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 


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3148 Federal Register / Vol. 75, No. 12 / Wednesday, January 20, 2010 / Rules and Regulations 

states that accomplishing the repair 

specified in paragraph (k) of the 

proposed AD terminates the repetitive 

inspections required by paragraph (g). 

Boeing therefore requests that we revise 

paragraph (g) of the proposed AD to also 

refer to paragraph (k) as a terminating 

action. 

We partially agree. The repetitive 

inspections are terminated after 

accomplishment of paragraph (k) or (l) 

of this AD, but only at the stringer 

locations that are modified or repaired. 

We have revised paragraphs (g), (i), (j), 

and (l) of this final rule accordingly. 

Explanation of Changes Made to This 

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 have carefully reviewed the 

available data, including the comment 

that has been received, and determined 

that air safety and the public interest 

require adopting the AD with the 

changes described previously. We have 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Costs of Compliance 

There are about 246 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. 

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspection (required by AD 

2005–15–08).

3 $80 $240 per inspection cycle 69 $16,560 per inspection cycle. 

Inspection required by this 

AD.

3 $80 $240 per inspection cycle 70 $16,800 per inspection cycle. 

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 have 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 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); 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. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–14197 (70 

FR 43020, July 26, 2005) and by adding 

the following new airworthiness 

directive (AD): 

2010–01–02 The Boeing Company: 

Amendment 39–16158. Docket No. 

FAA–2009–0636; Directorate Identifier 

2009–NM–031–AD. 

Effective Date 

(a) This AD becomes effective February 24, 

2010. 

Affected ADs 

(b) This AD supersedes AD 2005–15–08, 

Amendment 39–14197. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 747–100B SUD, –200B, 

–300, –400, and –400D series airplanes, 

certificated in any category; as identified in 

Boeing Service Bulletin 747–53A2484, 

Revision 1, dated February 12, 2009. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from findings of 

cracking in fuselage stringers 8L, 8R, 10L, 

and 10R at body station 460, 480, and 500 

frame locations. We are issuing this AD to 

detect and correct fatigue cracking in the 

specified 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. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Requirements of AD 2005–15–08 

Inspection for Certain Airplanes Subject to 

AD 2005–15–08 With New Service Bulletin 

(g) For airplanes identified in Boeing Alert 

Service Bulletin 747–53A2484, dated June 

26, 2003, except airplanes identified in 

paragraph (j) of this AD, do a detailed 

inspection for cracking in fuselage stringers 


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Federal Register / Vol. 75, No. 12 / Wednesday, January 20, 2010 / Rules and Regulations 3149 

8L, 8R, 10L, and 10R at body station 460, 

480, and 500 frame locations, in accordance 

with Part 1 of the Accomplishment 

Instructions in Boeing Alert Service Bulletin 

747–53A2484, dated June 26, 2003; or Boeing 

Service Bulletin 747–53A2484, Revision 1, 

dated February 12, 2009. Do the inspections 

at the applicable time specified in paragraph 

(g)(1) or (g)(2) of this AD. Repeat the 

inspection thereafter at intervals not to 

exceed 3,000 flight cycles until the 

requirements of paragraph (k) or (l) of this 

AD are accomplished. No further action is 

required by this AD for any stringer that is 

repaired or modified in accordance with 

paragraph (k) or (l) of this AD. After the 

effective date of this AD, use only Boeing 

Service Bulletin 747–53A2484, Revision 1, 

dated February 12, 2009. 

(1) For airplanes with 19,000 total flight 

cycles or less as of August 30, 2005 (the 

effective date of AD 2005–15–08): Prior to the 

accumulation of 8,000 total flight cycles, or 

within 2,000 flight cycles after August 30, 

2005, whichever is later, not to exceed 20,000 

total flight cycles. 

