15 (Regional Jet Series 705) airplanes. Bombardier, Inc .................................................. CL–600–2D24 (Regional Jet Series 900) airplanes. Bombardier, Inc .................................................. DHC–8–100, DHC–8–200, DHC–8–300, and DHC–8–400 airplanes. Fokker Services B.V ........................................... F.27 Mark 050, 100, 200, 300, 400, 500, 600, and 700 airplanes. Fokker Services B.V ........................................... F.28 Mark 0070, 0100, 1000, 2000, 3000, and 4000 airplanes. The Boeing Company ......................................... DC–8–11, DC–8–12, DC–8–21, DC–8–31, DC–8–32, DC–8–33, DC–8–41, DC–8–42, DC–8– 43, DC–8–51, DC–8–52, DC–8–53, DC–8–55, DC–8F–54, DC–8F–55, DC–8–61, DC–8–62, DC–8–63, DC–8–61F, DC–8–62F, DC–8–63F, DC–8–71, DC–8–72, DC–8–73, DC–8–71F, DC–8–72F, and DC–8–73F airplanes. The Boeing Company ......................................... DC–9–11, DC–9–12, DC–9–13, DC–9–14, DC–9–15, DC–9–15F, DC–9–21, DC–9–31, DC–9– 32, DC–9–32 (VC–9C), DC–9–32F, DC–9–33F, DC–9–34, DC–9–34F, DC–9–32F (C–9A, C–9B), DC–9–41, DC–9–51, DC–9–81 (MD–81), DC–9–82 (MD–82), DC–9–83 (MD–83), and DC–9–87 (MD–87) airplanes. The Boeing Company ......................................... DC–10–10, DC–10–10F, DC–10–15, DC–10–30, DC–10–30F (KC–10A and KDC–10), DC– 10–40, and DC–10–40F airplanes. The Boeing Company ......................................... MD–11 and MD–11F airplanes.

Note 1: This AD applies to Sicma Aero Seat passenger seat assemblies as installed on any airplane, regardless of whether the airplane has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance according to paragraph (g)(1) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Subject

(d) Air Transport Association (ATA) of America Code 25: Equipment/Furnishings.

Reason

(e) The mandatory continuing airworthiness information (MCAI) states:

Cracks have been found on seats [with] backrest links P/N (part number) 90–000200– 104–1 and 90–000200–104–2. These cracks can significantly affect the structural integrity of seat backrests.

Failure of the backrest links could result in injury to an occupant during emergency landing conditions. The required actions include a general visual inspection for cracking of the backrest links; replacement with new, improved links if cracking is found; and eventual replacement of all links with new, improved links.
Actions and Compliance

(f) Unless already done, do the following actions.

(1) At the later of the compliance times specified in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD, do a general visual inspection of the backrest links having P/Ns 90–000200– 104–1 and 90–000200–104–2, in accordance with Part One of Sicma Aero Seat Service Bulletin 90–25–013, Issue 4, dated March 19, 2004, including Annex 1, Issue 2, dated March 19, 2004:

(i) Before 6,000 flight hours on the backrest link since new.

(ii) Within 900 flight hours or 5 months after the effective date of this AD, whichever occurs later.

(2) If, during the inspection required by paragraph (f)(1) of this AD, cracking is found between the side of the backrest link and the lock-out pin hole but the cracking does not pass this lock-out pin hole (refer to Figure 2 of Sicma Aero Seat Service Bulletin 90–25– 013, Issue 4, dated March 19, 2004, including Annex 1, Issue 2, dated March 19, 2004): Within 600 flight hours or 3 months after doing the inspection, whichever occurs first, replace both backrest links of the affected seat with new, improved backrest links having P/Ns 90–100200–104–1 and 90– 100200–104–2, in accordance with Part Two of Sicma Aero Seat Service Bulletin 90–25– 013, Issue 4, dated March 19, 2004, including Annex 1, Issue 2, dated March 19, 2004. (3) If, during the inspection required by paragraph (f)(1) of this AD, cracking is found that passes beyond the lock-out pin hole (refer to Figure 2 of Sicma Aero Seat Service Bulletin 90–25–013, Issue 4, dated March 19, 2004, including Annex 1, Issue 2, dated March 19, 2004): Before further flight, replace both backrest links of the affected seat with new, improved backrest links having P/Ns 90–100200–104–1 and 90–100200–104–2, in accordance with Part Two of Sicma Aero Seat Service Bulletin 90–25–013, Issue 4, dated March 19, 2004, including Annex 1, Issue 2, dated March 19, 2004.

(4) If no cracking is found during the inspection required by paragraph (f)(1) of this AD: Do the replacement required by paragraph (f)(5) of this AD at the compliance time specified in paragraph (f)(5) of this AD.

