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

(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. 


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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. 


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

TABLE 1—CERTAIN AFFECTED AIRPLANE MODELS

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. 


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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 


sroberts on DSK5SPTVN1PROD with RULES