7576 Federal Register / Vol. 72, No. 32 / Friday, February 16, 2007 / Rules and Regulations 

Bulletin 767–28A0081, dated March 6, 2003; 

are considered acceptable for compliance 

with the corresponding action specified in 

paragraphs (f) and (g) of this AD. 

Parts Installation 

(k) As of the effective date of this AD, only 

main tank fuel boost pumps identified in 

paragraphs (k)(1) and (k)(2) of this AD may 

be installed on any airplane. 

(1) Any main tank fuel boost pump that has 

been inspected, and on which all applicable 

corrective actions have been performed, in 

accordance with paragraph (f) or (g) of this 

AD. 

(2) Any main tank fuel boost pump having 

P/N 5006003D. 

Alternative Methods of Compliance 

(AMOCs) 

(l)(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) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Material Incorporated by Reference 

(m) You must use the applicable service 

bulletin specified in Table 1 of this AD to 

perform the actions that are required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference of these 

documents in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207, for a copy 

of this service information. You may review 

copies at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, S.W., 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/ 

cfr/ibr-locations.html. 

TABLE 1.—MATERIAL INCORPORATED BY REFERENCE

Boeing alert service bulletin Revision level Date 

767–28A0077 ................................................................................................................................................ 1 ................... July 8, 2004. 

767–28A0081 ................................................................................................................................................ 1 ................... July 8, 2004. 

767–28A0088 ................................................................................................................................................ Original ......... February 24, 2005. 

767–28A0089 ................................................................................................................................................ Original ......... February 24, 2005. 

Issued in Renton, Washington, on February 

5, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–2644 Filed 2–15–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26235; Directorate 

Identifier 2006–CE–65–AD; Amendment 39–

14945; AD 2007–04–13] 

RIN 2120–AA64 

Airworthiness Directives; EADS 

SOCATA Model TBM 700 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) 

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 cracks found on several 

main landing gear cylinders. We are 

issuing this AD to require actions to 

correct the unsafe condition on these 

products. 

DATES: This AD becomes effective 

March 23, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 23, 2007. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Albert J. Mercado, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329–

4119; fax: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD 

The FAA is implementing a new 

process for streamlining the issuance of 

ADs related to MCAI. The streamlined 

process will allow us to adopt MCAI 

safety requirements in a more efficient 

manner and will reduce safety risks to 

the public. This process continues to 

follow all FAA AD issuance processes to 

meet legal, economic, Administrative 

Procedure Act, and Federal Register 

requirements. We also continue to meet 

our technical decision-making 

responsibilities to identify and correct 

unsafe conditions on U.S.-certificated 

products. 

This AD references the MCAI and 

related service information that we 

considered in forming the engineering 

basis to correct the unsafe condition. 

The AD contains text copied from the 

MCAI and for this reason might not 

follow our plain language principles. 

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 December 22, 2006 (71 FR 

76950). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states reports of 

cracks found on several main landing 

gear (MLG) cylinders. If not detected 

and corrected, fatigue cracks in the 

shock strut cylinder of the MLG could 

result in a collapsed MLG during takeoff 

or landing, and possible reduced 

structural integrity of the airplane. The 

MCAI requires inspecting the MLG 

forging body for cracks and repairing 

any cracks found. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Comment Issue No. 1: Change the 

Required Parts Cost in the Compliance 

Section 

EADS SOCATA comments the cost for 

the parts required to do the actions in 

the proposed AD are totally out of 

proportion. EADS SOCATA states the 

application of SB 70–130, ATA No. 32, 

dated January 2006, requires only two 

cotter pins and this cost is negligible. 

The proposed AD states it will take 

approximately $125,600 to comply with 

the AD. 


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In our cost estimate, we grouped all 

actions required to comply with the AD, 

including replacement of any MLG 

found cracked. We have since learned 

from EADS SOCATA that labor and 

parts costs for any cracked MLG will be 

provided under warranty. We will 

modify the Costs of Compliance section 

to reflect the 3 work-hours to do the 

inspection and the warranty coverage 

for the replacement MLG. 

Comment Issue No. 2: Change the 

Number of Work-Hours in the 

Compliance Section 

EADS SOCATA comments they have 

established, by applying the service 

bulletin, it takes 2 work-hours per 

product to perform an eddy current 

inspection, and it takes 3 work-hours 

per product to perform a dye penetrant 

or fluorescent penetrant inspection. 

The proposed AD states it will take 

approximately 18 work-hours to comply 

with the AD. 

In our cost estimate, we grouped all 

actions required to comply with the AD, 

including replacement of any MLG 

found cracked. We have since learned 

from EADS SOCATA that labor and 

parts costs for any cracked MLG will be 

provided under warranty. We will 

modify the Costs of Compliance section 

to reflect the 3 work-hours to do the 

inspection and the warranty coverage 

for the replacement MLG. 

Comment Issue No. 3: Change the 

Compliance Time 

EADS SOCATA comments that SB 

70–130, ATA No. 32, dated January 

2006, specifies for MLG with forging 

body totaling more than 3,500 landings 

to inspect the forging body within 25 

landings after issuance of the service 

bulletin. However, the proposed AD 

lowers the limit to 3,475 landings. 

