18020 Federal Register / Vol. 76, No. 63 / Friday, April 1, 2011 / Rules and Regulations 

in the ILP program is revoked upon the 

ILP Intermediary’s receipt of this final 

notification. 

(d) Appeals. Notification of default 

without opportunity to cure under 

paragraph (b) of this section and final 

notification of uncured default under 

paragraph (c) of this section are final 

agency decisions. An ILP Intermediary 

may appeal a final agency decision only 

in the appropriate federal district court. 

§ 109.530 Debarment and Suspension. 

In accordance with 2 CFR Parts 180 

and 2700, SBA may take any necessary 

action to debar or suspend an ILP 

Intermediary or any officer, director, 

general partner, manager, employee, 

agent or other participant in the affairs 

of an ILP Intermediary’s SBA 

operations. 

Dated: March 28, 2011. 

Karen G. Mills, 

Administrator. 

[FR Doc. 2011–7741 Filed 3–31–11; 8:45 am] 

BILLING CODE 8025–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0027; Directorate 

Identifier 2008–NM–204–AD; Amendment 

39–16642; AD 2011–07–05] 

RIN 2120–AA64 

Airworthiness Directives; Sicma Aero 

Seat 9140, 9166, 9173, 9174, 9184, 

9188, 9196, 91B7, 91B8, 91C0, 91C2, 

91C4, 91C5, and 9301 Series 

Passenger Seat Assemblies; and 

Sicma Aero Seat 9501311–05, 

9501301–06, 9501311–15, 9501301–16, 

9501441–30, 9501441–33, 9501311–55, 

9501301–56, 9501441–83, 9501441–95, 

9501311–97, and 9501301–98 

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 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: 

Cracks have been found on seat 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 May 

6, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 6, 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, MA 

01803; telephone (781) 238–7161; fax 

(781) 238–7170. 

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 January 13, 2010 (75 FR 

1731). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Cracks have been found on seat 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. Therefore a life limit is 

introduced on the links. On 9g seats also 

affected by this problem, stronger unlimited 

life limits have been developed and their 

installation has been rendered mandatory. 

However, on 16g seats the affected links have 

a direct influence on certification dynamic 

tests and cannot be replaced by similar 

stronger links without performing again all 

dynamic tests for each seat part number. 

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 links if cracking 

is found, and eventual replacement of 

all links with new 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. 

Request To Revise Service Bulletin 

Reference 

Boeing requested that we update all 

references to Sicma Aero Seat Service 

Bulletin 90–25–012, Issue 4, dated 

December 19, 2001, to Issue 5, dated 

March 19, 2004, including Annex 1, 

Issue 2, dated March 19, 2004. The 

commenter justified the request by 

stating that seat series 91C3 (installed 

on Boeing Model 737 airplanes) was 

inadvertently included in Issue 4 of that 

service bulletin in error, and that Issue 

5 of that service bulletin corrects the 

effectivity by limiting it to those 

installed seats that are affected. The 

commenter also requested that we revise 

the ‘‘Relevant Service Information’’ 

section of the NPRM to refer to Issue 5 

of that service bulletin. 

We agree to update the service 

information in the AD for the reason 

given. We have revised paragraphs (c), 

(f)(1) through (f)(4), and (h) of this AD 

to refer to Sicma Aero Seat Service 

Bulletin 90–25–012, Issue 5, dated 

March 19, 2004. We also have added 

Issue 4 of that service bulletin to 

paragraph (f)(5) of this AD to give credit 

for actions done before the effective date 

of this AD in accordance with Issue 4 

of that service bulletin. 

We have not changed the ‘‘Relevant 

Service Information’’ section of the 

NPRM because that section does not 

appear in this final rule. 

Request To Remove Series 91C3 Seat 

From the Applicability 

Boeing requested that we revise the 

Applicability, paragraph (c) of the 

NPRM, to remove seat series 91C3 for 

the reason stated in the previous 

comment. 

We agree to correct the Applicability 

of the AD because Sicma Aero Seat 

Service Bulletin 90–25–012, Issue 5, 

dated March 19, 2004, corrects the 

effectivity, and have removed seat series 

91C3 from paragraph (c) of this AD. 

No Reporting Requirement 

We removed paragraph (g)(3) of the 

NPRM from this final rule because 

reporting findings is not required. 

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 


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Federal Register / Vol. 76, No. 63 / Friday, April 1, 2011 / Rules and Regulations 18021 

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. 

Explanation of Change to Costs of 

Compliance 

Since issuance of the NPRM, we have 

increased the labor rate used in the 

Costs of Compliance from $80 per workhour to $85 per work-hour. The Costs of 

Compliance information, below, reflects 

this increase in the specified hourly 

labor rate. 

Costs of Compliance 

We estimate that this AD will affect 

70,073 seats on 163 products of U.S. 

registry. We also estimate that it will 

take 1 work-hour per product to comply 

with the basic requirements of this AD. 

The average labor rate is $85 per workhour. Required parts will cost about $0 

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 

$5,956,205, or $85 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 

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 

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. 

