11538 Federal Register / Vol. 73, No. 43 / Tuesday, March 4, 2008 / Rules and Regulations 

Actions Compliance Procedures 

Remove, modify, and reinstall the crew seats ... Within the next 50 hours time-in-service after 

April 8, 2008 (the effective date of this AD) 

or within the next 6 months after April 8, 

2008 (the effective date of this AD), whichever occurs first.

Follow Cessna Aircraft Company Single Engine Modification Kit No. MK206–25–10, 

dated April 23, 2007, as specified in 

Cessna Aircraft Company Service Bulletin 

SB07–25–04, dated April 23, 2007. 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Wichita 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: Gary Park, 

Aerospace Engineer, 1801 Airport Road, 

Room 100, Wichita, Kansas 67209; telephone: 

(316) 946–4123; fax: (316) 946–4107. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

Related Information 

(g) To get copies of the service information 

referenced in this AD, contact Cessna Aircraft 

Company, Product Support, P.O. Box 7706, 

Wichita, Kansas 67277; telephone: (316) 517–

5800; fax: (316) 942–9006. To view the AD 

docket, go to U.S. Department of 

Transportation, Docket Operations, M–30, 

West Building Ground Floor, Room W12–

140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, or on the Internet at 

http://dms.dot.gov. The docket number is 

Docket No. FAA–2007–28433; Directorate 

Identifier 2007–CE–052–AD. 

Material Incorporated by Reference 

(h) You must use Cessna Aircraft Company 

Single Engine Modification Kit No. MK206–

25–10, dated April 23, 2007, as specified in 

Cessna Aircraft Company Service Bulletin 

SB07–25–04, dated April 23, 2007, 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 Cessna Aircraft Company, 

Product Support, P.O. Box 7706, Wichita, 

Kansas 67277; telephone: (316) 517–5800; 

fax: (316) 942–9006. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Kansas City, Missouri 

64106; or 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 Kansas City, Missouri, on 

February 22, 2008. 

Patrick R. Mullen, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–3771 Filed 3–3–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–0224; Directorate 

Identifier 2007–NM–188–AD; Amendment 

39–15400; AD 2008–05–06] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–100, –200, –300, –400, and 

–500 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 737–100, –200, –300, 

–400, and –500 series airplanes. This 

AD requires repetitive inspections for 

fatigue cracking in the longitudinal floor 

beam web, upper chord, and lower 

chord located at certain body stations, 

and repair if necessary. This AD results 

from several reports of cracks in the 

center wing box longitudinal floor 

beams, upper chord, and lower chord. 

We are issuing this AD to detect and 

correct fatigue cracking of the upper and 

lower chords and web of the 

longitudinal floor beams, which could 

result in rapid loss of cabin pressure. 

DATES: This AD is effective April 8, 

2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 8, 2008. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. 

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: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6440; fax (425) 917–6590. 

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 

certain Boeing Model 737–100, –200, 

–300, –400, and –500 series airplanes. 

That NPRM was published in the 

Federal Register on November 26, 2007 

(72 FR 65911). That NPRM proposed to 

require repetitive inspections for fatigue 

cracking in the longitudinal floor beam 

web, upper chord, and lower chord 

located at certain body stations, and 

repair if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Boeing, the single commenter, supports 

the NPRM. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

There are 2,852 airplanes of the 

affected design in the worldwide fleet. 

This AD affects 652 airplanes of U.S. 

registry. The required inspection takes 

approximately 13 work hours per 

airplane, at an average labor rate of $80 

per work hour. Based on these figures, 

the estimated cost of the required 

inspection for U.S. operators is 

$678,080, or $1,040 per airplane, 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, 


rwilkins on PROD1PC63 with RULES
Federal Register / Vol. 73, No. 43 / Tuesday, March 4, 2008 / Rules and Regulations 11539 

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), 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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

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: 

2008–05–06 Boeing: Amendment 39–15400. 

Docket No. FAA–2007–0224; Directorate 

Identifier 2007–NM–188–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective April 8, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 737–

100, –200, –300, –400, and –500 series 

airplanes, certificated in any category; as 

identified in Boeing Service Bulletin 737–57–

1296, dated June 13, 2007. 

Unsafe Condition 

(d) This AD results from several reports of 

cracks in the center wing box longitudinal 

floor beams, upper chord, and lower chord. 

We are issuing this AD to detect and correct 

fatigue cracking of the upper and lower 

chords and web of the longitudinal floor 

beams, which could result in rapid loss of 

cabin pressure. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Repetitive Inspections 

(f) Do the various inspections for fatigue 

cracks in the longitudinal floor beam web, 

upper chord, and lower chord, located at the 

applicable body stations specified in the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–57–1296, dated June 13, 

2007, by doing all the actions specified in the 

Accomplishment Instructions of the service 

bulletin, except as provided by paragraph (g) 

of this AD. Do the inspections at the time 

specified in paragraph (f)(1) or (f)(2) of this 

AD, as applicable. 

(1) For Groups 1 and 2 airplanes as 

identified in the service bulletin: Do the 

inspections at the applicable initial 

compliance time listed in paragraph 1.E., 

‘‘Compliance,’’ of the service bulletin; except, 

where the service bulletin specifies a 

compliance time after the date on the service 

bulletin, this AD requires compliance within 

the specified compliance time after the 

effective date of this AD. Repeat the 

inspections thereafter at the intervals 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

the service bulletin. 

(2) For Group 3 airplanes as identified in 

the service bulletin: Do the inspections at the 

applicable initial compliance time listed in 

paragraph 1.E., ‘‘Compliance,’’ of the service 

bulletin; except, where the service bulletin 

specifies a compliance time after the date on 

the service bulletin, this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

Repeat the inspections thereafter at the 

intervals specified in paragraph 1.E., 

‘‘Compliance,’’ of the service bulletin. 

(g) If any crack is found during any 

inspection required by this AD, and Boeing 

Service Bulletin 737–57–1296, dated June 13, 

2007, specifies contacting Boeing for repair 

instructions: Before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (h) of 

this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Seattle Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

(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 appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(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. 

Material Incorporated by Reference 

(i) You must use Boeing Service Bulletin 

737–57–1296, dated June 13, 2007, 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, P.O. Box 3707, Seattle, 

Washington 98124–2207. 

(3) You may review copies of the service 

information incorporated by reference at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington; or 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 February 

20, 2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–3810 Filed 3–3–08; 8:45 am] 

BILLING CODE 4910–13–P 


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