(2) For airplanes with more than 19,000 

total flight cycles as of August 30, 2005: 

Within 1,000 flight cycles after August 30, 

2005. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’ 

New Requirements of This AD 

Inspection: Variable Number RS699 

(h) For Model 747 airplane variable 

number RS699, do a detailed inspection for 

cracking in fuselage stringers 8L, 8R, 10L, 

and 10R at body station 460, 480, and 500 

frame locations, in accordance with Boeing 

Service Bulletin 747–53A2484, Revision 1, 

dated February 12, 2009, at the later of the 

times specified in paragraphs (h)(1) and 

(h)(2) of this AD. 

(1) Before the accumulation of 8,000 total 

flight cycles. 

(2) Within 2,000 flight cycles after the 

effective date of this AD. 

(i) For Model 747 airplane variable number 

RS699, repeat the inspection specified in 

paragraph (h) of this AD thereafter at 

intervals not to exceed 3,000 flight cycles 

until the actions specified in paragraph (k) or 

(l) of this AD are accomplished. No further 

action is required by this AD for any stringer 

that is repaired or modified in accordance 

with paragraph (k) or (l) of this AD. 

Inspection: Group 4 Airplanes 

(j) For Group 4 airplanes as identified in 

Boeing Service Bulletin 747–53A2484, 

Revision 1, dated February 12, 2009, do a 

detailed inspection for cracking in fuselage 

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

460, 480, and 500 frame locations, within 

1,000 flight cycles after the effective date of 

this AD. Do the actions in accordance with 

Boeing Service Bulletin 747–53A2484, 

Revision 1, dated February 12, 2009. Repeat 

the inspection thereafter at intervals not to 

exceed 1,500 flight cycles until the actions 

specified in paragraph (k) or (l) of this AD are 

accomplished. No further action is required 

by this AD for any stringer that is repaired 

or modified in accordance with paragraph (k) 

or (l) of this AD. 

Repair 

(k) If cracking is found during any 

inspection required by this AD: Before 

further flight, repair the affected stringer in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2484, dated June 

26, 2003; or Boeing Service Bulletin 747– 

53A2484, Revision 1, dated February 12, 

2009. After the effective date of this AD, use 

only Boeing Service Bulletin 747–53A2484, 

Revision 1, dated February 12, 2009. 

Accomplishing the repair terminates the 

repetitive inspections required by this AD for 

that repaired stringer location only. 

Optional Terminating Action 

(l) Installing new frame clips and new 

doublers, and repairing as applicable, in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2484, dated June 

26, 2003; or Boeing Service Bulletin 747– 

53A2484, Revision 1, dated February 12, 

2009; terminates the repetitive inspections 

required by this AD for that modified stringer 

only. After the effective date of this AD, use 

only Boeing Service Bulletin 747–53A2484, 

Revision 1, dated February 12, 2009. 

Alternative Methods of Compliance (AMOCs) 

(m)(1) The Manager, Seattle ACO, 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: 

Ivan Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, Seattle Aircraft 

Certification Office (ACO), FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

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

917–6590; or e-mail information to 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane. 

(4) AMOCs approved previously in 

accordance with AD 2005–15–08, are 

approved as AMOCs for the corresponding 

provisions of this AD. 

Material Incorporated by Reference 

(n) You must use Boeing Alert Service 

Bulletin 747–53A2484, dated June 26, 2003; 

and Boeing Service Bulletin 747–53A2484, 

Revision 1, dated February 12, 2009; as 

applicable; 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 

Boeing Service Bulletin 747–53A2484, 

Revision 1, dated February 12, 2009, under 

5 U.S.C. 552(a) and 1 CFR part 51. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of Boeing Alert Service Bulletin 

747–53A2484, dated June 26, 2003, on 

August 30, 2005 (70 FR 43020, July 26, 2005). 

(3) 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. 

(4) 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. 

(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 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 

December 17, 2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–30970 Filed 1–19–10; 8:45 am] 

BILLING CODE 4910–13–P 


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