(5) At the later of the compliance times specified in paragraphs (f)(5)(i) and (f)(5)(ii) of this AD, replace the links, P/Ns 90– 000200–104–1 and 90–000200–104–2, with new improved links, P/Ns 90–100200–104–1 and 90–100200–104–2, in accordance with Part Two of Sicma Aero Seat Service Bulletin 90–25–013, Issue 4, dated March 19, 2004, including Annex 1, Issue 2, dated March 19, 2004. Doing this replacement for an affected passenger seat assembly terminates the inspection requirements of paragraph (f)(1) of this AD for that passenger seat assembly.

(i) Before 12,000 flight hours on the backrest links, P/Ns 90–000200–104–1 and 90–000200–104–2, since new.

(ii) Within 900 flight hours or 5 months after the effective date of this AD, whichever occurs later.


## 64798 Federal Register / Vol. 76, No. 202 / Wednesday, October 19, 2011 / Rules and Regulations

Credit for Actions Done in Accordance With Previous Service Information

(6) Actions done before the effective date of this AD in accordance with Sicma Aero Seat Service Bulletin 90–25–013, Issue 3, dated December 19, 2001, including Annex 1, Issue 1, dated June 26, 2001, are acceptable for compliance with the corresponding actions of this AD.

FAA AD Differences

Note 2: This AD differs from the MCAI and/or service information as follows: The MCAI specifies doing repetitive inspections for cracking of links having over 12,000 flight hours since new until the replacement of the link is done. This AD does not include those repetitive inspections because we have reduced the compliance time for replacing those links. This AD requires replacing the link before 12,000 flight hours since new or within 900 flight hours or 5 months of the effective date of this AD, whichever occurs later.

Other FAA AD Provisions

(g) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, Boston Aircraft Certification Office, 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 ACO, send it to ATTN: Jeffrey Lee, Aerospace Engineer, Boston Aircraft Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, Massachusetts 01803; telephone (781) 238–7161; fax (781) 238–7170. 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.

Related Information

(h) Refer to MCAI French Airworthiness Directive 2001–613(AB), dated December 12, 2001; and Sicma Aero Seat Service Bulletin 90–25–013, Issue 4, dated March 19, 2004, including Annex 1, Issue 2, dated March 19, 2004; for related information.
Material Incorporated by Reference

(i) You must use Sicma Aero Seat Service Bulletin 90–25–013, Issue 4, dated March 19, 2004, including Annex 1, Issue 2, dated March 19, 2004, to do the actions required by this AD, unless the AD specifies otherwise.

(1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Sicma Aero Seat, 7 Rue Lucien Coupet, 36100 ISSOUDUN, France, telephone: +33 (0) 2 54 03 39 39; fax: +33 (0) 2 54 03 39 00; e-mail: customerservices.sas@ zodiacaerospace.com; Internet: http:// www.sicma.zodiacaerospace.com/en/.

(3) 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.

(4) 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/ code

_ of

_ federal

_ regulations/ibr

_ locations.html.

Issued in Renton, Washington, on September 28, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2011–26083 Filed 10–18–11; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0478; Directorate Identifier 2010–NM–138–AD; Amendment**  **39–16832; AD 2011–21–09]**

**RIN 2120–AA64**



### Airworthiness Directives; Airbus Model **A300 B4–103, B4–203, and B4–2C Airplanes** 

**AGENCY** 

### : Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are superseding an existing airworthiness directive (AD) that applies to the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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:

One operator reported a failure of the MLG [main landing gear] retraction actuator sliding rod. This incident occurred at a number of operating flight cycles lower than the limit value imposed by the MLG manufacturer.

This condition, if not detected and corrected, results in undampened extension of the MLG, leading to higher than usual loads on the MLG attachment. Higher loads affect the structural integrity of the MLG and could lead to MLG failure.


### * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.

**DATES** 

### : This AD becomes effective November 23, 2011.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 23, 2011.

**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 June 8, 2011 (76 FR 33176), and proposed to supersede AD 2007– 25–15, Amendment 39–15297 (72 FR 69601, December 10, 2007). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI
states:

One operator reported a failure of the MLG [main landing gear] retraction actuator sliding rod. This incident occurred at a number of operating flight cycles lower than the limit value imposed by the MLG manufacturer.

This condition, if not detected and corrected, results in undampened extension of the MLG, leading to higher than usual loads on the MLG attachment. Higher loads affect the structural integrity of the MLG and could lead to MLG failure.

To address and correct this unsafe condition, EASA issued AD 2006–0075 (now at Revision 2) [which corresponds to FAA AD 2007–25–15 (72 FR 69601, December 10, 2007)] to require repetitive inspections of the retraction actuator sliding rod as installed on A300, A300–600 and A300–600ST aeroplanes and, depending on findings, repair or replacement of the affected parts.

Since this event, studies have been performed by Airbus, the consequences of which are that for A300 aeroplanes, a new inspection program (new threshold and interval) has been established.

For the reason described above, this new [EASA] AD retains the requirements of AD