3144 Federal Register / Vol. 75, No. 12 / Wednesday, January 20, 2010 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27346; Directorate 

Identifier 2008–NM–205–AD; Amendment 

39–16176; AD 2010–02–06] 

RIN 2120–AA64 

Airworthiness Directives; Sicma Aero 

Seat 90xx and 92xx Series Passenger 

Seats, Installed on, But Not Limited to 

ATR—GIE Avions de Transport 

Re ́gional Model ATR42 Airplanes and 

Model ATR72 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 in central 

spreaders P/N [part number] 92–000100– 

200–1 or P/N 92–000101–200–1. This may 

heavily affect the structural integrity of the 

seat. 

Failure of the central spreaders could 

result in injury to an occupant during 

emergency conditions. We are issuing 

this AD to require actions to correct the 

unsafe condition on these products. 

DATES: This AD becomes effective 

February 24, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 24, 2010. 

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 and Propeller Directorate, 12 

New England Executive Park, 

Burlington, Massachusetts 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 April 6, 2007 (72 FR 17045). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Cracks have been found in central 

spreaders P/N [part number] 92–000100– 

200–1 or P/N 92–000101–200–1. This may 

heavily affect the structural integrity of the 

seat. 

Failure of the central spreaders could 

result in injury to an occupant during 

emergency conditions. The required 

actions include repetitive visual 

inspections for cracking of central 

spreaders; replacement with new central 

spreaders if cracking is found; and 

eventual installation of doublers. 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 Change Costs of Compliance 

Section 

Sicma Aero Seat (Sicma) states that 

the Costs of Compliance section of the 

NPRM reflects that many of the seats 

were addressed due to the MCAI issued 

in 2002 (reference Direction Ge ́ne ́rale de 

l’Aviation Civile Airworthiness 

Directive 2002–504 (AB), effective 

October 12, 2002). Sicma also states that 

there were a low number of ATR Model 

ATR42 and ATR72 airplanes with 

Sicma seats operating in the United 

States at that time. Sicma notes that the 

NPRM gives an incorrect impression of 

the extent of the issue. In addition, 

Airbus states that it is surprised by the 

figures in the Costs of Compliance 

section of the NPRM. Airbus notes that 

the quantity of seats specified in the 

NPRM represent 10 airplanes and that 

Sicma provided 1,029 kits for doing 

Sicma Aero Seat Service Bulletin 92– 

25–005, Issue 3, dated January 17, 2003 

(an equivalent of eight airplanes). 

We infer that the commenters request 

we change the Costs of Compliance 

section. We agree to change the Costs of 

Compliance section of this AD. We 

reevaluated the number of seats in the 

U.S. fleet that may be affected and 

reduced our initial estimate of 3,283 

seat assemblies specified in the NPRM 

to 1,403 seat assemblies. We have 

modified the Costs of Compliance 

section in this AD accordingly to 

accurately represent the current number 

of affected airplanes on the U.S. registry. 

Request To Include Previous Issues of 

Service Bulletins as Alternative 

Methods of Compliance 

Airbus requests that we include 

previous versions of Sicma Aero Seat 

Service Bulletin 92–25–005, Issue 3, 

dated January 17, 2003, as alternative 

methods of compliance to this AD. 

Airbus notes that the changes to the 

original issue of Sicma Aero Seat 

Service Bulletin 92–25–005, dated July 

17, 2002, have been to add an appendix 

that lists part numbers, add the 

estimated time for installation of the kit, 

and add details of the installation of the 

kit for each of the types of the kits. 

We partially agree. In addition to the 

changes described by the commenter, 

Issue 1 of Sicma Aero Seat Service 

Bulletin 92–25–005, dated August 29, 

2002, made changes to the description 

of the appropriate actions in Part One of 

the Accomplishment Instructions of the 

service bulletin. The findings and 

corresponding corrective actions 

specified in Sicma Aero Seat Service 

Bulletins 92–25–005, dated July 17, 

2002, are different than those described 

in Issue 1 and subsequent issues of the 

service bulletin. Therefore, only Issue 1 

and Issue 2 are acceptable additional 

methods of compliance for the actions 

required by this AD. We have added 

paragraph (f)(3) of this AD to give credit 

for actions done in accordance with 

Sicma Aero Seat Service Bulletins 92– 

25–005, Issue 1, dated August 29, 2002; 

and Issue 2, dated October 29, 2002. 

Request To Clarify the Applicability 

Airbus also requests that we clarify 

the applicability of the NPRM. Airbus 

notes that the seats listed in the 

appendix (annex) of Sicma Aero Seat 

Service Bulletin 92–25–005, Issue 3, 

dated January 17, 2003, concern ATR 

Model ATR42 and ATR72 airplanes and 

not Airbus airplanes. 

