Airworthiness Directives; SOCATA-Groupe AEROSPATIALE Model TBM 700 Airplanes, 59240-59242 [05-19930]

Download as PDF 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. (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. (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 .......... (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). 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. 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. 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. 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/ VerDate Aug<31>2005 16:47 Oct 11, 2005 Jkt 208001 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 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: PO 00000 Frm 00032 Fmt 4700 Sfmt 4700 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 E:\FR\FM\12OCR1.SGM 12OCR1 59241 Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations 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 Generale 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 1 work hour × $65 per hour = $65 ............................................................. Not applicable ......... $65 Total cost on U.S. operators $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 VerDate Aug<31>2005 16:47 Oct 11, 2005 Jkt 208001 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. PO 00000 Frm 00033 Fmt 4700 Sfmt 4700 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 E:\FR\FM\12OCR1.SGM 12OCR1 59242 Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations 2005–20–24 Socata—Groupe Aerospatiale: Amendment 39–14320; Docket No. FAA–2005–21464; Directorate Identifier 2005–CE–32–AD. 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. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. When Does This AD Become Effective? What Must I Do To Address This Problem? (a) This AD becomes effective on November 9, 2005. (e) To address this problem, you must do the following: Adoption of the Amendment What Other ADs Are Affected by This Action? 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. 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 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: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I § 39.13 [Amended] 2. FAA amends § 39.13 by adding a new AD to read as follows: I (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? Authority: 49 U.S.C. 106(g), 40113, 44701. (d) This AD is the result of mandatory continuing airworthiness information (MCAI) 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. 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 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. May I Request an Alternative Method of Compliance? Does This AD Incorporate Any Material by Reference? (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. (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 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. VerDate Aug<31>2005 18:10 Oct 11, 2005 Jkt 208001 PO 00000 Frm 00034 Fmt 4700 Sfmt 4700 Follow EADS SOCATA Recommended Service Bulletin TBM Aircraft, SB 70–111, ATA No. 53, dated October 2003, and the applicable maintenance manual. 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 E:\FR\FM\12OCR1.SGM 12OCR1

Agencies

[Federal Register Volume 70, Number 196 (Wednesday, October 12, 2005)]
[Rules and Regulations]
[Pages 59240-59242]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-19930]


-----------------------------------------------------------------------

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

[[Page 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 
G[eacute]n[eacute]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:

----------------------------------------------------------------------------------------------------------------
                                                           Total cost per
          Labor cost                   Parts cost             airplane          Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
1 work hour x $65 per hour =   Not applicable............            $65   $65 x $185 = $12,025
 $65.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do the modification.

------------------------------------------------------------------------
                                                          Total cost per
                Labor cost                  Parts cost       airplane
------------------------------------------------------------------------
4 work hours x $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

[[Page 59242]]

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

0
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

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. FAA amends Sec.  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  Within the next 50 hours time-in-    Follow EADS SOCATA Mandatory
 antenna mount area between frame C12 and   service (TIS) after November 9,      Service Bulletin TBM Aircraft,
 C13 or C13 and C13bis for cracks and       2005, (the effective date of this    SB 70-103, Amendment 1, ATA No.
 loose rivets.                              AD). Repetitively inspect            53, dated September 2003.
                                            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.
(2) Modify the VHF1 antenna bracket and    At whichever of the following that   Follow EADS SOCATA Recommended
 the antenna/fuselage interface.            occurs first:                        Service Bulletin TBM Aircraft,
                                           (i) Before further flight anytime a   SB 70-111, ATA No. 53, dated
                                            crack or loose rivet is found        October 2003, and the
                                            during any inspection required in    applicable maintenance manual.
                                            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.
----------------------------------------------------------------------------------------------------------------

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