Federal Register / Vol. 74, No. 149 / Wednesday, August 5, 2009 / Rules and Regulations 38901 

FAA, Rotorcraft Directorate, Regulations and 

Policy Group, 2601 Meacham Blvd., Fort 

Worth, Texas 76137; telephone (817) 222– 

5167; fax (817) 222–5961, has the authority 

to approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Related Information 

(h) MCAI Ente Nazionale Per L’Aviazione 

Civile Airworthiness Directive No. 2007–227, 

dated June 18, 2007, contains related 

information. 

Joint Aircraft System/Component (JASC) 

Code 

(i) JASC Code 2621: Fire Bottle, Fixed. 

Material Incorporated by Reference 

(j) You must use the specified portions of 

Agusta Bollettino Tecnico No. 139–085, 

dated May 18, 2007 to do the actions 

required. 

(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 Agusta, Via Giovanni 

Agusta, 520 21017 Cascina Costa di Samarate 

(VA), Italy, telephone 39 0331–229111, fax 39 

0331–229605/222595, or at http:// 

customersupport.agusta.com/ 

technical_advice.php. 

(3) You may review copies at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas; 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/ 

cfr/ibr-locations.html. 

Issued in Fort Worth, Texas, on July 10, 

2009. 

Larry M. Kelly, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–18430 Filed 8–4–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1213; Directorate 

Identifier 2007–NM–092–AD; Amendment 

39–15987; AD 2009–16–14] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–100, –200, –200C, –300, 

–400, and –500 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) 

that applies to certain Boeing Model 

737–100, –200, –200C, –300, –400, and 

–500 series airplanes. That AD currently 

requires repetitive inspections of the 

intercostal webs, attachment clips, and 

stringer splice channels for cracks; and 

corrective action if necessary. This new 

AD reduces the repetitive inspection 

intervals from 25,000 flight cycles to 

6,000 flight cycles, and expands the 

inspection area for Model 737–200C 

series airplanes to include the area aft 

of the forward entry door. This AD 

results from additional reports of fatigue 

cracks. We are issuing this AD to detect 

and correct fatigue cracking of the 

intercostals on the forward and aft sides 

of the forward entry door, which could 

result in loss of the forward entry door 

and rapid decompression of the 

airplane. 

DATES: This AD becomes effective 

September 9, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of September 9, 2009. 

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: 

Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6450; 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 2005–20–03, amendment 

39–14296 (70 FR 56361, September 27, 

2005). The existing AD applies to 

certain Boeing Model 737–100, –200, 

–200C, –300, –400, and –500 series 

airplanes. That NPRM was published in 

the Federal Register on November 17, 

2008 (73 FR 67815). That NPRM 

proposed to continue to require 

repetitive inspections of the intercostal 

webs, attachment clips, and stringer 

splice channels for cracks, at repetitive 

inspection intervals reduced from 

25,000 flight cycles to 6,000 flight 

cycles; and corrective action if 

necessary. That NPRM also proposed to 

expand the inspection area for Model 

737–200C series airplanes to include the 

area aft of the forward entry door. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been received on the NPRM. 

Request to Increase Grace Period 

US Airways requests that we increase 

the threshold grace period from 3,000 

flight cycles after the effective date of 

this AD to 4,500 flight cycles. US 

Airways states that the new grace period 

it requests would allow operators to 

schedule more airplanes into 

appropriate maintenance tasks. US 

Airways explains that the inspection 

would affect its operation by requiring 

additional maintenance that is not 

presently scheduled. 

We do not agree with the commenter’s 

request. In developing an appropriate 

compliance time for this AD, we 

considered not only the safety 

implications, but the manufacturer’s 

recommendations, and the practical 

aspect of accomplishing the 

modification within an interval of time 

that corresponds to typical scheduled 

maintenance for affected operators. 

However, under the provisions of 

paragraph (m) of this AD, we may 

consider requests for adjustments to the 

compliance time if data are submitted to 

substantiate that such an adjustment 

would provide an acceptable level of 

safety. We have not changed this AD in 

this regard. 

Explanation of Additional Changes to 

the AD 

We have clarified paragraphs (h), (i), 

and (l) of this AD to include the full 

citation for the service information 

referenced in those paragraphs. We 

made this change to ensure that it is 

clear which service information 

operators must use for a specific action. 

