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 


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Federal Register / Vol. 76, No. 63 / Friday, April 1, 2011 / Rules and Regulations 18023 

of a certain publication listed in the AD 

as of May 6, 2011. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, California 90846–0001; 

telephone 206–544–5000, extension 2; 

fax 206–766–5683; e-mail 

dse.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

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 FURTHER INFORMATION CONTACT: 

Samuel Lee, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, 

Los Angeles Aircraft Certification 

Office, 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

phone: 562–627–5262; fax: 562–627– 

5210, e-mail: Samuel.Lee@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to the 

specified products. That NPRM 

published in the Federal Register on 

October 8, 2010 (75 FR 62331). That 

NPRM proposed to require 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request Revision of FAA AD 2008–11– 

15 

Aeropostal requested that we issue 

this AD as a revision to existing AD 

2008–11–15. Aeropostal stated that the 

requirement of installing fuses in the 

proposed AD is incorporated by Boeing 

Critical Design Configuration Control 

Limitation (CDCCL) 20–13 of Twinjet 

Special Compliance Items Report, 

MDC–92K9145, Revision J, dated 

January 26, 2010. 

We disagree with the request to revise 

AD 2008–11–15. AD 2008–11–15 

requires incorporation of Boeing 

Twinjet Special Compliance Items 

Report, MDC–92K9145, Revision G, 

dated June 7, 2007, which does not 

include CDCCL 20–13. This proposed 

AD does not require incorporating 

CDCCL 20–13. This AD requires the 

installation of new in-line fuses for the 

fuel level float switch and new in-line 

fuses for the pressure switch. We might 

consider future rulemaking to revise AD 

2008–11–15 to include CDCCL 20–13. 

No change has been made to AD 2008– 

11–15 or this AD in this regard. 

Request for Clarification 

Aeropostal requested clarification 

concerning the NPRM and whether it 

will satisfy the requirements of AD 

2008–11–15. 

We agree that clarification is needed. 

AD 2008–11–15 requires revising the 

maintenance program or the 

Airworthiness Limitations (AWL) 

section of the Instructions for Continued 

Airworthiness to incorporate new AWLs 

for fuel tank systems, in accordance 

with Boeing Twinjet Special 

Compliance Items Report, MDC– 

92K9145, Revision G, dated June 7, 

2007. This AD has different 

requirements including the installation 

of new in-line fuses for the fuel level 

float switch and new in-line fuses for 

the pressure switches. No change has 

been made to this AD in this regard. 

Explanation of Change Made to the AD 

We have revised this AD to identify 

the legal name of the manufacturer as 

published in the most recent type 

certificate data sheet for the affected 

airplane models. 

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 change described previously. 

We have determined that this change: 

• Is consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Does not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that this change 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Costs of Compliance 

We estimate that this AD affects 275 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Installation .... Up to 17 work-hours × $85 

per hour = Up to $1,4451.

Between $289 and $1,4491 ... Between $1,734 and $2,8941 Between $476,850 and 

$795,850.1

1 Depending on airplane group as identified in Boeing Service Bulletin DC9–28–217, Revision 1, dated August 12, 2010. 

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 


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18024 Federal Register / Vol. 76, No. 63 / Friday, April 1, 2011 / Rules and Regulations 

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. 

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 airworthiness 

directive (AD): 

2011–07–04 The Boeing Company: 

Amendment 39–16641; Docket No. 

FAA–2010–0958; Directorate Identifier 

2010–NM–188–AD. 

Effective Date 

(a) This AD is effective May 6, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 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–9–32F (C–9A), DC– 

9–32F (C9–B), DC–9–33F, DC–9–34, DC–9– 

34F, DC–9–41, and DC–9–51 airplanes, 

certificated in any category; as identified in 

Boeing Service Bulletin DC9–28–217, 

Revision 1, dated August 12, 2010. 

Subject 

(d) Joint Aircraft System Component 

(JASC)/Air Transport Association (ATA) of 

America Code 28: Fuel. 

Unsafe Condition 

(e) 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. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Installation 

(g) Within 60 months after the effective 

date of this AD: Install new in-line fuses for 

the fuel level float switch and new in-line 

fuses for the pressure switch, as applicable; 

and change the wiring; on the left and right 

wing forward spars, center wing forward 

spar, forward auxiliary fuel tank, and aft 

auxiliary fuel tank, as applicable; in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin DC9– 

28–217, Revision 1, dated August 12, 2010. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) Actions done before the effective date 

of this AD in accordance with Boeing Service 

Bulletin DC9–28–217, dated December 1, 

2009, are acceptable for compliance with the 

requirements of paragraph (g) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Los Angeles Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. 

Related Information 

(j) For more information about this AD, 

contact Samuel Lee, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, Los 

Angeles ACO, 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; phone: 

562–627–5262; fax: 562–627–5210; e-mail: 

Samuel.Lee@faa.gov. 

Material Incorporated by Reference 

(k) You must use Boeing Service Bulletin 

DC9–28–217, Revision 1, dated August 12, 

2010, 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 Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, 3855 Lakewood Boulevard, MC 

D800–0019, Long Beach, California 90846– 

0001; telephone 206–544–5000, extension 2; 

fax 206–766–5683; e-mail 

dse.boecom@boeing.com; Internet https:// 

www.myboeingfleet.com. 

(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 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 March 

14, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–6633 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–2010–0436; Directorate 

Identifier 2009–NM–230–AD; Amendment 

39–16643; AD 2011–07–06] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model CL–600–2B19 (Regional Jet 

Series 100 & 440) 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: 

* * * There have recently been several inservice occurrences that have highlighted the 

inability of the existing [wing anti-ice] 

system to detect a low-heat condition in the 

wing leading edge at all times, with the 

potential consequence of unannunciated 

asymmetric ice build-up on the wing. * * * 


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