We agree to clarify the applicability. 

The applicability of the NPRM specified 

90xx and 92xx series passenger seats but 

did not limit the seats to those specified 

in Sicma Aero Seat Service Bulletin 92– 

25–005, Issue 3, dated January 17, 2003. 

We have limited the applicability of this 

AD by specifying 90xx and 92xx series 

seat part numbers as listed in Sicma 

Aero Seat Service Bulletin 92–25–005, 

Issue 3, dated January 17, 2003, 

including Annex 1, dated July 17, 2002. 

We have also revised this AD to 

identify the correct legal name of the 

manufacturer of Model ATR42 and 

ATR72 airplanes as published in the 

most recent type certificate data sheet 

for the affected airplane models. 


pwalker on DSK8KYBLC1PROD with RULES
Federal Register / Vol. 75, No. 12 / Wednesday, January 20, 2010 / Rules and Regulations 3145 

Compliance Time Change 

We have replaced the compliance 

time ‘‘before March 31, 2010’’ for the 

installation specified in paragraph (e)(3) 

of the NPRM with ‘‘Within 24 months 

after the effective date of this AD’’ in 

paragraph (f)(2) of this AD (which 

corresponds to paragraph (e)(3) of the 

NPRM). We have also revised Note 2 of 

this AD to refer to the new compliance 

time. In developing an appropriate 

compliance time, we considered the 

safety implications and the normal 

maintenance schedules for timely 

accomplishment of the installation. We 

have determined that extending the 

compliance time will not adversely 

affect safety. 

Clarification of Terminating Action 

We have revised the sentence 

requiring repetitive inspections in 

paragraph (f)(1) of this AD by adding the 

phrase ‘‘until a new central spreader, P/ 

N 92–000100–200–1 or P/N 92–000101– 

200–1, and doublers, P/N 00–6536, are 

installed in accordance with ‘Part Three: 

Central Spreader Replacement’ of the 

service bulletin.’’ Installation of the 

central spreader and doublers 

terminates the repetitive inspections. 

We have also revised the wording in 

paragraph (f)(2) of this AD to clarify the 

terminating action. 

Change to Directorate Identifier 

Number 

The Engine and Propeller Directorate 

issued the NPRM for this AD and 

assigned Directorate Identifier 2007– 

NE–07–AD to the NPRM. Because the 

final rule is being issued by the 

Transport Airplane Directorate, we have 

re-assigned Directorate Identifier 2008– 

NM–205–AD to this AD and revised the 

directorate identifier references in the 

AD accordingly. 

New Subject Paragraph and Note 

We have added the Air Transport 

Association (ATA) of America Code 

identifying the subject of this AD to new 

paragraph (d) of this AD and revised the 

subsequent paragraph identifiers 

accordingly. We have also added Note 1 

to this AD to clarify that when certain 

conditions exist, it is necessary to 

request approval of an alternative 

method of compliance. 

Revision to Reason, FAA Difference, 

and Other FAA AD Provisions 

Paragraphs 

To match the template specified in 

FAA Order 8040.5, we have added the 

phrase ‘‘The mandatory continuing 

airworthiness information (MCAI) 

states’’ before the quoted material in 

paragraph (e) of this AD, removed 

paragraph (f) of the NPRM, and added 

Note 2 to this AD. Note 2 of this AD 

includes the same information as 

paragraph (f) of the NPRM. We have also 

added paragraphs (g)(2) and (g)(3) to this 

AD. 

Changes to Other Paragraphs in the 

NPRM 

We have moved the text specified in 

paragraph (e)(2) of the NPRM into 

paragraph (f)(1) of this AD, and we have 

reidentified paragraph (e)(3) of the 

NPRM as paragraph (f)(2) of this AD. We 

have also made minor editorial changes 

to paragraphs (f)(1), (f)(1)(i), (f)(1)(ii), 

and (f)(1)(iii) of this AD. 

Changes to Service Bulletin References 

We have revised the service bulletin 

references in paragraphs (f)(1), (f)(1)(i), 

(f)(1)(ii), (f)(1)(iii), and (f)(2) of this AD 

to specify where each action is 

described in the relevant service 

bulletin. 

Clarification of Compliance Time 

We have added the phrase ‘‘before 

further flight’’ to paragraph (f)(1)(iii) of 

this AD to clarify the compliance time 

for doing the temporary repair and for 

doing the installation after removing the 

temporary repair. 

We have also added the phrase ‘‘after 

accomplishing the inspection’’ to 

paragraph (f)(1)(i) of this AD to clarify 

the compliance time for doing the check 

specified in paragraph (f)(1)(i) 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 

1,403 seat assemblies on 105 airplanes 

of U.S. registry. We also estimate that it 

will take about 6 work-hours per seat 

assembly to comply with the basic 

requirements of this AD. The average 

labor rate is $80 per work-hour. 