We have changed paragraph (j) of this 

AD to remove the reference to ‘‘Part 4 

of the Work Instructions of Boeing 


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38902 Federal Register / Vol. 74, No. 149 / Wednesday, August 5, 2009 / Rules and Regulations 

Special Attention Service Bulletin 737– 

53–1204, dated June 19, 2003,’’ because 

that service bulletin does not contain a 

Part 4. Boeing Alert Service Bulletin 

737–53A1204, Revision 1, dated March 

26, 2007, does include Part 4 to provide 

procedures related to inspections and 

corrective actions for the intercostal 

webs and attachment clips located aft of 

the forward entry door. Boeing Special 

Attention Service Bulletin 737–53– 

1204, dated June 19, 2003, does not 

include any actions for this area of the 

airplane. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We also determined that these changes 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Costs of Compliance 

There are about 3,132 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 of areas forward of 

the aft entry door (required by 

AD 2005-20-03).

2 $80 $160 per inspection 

cycle.

876 $140,160 per inspection cycle. 

Inspection of areas aft of the 

forward entry door for Model 

737-200C series airplanes 

(new action).

1 80 80 per inspection 

cycle.

19 1,520 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 39–14296 (70 

FR 56361, September 27, 2005) and by 

adding the following new airworthiness 

directive (AD): 

2009–16–14 Boeing: Amendment 39–15987. 

Docket No. FAA–2008–1213; Directorate 

Identifier 2007–NM–092–AD. 

Effective Date 

(a) This AD becomes effective September 9, 

2009. 

Affected ADs 

(b) This AD supersedes AD 2005–20–03. 

Applicability 

(c) This AD applies to Model 737–100, 

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

airplanes, certificated in any category; as 

identified in Boeing Alert Service Bulletin 

737–53A1204, Revision 1, dated March 26, 

2007. 

Unsafe Condition 

(d) This AD results from reports of fatigue 

cracks. We are issuing this AD to detect and 

correct fatigue cracking of the intercostals on 

the forward and aft sides of the forward entry 

door, which could result in loss of the 

forward entry door and rapid decompression 

of the airplane. 

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. 

Initial Compliance Time 

(f) For all Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes: Before 

the accumulation of 15,000 total flight cycles, 

or within 4,500 flight cycles after November 

1, 2005 (the effective date of AD 2005–20– 

03), whichever occurs later: Do the 

inspections required by paragraphs (h) and (i) 

of this AD. 

(g) For all Model 737–200C series 

airplanes: Before the accumulation of 15,000 

total flight cycles, or within 4,500 flight 

cycles after the effective date of this AD, 

whichever occurs later: Do the inspection 

required by paragraph (j) of this AD. 

Initial Inspection for Passenger 

Configuration Airplanes 

(h) For Group 1 passenger airplanes 

identified in Boeing Alert Service Bulletin 

737–53A1204, Revision 1, dated March 26, 

2007: Perform a detailed inspection for 


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Federal Register / Vol. 74, No. 149 / Wednesday, August 5, 2009 / Rules and Regulations 38903 

cracking of the intercostal web, attachment 

clips, and stringer splice channels; and a 

high frequency eddy current inspection for 

cracking of the stringer splice channels 

located forward and aft of the forward entry 

door; and do all applicable corrective actions 

before further flight; in accordance with Parts 

1 and 2 of the Work Instructions of Boeing 

Special Attention Service Bulletin 737–53– 

1204, dated June 19, 2003; or Boeing Alert 

Service Bulletin 737–53A1204, Revision 1, 

dated March 26, 2007. After the effective date 

of this AD, only Boeing Alert Service Bulletin 

737–53A1204, Revision 1, dated March 26, 

2007, may be used. 

Initial Inspection for Cargo Configuration 

Airplanes (Forward of the Forward Entry 

Door) 

(i) For Group 2 cargo airplanes identified 

in Boeing Alert Service Bulletin 737– 

53A1204, Revision 1, dated March 26, 2007: 

Perform a detailed inspection for cracking of 

the intercostal webs and attachment clips 

located forward of the forward entry door, 

and do all applicable corrective actions 

before further flight, in accordance with Part 

3 of the Work Instructions of Boeing Special 

Attention Service Bulletin 737–53–1204, 

dated June 19, 2003; or Boeing Alert Service 

Bulletin 737–53A1204, Revision 1, dated 

March 26, 2007. After the effective date of 

this AD, only Boeing Alert Service Bulletin 

737–53A1204, Revision 1, dated March 26, 

2007, may be used. 

