59240 Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations 

Actions Compliance Procedures 

(1) Inspect the avionics bus circuit breaker 

switch to determine the part number (P/N) 

and date code. (i) If the P/N is CM3589–50, 

593–250–101, 593–250–102, W31–X2M5A–

50, or W31–X1000–50; and (ii) The date 

code is 0434 or later; then (iii) No further action is required.

Within the next 200 hours time-in-service 

(TIS), the next 12 months, or at the next 

scheduled inspection, after November 9, 

2005 (the effective date of this AD), whichever occurs first.

For Models 425 and 441 airplanes, follow the 

procedures in Cessna Conquest Service 

Bulletin CQB05–2, dated February 21, 

2005, and the applicable maintenance manual. For all other affected airplane models, 

follow the procedures in Cessna Multi-engine Service Bulletin MEB05–1 dated February 21, 2005, and the applicable maintenance manual. 

(2) If the P/N is CM3589–50, 593–250–101, 

593–250–102, W31–X2M5A–50, or W31–

X1000–50 and there is no date code, replace 

the avionics bus circuit breaker switch with a 

P/N CM3589–50 that has a date code of 

0434 or later.

Before further flight after the inspection required in paragraph (e)(1) of this AD.For Models 425 and 441 airplanes, follow the 

procedures in Cessna Conquest Service 

Bulletin CQB05–2, dated February 21, 

2005, and the applicable maintenance manual. For all other affected airplane models, 

follow the procedures in Cessna Multi-engine Service Bulletin MEB05–1, dated February 21, 2005, and the applicable maintenance manual. 

(3) If the P/N is CM3589–50, 593–250–101, 

593–250–102, W31–X2M5A–50, or W31–

X1000–50, or W31–X1000–50 and the date 

code is earlier than 0434, the part has a safe 

life limit of 1,000 hours TIS and must be replaced within the 1,000-hour time limit with a 

P/N CM3589–50 that has a date code of 

0434 or later.

Within the 1,000-hour TIS safe life limit .......... For Models 425 and 441 airplanes, follow the 

procedures in Cessna Conquest Service 

Bulletin CQB05–2, dated February 21, 

2005, and the applicable maintenance manual. For all other affected airplane models, 

follow the procedures in Cessna Multi-engine Service Bulletin MEB05–1, dated February 21, 2005, and the applicable maintenance manual. 

(4) Do not install a P/N CM3589–50, 593–250–

101, 593–250–102, W31–X2M5A–50, or 

W31–X1000–50 that does not have a date 

code or has a date code earlier than 0434.

As of November 9, 2005 (the effective date of 

this AD).

Not applicable. 

May I Request an Alternative Method of 

Compliance? 

(f) You may request a different method of 

compliance or a different compliance time 

for this AD by following the procedures in 14 

CFR 39.19. Unless FAA authorizes otherwise, 

send your request to your principal 

inspector. The principal inspector may add 

comments and will send your request to the 

Manager, Wichita Aircraft Certification Office 

(ACO), FAA. For information on any already 

approved alternative methods of compliance, 

contact Gerald Pilj, Aerospace Engineer, FAA 

Wichita ACO, 1801 Airport Road, MidContinent Airport, Wichita, Kansas 67209; 

telephone: (316) 946–4151; facsimile: (316) 

946–4107. 

Does This AD Incorporate Any Material by 

Reference? 

(g) You must do the actions required by 

this AD following the instructions in Cessna 

Conquest Service Bulletin CQB05–2, dated 

February 21, 2005, and Cessna Multi-engine 

Service Bulletin MEB05–1, dated February 

21, 2005. The Director of the Federal Register 

approved the incorporation by reference of 

this service bulletin in accordance with 5 

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

copy of this service information, contact The 

Cessna Aircraft Company, Citation Marketing 

Division, Product Support P.O. Box 7706, 

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

5800; facsimile: (316) 942–9006. To review 

copies of this service information, go to the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html or call (202) 741–6030. To 

view the AD docket, go to the Docket 

Management Facility; U.S. Department of 

Transportation, 400 Seventh Street, SW., 

Nassif Building, Room PL–401, Washington, 

DC 20590–001 or on the Internet at http:// 

dms.dot.gov. The docket number is FAA–

2005–21173; Directorate Identifier 2005–CE–

22–AD. 

Issued in Kansas City, Missouri, on 

September 28, 2005. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19928 Filed 10–11–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21464; Directorate 

Identifier 2005–CE–32–AD; Amendment 39–

14320; AD 2005–20–24] 

RIN 2120–AA64 

Airworthiness Directives; SOCATA—

Groupe AEROSPATIALE Model TBM 

700 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for certain 

SOCATA—Groupe AEROSPATIALE 

(SOCATA) Model TBM 700 airplanes. 

This AD requires you to inspect the 

fuselage skin in the VHF1 antenna 

mounting area for cracks and loose 

rivets. This AD also requires you to 

modify the area if you find cracks or 

loose rivets. This AD results from 

mandatory continuing airworthiness 

information (MCAI) issued by the 

airworthiness authority for France. We 

are issuing this AD to detect and correct 

cracks in the fuselage skin, which could 

result in loss of aircraft pressurization. 