Required parts will cost about $207 per 

seat assembly. 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 

$963,861, or $687 per seat assembly. 

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. 


pwalker on DSK8KYBLC1PROD with RULES
3146 Federal Register / Vol. 75, No. 12 / Wednesday, January 20, 2010 / Rules and Regulations 

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, 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: 

2010–02–06 Sicma Aero Seat: Amendment 

39–16176. Docket No. FAA–2007–27346; 

Directorate Identifier 2008–NM–205–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective February 24, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Sicma Aero Seat 

90xx and 92xx series passenger seats with 

part numbers (P/Ns) listed in Annex 1, dated 

July 17, 2002, of Sicma Aero Seat Service 

Bulletin 92–25–005, Issue 3, dated January 

17, 2003. These products are installed on, but 

not limited to, ATR—GIE Avions de 

Transport Re ́gional Model ATR42–200, –300, 

–320, and –500 airplanes, and Model 

ATR72–101, –201, –102, –202, –211, –212, 

and –212A airplanes; certificated in any 

category. 

Note 1: This AD applies to certain Sicma 

Aero Seat passenger seats 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) 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 in central 

spreaders P/N 92–000100–200–1 or P/N 92– 

000101–200–1. This may heavily affect the 

structural integrity of the seat. 

Failure of the central spreaders could 

result in injury to an occupant during 

emergency conditions. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within 500 flight hours after the 

effective date of this AD, perform a visual 

inspection of central spreaders, P/N 92– 

000100–200–1 and P/N 92–000101–200–1, of 

the affected seats using the Accomplishment 

Instructions, ‘‘Part One: Checking Procedure,’’ 

of Sicma Aero Seat Service Bulletin 92–25– 

005, Issue 3, dated January 17, 2003 (‘‘the 

service bulletin’’). If no crack is found, repeat 

this inspection at intervals not exceeding 500 

flight hours until a new central spreader, P/ 

N 92–000100–200–1 or P/N 92–000101–200– 

1, and doublers, P/N 00–6536, are installed 

in accordance with ‘‘Part Three: Central 

Spreader Replacement’’ of the service 

bulletin. Type 1, 2, and 3 cracks are defined 

in the Accomplishment Instructions, ‘‘Part 

One: Checking Procedure,’’ of the service 

bulletin. 

(i) If a type 1 crack is found, within 6 

months or 500 flight hours after 

accomplishing the inspection, whichever 

comes first, check the crack to determine that 

it did not enlarge to a type 2 or type 3 crack 

by using the Accomplishment Instructions, 

‘‘Part One: Checking Procedure,’’ of the 

service bulletin; install doublers, P/N 00– 

6536, by using the Accomplishment 

Instructions, ‘‘Part Two: Central Spreader 

Modification,’’ of the service bulletin, and 

record this modification by using ‘‘B—Seat 

identification’’ of the Accomplishment 

Instructions, ‘‘Part One: Checking Procedure,’’ 

of the service bulletin. 

(ii) If a type 2 or 3 crack is found, before 

further flight, replace the affected central 

spreader with a new one with the same part 

number, equipped with doublers, P/N 00– 

6536, by using the Accomplishment 

Instructions, ‘‘Part Three: Central Spreader 

Replacement,’’ of the service bulletin. 

(iii) If a new spreader is unavailable, before 

further flight, do a temporary repair by 

installing doublers, P/N 00–6536, by using 

the Accomplishment Instructions, ‘‘Part Two: 

Central Spreader Modification,’’ of the service 

bulletin. This temporary repair may remain 

in place no longer than 500 flight hours or 

six months, whichever comes first. After 

removing the temporary repair, before further 

flight, install a new spreader with the same 

P/N equipped with doublers, P/N 00–6536, 

by using the Accomplishment Instructions, 

‘‘Part Three: Central Spreader Replacement,’’ 

of the service bulletin, and record this 

modification by following the instructions in 

‘‘B—Seat identification’’ of the 

Accomplishment Instructions, ‘‘Part Three: 

Central Spreader Replacement,’’ of the service 

bulletin. 

(2) If not already done, within 24 months 

after the effective date of this AD, install 

doublers, P/N 00–6536, on new central 

spreaders of affected seats by using the 

Accomplishment Instructions, ‘‘Part Three: 

Central Spreader Replacement,’’ of Sicma 

Aero Seat Service Bulletin 92–25–005, Issue 

3, dated January 17, 2003 (‘‘the service 

bulletin’’). Record this modification by 

following instructions in ‘‘B—Seat 

identification’’ of the Accomplishment 

Instructions, ‘‘Part Three: Central Spreader 

Replacement,’’ of the service bulletin. 