EADS SOCATA states the limit of 3,500 

landings was established by analysis 

considering all necessary margins. 

EADS SOCATA requests the FAA 

change paragraph (e)(2) to read, ‘‘For 

MLG with forging body totaling more 

than 3,500 landings:’’ or explain the 

reason for the difference in the FAA AD 

Differences section. 

After evaluating the service bulletin 

further, we agree with the language 

presented by the commenter. We will 

change the final rule AD action based on 

this comment. 

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 a U.S. 

court of law. 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 described in a 

separate paragraph of the AD. These 

requirements, if any, take precedence 

over the actions copied from the MCAI. 

Costs of Compliance 

We estimate that this AD will affect 

272 products of U.S. registry. We also 

estimate that it will take about 3 workhours per product to comply with the 

basic requirements (inspection) of this 

AD. The average labor rate is $80 per 

work-hour. Based on these figures, we 

estimate the cost of the basic 

requirements of this AD to the U.S. 

operators to be $65,280, or $240 per 

product. 

In addition, follow-on actions 

(possible MLG replacement) would be 

covered by EADS SOCATA under 

warranty (both parts and labor). We 

have no way of determining the number 

of airplanes that would need this action. 

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://dms.dot.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–

5227) 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: 

2007–04–13 EADS SOCATA: Amendment 

39–14945; Docket No. FAA–2006–26235; 

Directorate Identifier 2006–CE–65–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective March 23, 2007. 


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Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model TBM 700 

airplanes, serial numbers 1 through 9999, 

certificated in any category. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) states 

reports of cracks found on several main 

landing gear (MLG) cylinders. If not detected 

and corrected, fatigue cracks in the shock 

strut cylinder of the MLG could result in a 

collapsed MLG during takeoff or landing, and 

possible reduced structural integrity of the 

airplane. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) As of March 23, 2007 (the effective date 

of this AD), for MLG with forging body 

totaling more than 1,750 landings but less 

than 3,501 landings since new: 

(i) Inspect the forging body for cracks 

within 100 landings after March 23, 2007 (the 

effective date of this AD) in accordance with 

the accomplishment instructions of EADS 

SOCATA TBM Aircraft Mandatory Service 

Bulletin SB 70–130, ATA No. 32, dated 

January 2006. 

(ii) If no cracks are detected, repetitively 

inspect thereafter every 175 landings. 

(2) As of March 23, 2007 (the effective date 

of this AD), for MLG with forging body 

totaling more than 3,500 landings since new: 

(i) Inspect the forging body for cracks 

within 25 landings after March 23, 2007 (the 

effective date of this AD) in accordance with 

the accomplishment instructions of EADS 

SOCATA TBM Aircraft Mandatory Service 

Bulletin SB 70–130, ATA No. 32, dated 

January 2006. 

(ii) If no cracks are detected, repetitively 

inspect thereafter every 175 landings. 

(3) If any cracks are detected during any 

inspection required in paragraph (e) of this 

AD: 

(i) Before further flight, remove the affected 

landing gear leg and confirm the presence of 

the crack with dye penetrant inspection or 

fluorescent penetrant inspection. 

(ii) If the crack is confirmed, before further 

flight, contact EADS SOCATA to coordinate 

the landing gear repair/replacement and then 

conform to any instruction stated by EADS 

SOCATA. 

(4) If you do not know the number of 

landings, follow the instructions in the 

Compliance section of EADS SOCATA TBM 

Aircraft Mandatory Service Bulletin SB 70–

130, ATA No. 32, dated January 2006. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(f) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Staff, 

FAA, Small Airplane Directorate, ATTN: 

Albert J. Mercado, Aerospace Engineer, 901 

Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4119; fax: (816) 

329–4090, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

(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 

(g) Refer to MCAI European Aviation 

Safety Agency (EASA) AD No. 2006–0085, 

dated April 12, 2006, for related information. 

Material Incorporated by Reference 

(h) You must use EADS SOCATA TBM 

Aircraft Mandatory Service Bulletin SB 70–

130, ATA No. 32, dated January 2006, 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 EADS SOCATA, Direction 

des Services, 65921 Tarbes Cedex 9, France; 

telephone: 33 (0)5 62.41.73.00; fax: 33 (0)5 

62.41.76.54. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Room 506, 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/ 

cfr/ibr-locations.html. 

Issued in Kansas City, Missouri, on 

February 8, 2007. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 07–670 Filed 2–15–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Document No. FAA–2007–27174; 

Directorate Identifier 2007–CE–006–AD; 

Amendment 39–14944; AD 2007–04–12] 

RIN 2120–AA64 

Airworthiness Directives; Gippsland 

Aeronautics Pty. Ltd. Model GA8 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by the aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Inspection of a high time aircraft has 

revealed cracks in the Horizontal Stabiliser 

rear spar splice plate and inboard main ribs 

around the area of the Horizontal Stabiliser 

rear pivot attachment. Additionally, failure of 

some attach bolts in service may be due to 

improper assembly. 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective 

March 8, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 8, 2007. 

We must receive comments on this 

AD by March 19, 2007. 

ADDRESSES: You may send comments by 

any of the following methods: 

• DOT Docket Web Site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Fax: (202) 493–2251. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 


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