Loss of aircraft pressurization could 

lead to flight crew incapacitation. 

DATES: This AD becomes effective on 

November 9, 2005. 

As of November 9, 2005, the Director 

of the Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulation. 

ADDRESSES: To get the service 

information identified in this AD, 

contact EADS SOCATA Tarbes, 

Direction des Services, 65921 Tarbes 

Cedex 9, France; telephone: 33 (0)5 

62.41.73.00; facsimile: 33 (0)5 

62.41.76.54; or SOCATA AIRCRAFT, 

North Perry Airport, 7501 Pembroke 

Road, Pembroke Pines, Florida 33023. 

To view the AD docket, go to the 

Docket Management Facility; U.S. 

Department of Transportation, 400 

Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations 59241 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

001 or on the Internet at http:// 

dms.dot.gov. The docket number is 

FAA–2005–21464; Directorate Identifier 

2005–CE–32–AD. 

FOR FURTHER INFORMATION CONTACT: 

Peter L. Rouse, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329–

4135; facsimile: (816) 329–4090. 

SUPPLEMENTARY INFORMATION:

Discussion 

What events have caused this AD? 

The Direction Ge ́ne ́rale de L’Aviation 

Civile (DGAC), which is the 

airworthiness authority for France, 

notified FAA that an unsafe condition 

may exist on certain SOCATA Model 

TBM 700 airplanes. The DGAC reports 

cracks in the fuselage skin by the 

passenger door on the affected 

airplanes. These airplanes have a VHF1 

antenna mounted under the fuselage 

between frame C12 and C13 or C13 and 

C13bis. 

Investigations reveal that antenna 

vibrations are causing the cracks. 

What is the potential impact if FAA 

took no action? If not detected and 

corrected, cracks in the fuselage skin 

could cause loss of aircraft 

pressurization. Loss of pressurization 

could lead to flight crew incapacitation. 

Has FAA taken any action to this 

point? We issued a proposal to amend 

part 39 of the Federal Aviation 

Regulations (14 CFR part 39) to include 

an AD that would apply to certain 

SOCATA Model TBM 700 airplanes. 

This proposal was published in the 

Federal Register as a notice of proposed 

rulemaking (NPRM) on July 7, 2005 (70 

FR 39204). The NPRM proposed to 

require you to inspect the fuselage skin 

where the VHF1 antenna mounts under 

the fuselage between frame C12 and C13 

or C13 and C13bis for cracks and loose 

rivets. The NPRM also proposes to 

require you to modify the VHF1 antenna 

bracket and the antenna/fuselage 

interface. 

Comments 

Was the public invited to comment? 

We provided the public the opportunity 

to participate in developing this AD. We 

received no comments on the proposal 

or on the determination of the cost to 

the public. 

Conclusion 

What is FAA’s final determination on 

this issue? We have carefully reviewed 

the available data and determined that 

air safety and the public interest require 

adopting the AD as proposed except for 

minor editorial corrections. We have 

determined that these minor 

corrections: 

—Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

—Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Changes to 14 CFR Part 39—Effect on 

the AD 

How does the revision to 14 CFR part 

39 affect this AD? On July 10, 2002, the 

FAA published a new version of 14 CFR 

part 39 (67 FR 47997, July 22, 2002), 

which governs the FAA’s AD system. 

This regulation now includes material 

that relates to altered products, special 

flight permits, and alternative methods 

of compliance. This material previously 

was included in each individual AD. 

Since this material is included in 14 

CFR part 39, we will not include it in 

future AD actions. 

Costs of Compliance 

How many airplanes does this AD 

impact? We estimate that this AD affects 

185 airplanes in the U.S. registry. 

What is the cost impact of this AD on 

owners/operators of the affected 

airplanes? We estimate the following 

costs to do the inspection: 

Labor cost Parts cost Total cost per 

airplane Total cost on U.S. operators 

1 work hour × $65 per hour = $65 ............................................................. Not applicable ......... $65 $65 × $185 = $12,025 

We estimate the following costs to do 

the modification. 

Labor cost Parts cost Total cost per 

airplane 

4 work hours × $65 per hour = $260 .......................................................................................................................... $181 $441 

Authority for This Rulemaking 

What authority does FAA have for 

issuing this rulemaking action? 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 AD. 

Regulatory Findings 

Will this AD impact various entities? 

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. 

Will this AD involve a significant rule 

or regulatory action? 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 the 

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 summary of the costs 

to comply with this AD (and other 

information as included in the 

Regulatory Evaluation) and placed it in 

the AD Docket. You may get a copy of 

59242 Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations 

this summary by sending a request to us 

at the address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2005–21464; 

Directorate Identifier 2005–CE–32–AD’’

in your request. 

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 Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. FAA amends § 39.13 by adding a 

new AD to read as follows: 

2005–20–24 Socata—Groupe Aerospatiale: 

Amendment 39–14320; Docket No. 

FAA–2005–21464; Directorate Identifier 

2005–CE–32–AD. 

When Does This AD Become Effective? 

(a) This AD becomes effective on 

November 9, 2005. 

What Other ADs Are Affected by This 

Action? 

