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 


srobinson on DSKHWCL6B1PROD with RULES
38904 Federal Register / Vol. 74, No. 149 / Wednesday, August 5, 2009 / Rules and Regulations 

incorporation by reference of SOCATA 

TBM Aircraft Mandatory Service 

Bulletin SB 70–129, AMENDMENT 1, 

dated February 2009, listed in this AD. 

As of March 15, 2007 (72 FR 5923, 

February 8, 2007), the Director of the 

Federal Register approved the 

incorporation by reference of SOCATA 

TBM Aircraft Mandatory Service 

Bulletin SB 70–129, dated June 2005, 

listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

Docket 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: 

Albert Mercado, Aerospace Engineer, 

901 Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4119; fax: (816) 329–4090. 

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 May 12, 2009 (74 FR 22125), 

and proposed to revise AD 2007–03–17, 

Amendment 39–14928 (72 FR 5923, 

February 8, 2007). 

Since we issued AD 2007–03–17, 

EADS SOCATA revised the service 

bulletin used in the AD to change the 

applicability. 

The NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states that: 

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. 

This MCAI requires you to inspect the 

rivets on frames C18 BIS and C19, and, 

if necessary, apply corrective actions. 

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 comment received. 

Comment Issue: Required Work-Hours 

and Labor Cost 

SOCATA comments that the initial 

inspection would take 0.5 work-hour. If 

necessary, rivets replacement would 

never take more than 5 work-hours. If 

parts are necessary, only rivets and 

shims are required, and their cost is 

negligible. 

We agree with SOCATA, and we will 

revise the basic requirement work-hours 

estimate from 3 work-hours to 1 workhour. We will also revise the follow-on 

work-hours from 15 hours to 5 hours 

and revise the follow-on parts cost from 

$2,000 to $5 per product per SOCATA’s 

comments. 

Conclusion 

We reviewed the available data, 

including the comment 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 FAA policies. 

Any such differences are highlighted in 

a note within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

272 products of U.S. registry. We also 

estimate that it will take about 1 workhour per product to comply with the 

basic requirements of this AD. The 

average labor rate is $80 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $21,760, or $80 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 5 work-hours and require parts 

costing $5 for a cost of $405 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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 

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. 

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 the NPRM, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket 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: 


srobinson on DSKHWCL6B1PROD with RULES
Federal Register / Vol. 74, No. 149 / Wednesday, August 5, 2009 / Rules and Regulations 38905 

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 

removing AD 2007–03–17, Amendment 

39–14928 (72 FR 5923, February 8, 

2007) and adding the following new AD: 

2007–03–17 R1 SOCATA: Amendment 39– 

15983; Docket No. FAA–2006–26234; 

Directorate Identifier 2006–CE–064–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective September 9, 2009. 

Affected ADs 

(b) This AD revises AD 2007–03–17, 

Amendment 39–14928 (72 FR 5923, February 

8, 2007). 

Applicability 

(c) This AD applies to TBM 700 airplanes, 

serial numbers 1 through 345, certificated in 

any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 53: Fuselage. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

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. 

This MCAI requires you to inspect the rivets 

on frames C18 BIS and C19, and, if necessary, 

apply corrective actions. You may obtain 

further information by examining the MCAI 

in the AD docket. 

Actions and Compliance 

(f) Unless already done, within the next 

100 hours time-in-service (TIS) after 

September 9, 2009 (the effective date of this 

AD) or within the next 12 months after 

September 9, 2009 (the effective date of this 

AD), whichever occurs later, and repetitively 

thereafter at intervals not to exceed every 100 

hours TIS, do a detailed inspection of the 

area and apply corrective actions, as 

necessary. Follow the accomplishment 

instructions of either SOCATA TBM Aircraft 

Mandatory Service Bulletin SB 70–129, dated 

June 2005 or SOCATA TBM Aircraft 

Mandatory Service Bulletin SB 70–129, 

AMENDMENT 1, dated February 2009. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: SOCATA 

revised the service bulletin used in AD 2007– 

03–17, Amendment 39–14928 (72 FR 5923, 

February 8, 2007). The revised service 

bulletin changes the applicability of the 

airplanes from what was in the original 

service bulletin. The MCAI has not been 

revised and allows the use of ‘‘Any 

subsequent approved revision of this 

document is acceptable’’ for service bulletin 

revisions. The FAA AD does not have a 

similar provision. This revised AD changes 

the Applicability section based on the 

revised service bulletin. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards 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: Albert Mercado, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4119; fax: (816) 329– 

4090. 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. 

(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. 

(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 Direction Ge ́ne ́rale de 

l’aviation Civile Airworthiness Directive No 

F–2005–132, dated August 3, 2005; SOCATA 

TBM Aircraft Mandatory Service Bulletin SB 

70–129, dated June 2005; and SOCATA TBM 

Aircraft Mandatory Service Bulletin SB 70– 

129, AMENDMENT 1, dated February 2009 

for related information. 

Material Incorporated by Reference 

(i) You must use SOCATA TBM Aircraft 

Mandatory Service Bulletin SB 70–129, dated 

June 2005, or SOCATA TBM Aircraft 

Mandatory Service Bulletin SB 70–129, 

AMENDMENT 1, dated February 2009, 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 

SOCATA TBM Aircraft Mandatory Service 

Bulletin SB 70–129, AMENDMENT 1, dated 

February 2009, under 5 U.S.C. 552(a) and 1 

CFR part 51. 

(2) On March 15, 2007 (72 FR 5923, 

February 8, 2007), the Director of the Federal 

Register previously approved the 

incorporation by reference of SOCATA TBM 

Aircraft Mandatory Service Bulletin SB 70– 

129, dated June 2005. 

(3) For service information identified in 

this AD, contact SOCATA, 65921 Tarbes 

Cedex 9, France; Telephone: +33 (0) 5 62 41 

73 00; Fax: +33 (0)5 62 41 73 05; Internet: 

http://www.socata.com. 

(4) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Central Region, Office of 

the Regional Counsel, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the Central 

Region, call (816) 329–3768. 

(5) You may also review copies of the 

service information incorporated by reference 

for this AD 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 July 16, 

2009. 

Wes Ryan, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–17897 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–2007–29173; Directorate 

Identifier 2006–NM–283–AD; Amendment 

39–15989; AD 2009–16–06] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 767 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Boeing Model 767 airplanes. This AD 

requires installing an automatic shutoff 

system for the auxiliary fuel tank 

override/jettison fuel pumps (also 

referred to as center tank fuel pumps in 

the airplane flight manual (AFM)), 

revising the AFM to advise the 

flightcrew of certain operating 

restrictions for airplanes equipped with 

an automatic auxiliary fuel tank pump 

shutoff control, and, for certain 

airplanes, installing a placard to alert 

the flightcrew of certain fuel usage 

restrictions. This AD provides optional 

terminating actions for certain 

requirements. This AD results from a 

design review of the fuel tank systems. 

We are issuing this AD to prevent an 

overheat condition outside the center 

tank fuel pump explosion-resistance 

area that is open to the pump inlet, 

which could cause an ignition source 

for the fuel vapors in the fuel tank and 

result in fuel tank explosions and 

consequent loss of the airplane. 


srobinson on DSKHWCL6B1PROD with RULES