Installing a new central spreader P/N 92– 

000100–200–1 or 92–000101–200–1, and 

doublers, P/N 00–6536 on all affected seats 

terminates the requirements of this AD. 

(3) Actions accomplished before the 

effective date of this AD in accordance with 

Sicma Aero Seat Service Bulletin 92–25–005, 

Issue 1, dated August 29, 2002; and Issue 2, 

dated October 29, 2002; are considered 

acceptable for compliance with the 

corresponding actions specified in this AD. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: The 

Direction Ge ́ne ́rale de l’Aviation Civile 

(DGAC) airworthiness directive 2002– 

504(AB), effective October 12, 2002, specifies 

that doublers, P/N 00–6536, be installed on 

central spreaders of affected seats by 

December 31, 2005. This AD requires the 

doublers to be installed within 24 months 

after the effective date of this AD. 

Other FAA AD Provisions 

(h) 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. 

Send information 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 on any airplane 

to which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards 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 


pwalker on DSK8KYBLC1PROD with RULES
Federal Register / Vol. 75, No. 12 / Wednesday, January 20, 2010 / Rules and Regulations 3147 

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, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI DGAC Airworthiness 

Directive 2002–504(AB), effective October 12, 

2002; and Sicma Aero Seat Service Bulletin 

92–25–005, Issue 3, dated January 17, 2003, 

including Annex 1, dated July 17, 2002; for 

related information. 

(i) Contact Jeffrey Lee, Aerospace Engineer, 

Boston Aircraft Certification Office, FAA, 

Engine and Propeller Directorate; 12 New 

England Executive Park, Burlington, MA 

01803; telephone 781–238–7161; fax 781– 

238–7170, for more information about this 

AD. 

Material Incorporated by Reference 

(j) You must use Sicma Aero Seat Service 

Bulletin 92–25–005, Issue 3, dated January 

17, 2003, including Annex 1, dated July 17, 

2002, to do the actions required by this AD, 

unless the AD specifies otherwise. The Sicma 

Aero Seat service bulletin contains the 

following effective pages: 

Page No. 

Issue level 

shown on 

page 

Date shown on 

page 

1–30 ....... 3 ................ January 17, 2003. 

ANNEX 1 

1–3 ......... Original ...... July 17, 2002. 

(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 15 16; 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 or 425–227–1152. 

(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 January 

8, 2010. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–701 Filed 1–19–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0636; Directorate 

Identifier 2009–NM–031–AD; Amendment 

39–16158; AD 2010–01–02] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–100B SUD, 

–200B, –300, –400, and –400D Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Model 747– 

100B SUD, –200B, –300, –400, and 

–400D series airplanes. That AD 

currently requires repetitive inspections 

for cracking in fuselage stringers 8L, 8R, 

10L, and 10R at body stations 460, 480, 

and 500 frame locations; and repair if 

necessary. This new AD requires 

revising the applicability to include an 

additional airplane, and reduces 

compliance times for the initial 

inspection and repetitive intervals for 

Model 747–400 series airplanes that 

have been converted to the large cargo 

freighter configuration. This AD results 

from findings of cracking in fuselage 

stringers 8L, 8R, 10L, and 10R at body 

stations 460, 480, and 500 frame 

locations. We are issuing this AD to 

detect and correct fatigue cracking in 

certain fuselage stringers, which, if left 

undetected, could result in fuselage skin 

cracking that reduces the structural 

integrity of the skin panel, and 

consequent rapid depressurization of 

the airplane. 

DATES: This AD becomes effective 

February 24, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of February 24, 2010. 

The Director of the Federal Register 

previously approved the incorporation 

by reference of Boeing Alert Service 

Bulletin 747–53A2484, dated June 26, 

2003, as of August 30, 2005 (70 FR 

43020, July 26, 2005). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. 

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 (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, Seattle Aircraft 

Certification Office, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2005–15–08, amendment 

39–14197 (70 FR 43020, July 26, 2005). 

The existing AD applies to certain 

Model 747–100B SUD, –200B, –300, 

–400, and –400D series airplanes. That 

NPRM was published in the Federal 

Register on July 14, 2009 (74 FR 33928). 

That NPRM proposed to require 

repetitive inspections for cracking in 

fuselage stringers 8L, 8R, 10L, and 10R 

at body stations 460, 480, and 500 frame 

locations; and repair if necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment that has been 

received on the NPRM. 

Request for Change to Paragraph (g) of 

This AD 

Boeing requests a change to paragraph 

(g) of the NPRM. The NPRM proposes to 

require repeating the inspections 

specified in paragraph (g) at intervals 

not to exceed 3,000 flight cycles until 

the requirements of paragraph (l) of the 

proposed AD are accomplished. Boeing 


pwalker on DSK8KYBLC1PROD with RULES