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, 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: 

2011–07–05 Sicma Aero Seat: Amendment 

39–16642. Docket No. FAA–2010–0027; 

Directorate Identifier 2008–NM–204–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective May 6, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Sicma Aero Seats 

9140, 9166, 9173, 9174, 9184, 9188, 9196, 

91B7, 91B8, 91C0, 91C2, 91C4, 91C5, and 

9301 series passenger seat assemblies; and 

Sicma Aero Seats 9501311–05, 9501301–06, 

9501311–15, 9501301–16, 9501441–30, 

9501441–33, 9501311–55, 9501301–56, 

9501441–83, 9501441–95, 9501311–97, and 

9501301–98 passenger seat assemblies; 

identified in Annex 1, Issue 2, dated March 

19, 2004, of Sicma Aero Seat Service Bulletin 

90–25–012, Issue 5, dated March 19, 2004; 

that have backrest links 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. 

TABLE 1—CERTAIN AFFECTED MODELS

Manufacturer Model 

Airbus .......... A330–200 and –300 Series 

Airplanes. 

Airbus .......... A340–200, –300, –500, and 

–600 Series Airplanes. 

The Boeing 

Company.

777–200, –300, –300ER, and 

–200LR Series 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 seat backrest 

links P/N (part numbers) 90–000200–104–1 

and 90–000200–104–2. These cracks can 

significantly affect the structural integrity of 

seat backrests. Therefore a life limit is 

introduced on the links. On 9g seats also 

affected by this problem, stronger unlimited 

life limits have been developed and their 

installation has been rendered mandatory. 


jlentini on DSKJ8SOYB1PROD with RULES
18022 Federal Register / Vol. 76, No. 63 / Friday, April 1, 2011 / Rules and Regulations 

However, on 16g seats the affected links have 

a direct influence on certification dynamic 

tests and cannot be replaced by similar 

stronger links without performing again all 

dynamic tests for each seat part number. 

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 links if cracking is found, and eventual 

replacement of all links with new links. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) At the later of the times specified in 

paragraphs (f)(1)(i) and (f)(1)(ii) of this AD, 

do a general visual inspection for cracking of 

the backrest links, P/Ns 90–000200–104–1 

and 90–000200–104–2, in accordance with 

Part One, ‘‘Checking Procedure,’’ of Sicma 

Aero Seat Service Bulletin 90–25–012, Issue 

5, 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– 

012, Issue 5, 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 backrest links having the same part 

number (P/N 90–000200–104–1 or 90– 

000200–104–2), in accordance with Part 

Two, ‘‘Replacement Procedure,’’ of Sicma 

Aero Seat Service Bulletin 90–25–012, Issue 

5, 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 90–25–012, Issue 5, dated March 19, 

2004): Before further flight, replace both 

backrest links of the affected seat with new 

backrest links having the same part numbers 

(P/N 90–000200–104–1 or 90–000200–104– 

2), in accordance with Part Two, 

‘‘Replacement Procedure,’’ of Sicma Aero Seat 

Service Bulletin 90–25–012, Issue 5, dated 

March 19, 2004. 

(4) If no cracking is found during the 

inspection required by paragraph (f)(1) of this 

AD: At the later of the times specified in 

paragraphs (f)(4)(i) and (f)(4)(ii) of this AD, 

replace the links, P/Ns 90–000200–104–1 and 

90–000200–104–2, with new backrest links 

having the same part numbers (P/N 90– 

000200–104–1 or 90–000200–104–2), in 

accordance with Part Two, ‘‘Replacement 

Procedure,’’ of Sicma Aero Seat Service 

Bulletin 90–25–012, Issue 5, dated March 19, 

2004. 

(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. 

(5) Actions done before the effective date 

of this AD in accordance with Sicma Aero 

Seat Service Bulletin 90–25–012, Issue 3, 

dated October 3, 2001; and Sicma Aero Seat 

Service Bulletin 90–25–012, Issue 4, dated 

December 19, 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 required time for replacing those 

links. This AD requires replacement of the 

link before 12,000 flight hours since new, or 

within 900 flight hours or 5 months after 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, MA 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 2001–605(AB), dated December 12, 

2001; and Sicma Aero Seat Service Bulletin 

90–25–012, Issue 5, dated March 19, 2004; 

for related information. 

Material Incorporated by Reference 

(i) You must use Sicma Aero Seat Service 

Bulletin 90–25–012, Issue 5, 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@sicma.zodiac.com; Internet 

http://www.sicma.zodiac.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 March 

14, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–6628 Filed 3–31–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0958; Directorate 

Identifier 2010–NM–188–AD; Amendment 

39–16641; AD 2011–07–04] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model DC–9–14, DC–9–15, 

and DC–9–15F Airplanes; and DC–9– 

20, DC–9–30, DC–9–40, and DC–9–50 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD requires 

installing new in-line fuses for the fuel 

level float switch and new in-line fuses 

for the pressure switch, as applicable, 

and changing the wiring. The proposed 

actions would affect the left and right 

wing forward spars, center wing forward 

spar, forward auxiliary fuel tank, and aft 

auxiliary fuel tank, as applicable. This 

AD was prompted by fuel system 

reviews conducted by the manufacturer. 

We are issuing this AD to prevent the 

potential of ignition sources inside fuel 

tanks, which, in combination with 

flammable fuel vapors, could result in 

fuel tank explosions and consequent 

loss of the airplane. 

DATES: This AD is effective May 6, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 


jlentini on DSKJ8SOYB1PROD with RULES