(b) None. 

What Airplanes Are Affected by This AD? 

(c) This AD affects the following Model 

TBM 700 airplanes, serial numbers 1 through 

255; 257 through 267; and 270, that are: 

(1) equipped with a VHF1 antenna 

mounted under the fuselage between frame 

C12 and C13 or C13 and C13bis; and 

(2) certificated in any category. 

What Is the Unsafe Condition Presented in 

This AD? 

(d) This AD is the result of mandatory 

continuing airworthiness information (MCAI) 

issued by the airworthiness authority for 

France. The actions specified in this AD are 

intended to detect and correct cracks in the 

fuselage skin, which could result in loss of 

aircraft pressurization. Loss of aircraft 

pressurization could lead to flight crew 

incapacitation. 

What Must I Do To Address This Problem? 

(e) To address this problem, you must do 

the following: 

Note: The EADS SOCATA Mandatory 

Service Bulletin TBM Aircraft, SB 70–103, 

Amendment 1, ATA No. 53, dated September 

2003, allows the pilot to perform the visual 

inspection of the fuselage skin in the VHF1 

antenna mount area for cracks and loose 

rivets. The Federal Aviation Regulations (14 

CFR 43.3) only allow the pilot to perform 

preventive maintenance as described in 14 

CFR part 43, App. A, paragraph (c). These 

visual inspections are not considered 

preventive maintenance under 14 CFR part 

43, App. A, paragraph (c). Therefore, an 

appropriately-rated mechanic must perform 

all actions of this AD. 

Actions Compliance Procedures 

(1) Inspect the fuselage skin in the VHF1 antenna mount area between frame C12 and 

C13 or C13 and C13bis for cracks and 

loose rivets.

Within the next 50 hours time-in-service (TIS) after 

November 9, 2005, (the effective date of this 

AD). Repetitively inspect thereafter at intervals 

not to exceed 50 hours TIS until the modification in paragraph (e)(2) of this AD is done. 

Modifying the VHF1 antenna bracket and interface area terminates the repetitive inspection requirement of this AD.

Follow EADS SOCATA Mandatory Service 

Bulletin TBM Aircraft, SB 70–103, 

Amendment 1, ATA No. 53, dated September 2003. 

(2) Modify the VHF1 antenna bracket and the 

antenna/fuselage interface.

At whichever of the following that occurs first: 

(i) Before further flight anytime a crack or loose 

rivet is found during any inspection required in 

paragraph (e)(1) of this AD.

(ii) Within 100 hours TIS or 12 months after November 9, 2005 (the effective date of this AD), 

whichever occurs later.

Follow EADS SOCATA Recommended 

Service Bulletin TBM Aircraft, SB 70–111, 

ATA No. 53, dated October 2003, and 

the applicable maintenance manual. 

May I Request an Alternative Method of 

Compliance? 

(f) You may request a different method of 

compliance or a different compliance time 

for this AD by following the procedures in 14 

CFR 39.19. Unless FAA authorizes otherwise, 

send your request to your principal 

inspector. The principal inspector may add 

comments and will send your request to the 

Manager, Standards Office, Small Airplane 

Directorate, FAA. For information on any 

already approved alternative methods of 

compliance, contact Peter L. Rouse, 

Aerospace Engineer, FAA, Small Airplane 

Directorate, 901 Locust, Room 301, Kansas 

City, Missouri 64106; telephone: (816) 329–

4135; facsimile: (816) 329–4090. 

Is There Other Information That Relates to 

This Subject? 

(g) French AD Number F–2003–367 R1, 

Distribution A, Issue date: February 4, 2004, 

also addresses the subject of this AD. 

Does This AD Incorporate Any Material by 

Reference? 

(h) You must do the actions required by 

this AD following the instructions in EADS 

SOCATA Mandatory Service Bulletin TBM 

Aircraft, SB 70–103, Amendment 1, ATA No. 

53, dated September 2003, and EADS 

SOCATA Recommended Service Bulletin 

TBM Aircraft, SB 70–111, ATA No. 53, dated 

October 2003. The Director of the Federal 

Register approved the incorporation by 

reference of this service bulletin in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. To get a copy of this service 

information, contact EADS SOCATA Tarbes, 

Direction des Services, 65921 Tarbes Cedex 

9, France; telephone: 33 (0)5 62.41.73.00; 

facsimile: 33 (0)5 62.41.76.54; or SOCATA 

AIRCRAFT, North Perry Airport, 7501 

Pembroke Road, Pembroke Pines, Florida 

33023. To review copies of this service 

information, go to the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, go to: http:// 

www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html or call (202) 741–6030. To 

view the AD docket, go to the Docket 

Management Facility; U.S. Department of 

Transportation, 400 Seventh Street, SW., 

Nassif Building, Room PL–401, Washington, 

DC 20590–001 or on the Internet at http:// 

dms.dot.gov. The docket number is FAA–

2005–21464; Directorate Identifier 2005–CE–

32–AD. 

Issued in Kansas City, Missouri, on 

September 28, 2005. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19930 Filed 10–11–05; 8:45 am] 

BILLING CODE 4910–13–P