Initial Inspection for Cargo Configuration 

Airplanes (Aft of the Forward Entry Door) 

(j) For Group 2 cargo airplanes identified 

in Boeing Alert Service Bulletin 737– 

53A1204, Revision 1, dated March 26, 2007: 

Perform a detailed inspection for cracking of 

the intercostal webs and attachment clips 

located aft of the forward entry door, and do 

all applicable corrective actions before 

further flight, in accordance with Part 4 of 

the Work Instructions of Boeing Alert Service 

Bulletin 737–53A1204, Revision 1, dated 

March 26, 2007. 

Repeat Inspections 

(k) Repeat the inspections required by 

paragraphs (h), (i), and (j) of this AD 

thereafter at intervals not to exceed 6,000 

flight cycles after the previous inspection, or 

within 3,000 flight cycles after the effective 

date of this AD, whichever occurs later. 

Exceptions 

(l) Do the actions required by this AD by 

accomplishing all the applicable actions 

specified in the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–53–1204, dated June 19, 

2003; or Boeing Alert Service Bulletin 737– 

53A1204, Revision 1, dated March 26, 2007; 

except as provided by paragraphs (l)(1) and 

(l)(2) of this AD. After the effective date of 

this AD, only Boeing Alert Service Bulletin 

737–53A1204, Revision 1, dated March 26, 

2007, may be used. 

(1) Where Boeing Special Attention Service 

Bulletin 737–53–1204, dated June 19, 2003; 

or Boeing Alert Service Bulletin 737– 

53A1204, Revision 1, dated March 26, 2007; 

specifies to contact Boeing for repair 

instructions: Before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (m) of 

this AD. 

(2) Where Boeing Special Attention Service 

Bulletin 737–53–1204, dated June 19, 2003; 

or Boeing Alert Service Bulletin 737– 

53A1204, Revision 1, dated March 26, 2007; 

specifies a compliance time relative to the 

date of a service bulletin, this AD requires 

compliance relative to the effective date of 

this AD. Where Boeing Special Attention 

Service Bulletin 737–53–1204, dated June 19, 

2003; or Boeing Alert Service Bulletin 737– 

53A1204, Revision 1, dated March 26, 2007; 

specifies a compliance time relative to the 

date of the initial release of the service 

bulletin, this AD requires compliance relative 

to the effective date of AD 2005–20–03 

(November 1, 2005). 

Alternative Methods of Compliance 

(AMOCs) 

(m)(1) The Manager, Seattle 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: Alan Pohl, 

Aerospace Engineer, Airframe Branch, ANM– 

120S, FAA, Seattle ACO, 1601 Lind Avenue, 

SW., Renton, Washington 98057–3356; 

telephone (425) 917–6450; fax (425) 917– 

6590. 

(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, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved previously in 

accordance with AD 2005–20–03 are 

approved as AMOCs for the corresponding 

provisions of this AD, provided the repetitive 

inspection intervals (if any) do not exceed 

6,000 flight cycles. 

(5) AMOCs approved previously in 

accordance with AD 2005–20–03 are not 

approved as AMOCs for the provisions of 

paragraph (j) or (k) of this AD. 

Material Incorporated by Reference 

(n) You must use Boeing Alert Service 

Bulletin 737–53A1204, Revision 1, dated 

March 26, 2007; 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 Alert Service Bulletin 737–53A1204, 

Revision 1, dated March 26, 2007, 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, 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. 

(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 July 23, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–18419 Filed 8–4–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26234; Directorate 

Identifier 2006–CE–064–AD; Amendment 

39–15983; AD 2007–03–17 R1 

RIN 2120–AA64 

Airworthiness Directives; SOCATA 

Model TBM 700 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are revising an existing 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued 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: 

This Airworthiness Directive (AD) was 

prompted by reports of loose rivets on frames 

C18 BIS and C19, which could result in a 

reduced structural integrity of the tail area. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

September 9, 2009. 

On September 9, 2009, the Director of 

the Federal Register approved the 


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