Airworthiness Directives; The Cessna Aircraft Company Models 401, 401A, 401B, 402, 402A, 402B, 402C, 404, 411, 411A, 414, 414A, 421, 421A, 421B, 421C, 425, and 441 Airplanes, 59237-59240 [05-19928]

Download as PDF Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations actions will take about 2 work hours per airplane, at an average labor rate of $65 per work hour. Required parts will be obtained from operator stores. Based on these figures, the estimated cost of the AD for U.S. operators is $52,390, or $130 per airplane. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, I VerDate Aug<31>2005 18:10 Oct 11, 2005 Jkt 208001 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: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): I 2005–20–36 Airbus: Amendment 39–14333. Docket No. FAA–2005–21862; Directorate Identifier 2005–NM–091–AD. Effective Date (a) This AD becomes effective November 16, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A320– 111, –211, –212, –214, –231, –232, and –233 airplanes, and Model A321–111, –112, –131, –211, and –231 airplanes, certificated in any category; except those airplanes on which Airbus Modification 23645 has been incorporated in production. Unsafe Condition (d) This AD was prompted by the results of fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent an ignition source for fuel vapor in the wing, which could result in fire or explosion in the adjacent wing fuel tank. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Installation of Bonding Lead (f) Within 56 months after the effective date of this AD, install a bonding lead between the low pressure valve and the adjacent pipe assembly in each wing, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 28–1055, Revision 1, dated March 8, 1994. Actions Accomplished Using Original Issue of Service Bulletin (g) Actions accomplished prior to the effective date of this AD in accordance with Airbus Service Bulletin A320–28–1055, dated July 12, 1993, are considered acceptable for compliance with the corresponding actions required by paragraph (f) of this AD. Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 59237 (2) Before using any AMOC approved in accordance with 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (i) French airworthiness directive F–2005– 058, dated April 13, 2005, also addresses the subject of this AD. Material Incorporated by Reference (j) You must use Airbus Service Bulletin A320–28–1055, Revision 1, dated March 8, 1994, 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 this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the 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 September 28, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–20067 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–2005–21173; Directorate Identifier 2005–CE–22–AD; Amendment 39– 14321; AD 2005–20–25] RIN 2120–AA64 Airworthiness Directives; The Cessna Aircraft Company Models 401, 401A, 401B, 402, 402A, 402B, 402C, 404, 411, 411A, 414, 414A, 421, 421A, 421B, 421C, 425, and 441 Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain The Cessna Aircraft Company (Cessna) Models 401, 401A, 401B, 402, 402A, 402B, 402C, 404, 411, 411A, 414, 414A, 421, 421A, 421B, 421C, 425, and 441 airplanes equipped with certain avionics bus circuit breaker switches. E:\FR\FM\12OCR1.SGM 12OCR1 59238 Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations This AD requires you to inspect the avionics bus circuit breaker switch to determine the date code and replace any without a date code. This AD also imposes a 1,000-hour safe life limit on avionics bus circuit breaker switches with a date code earlier than 0434. This AD results from reports of smoke and a burning smell in the cockpit. We are issuing this AD to prevent failure of the avionics bus circuit breaker switch, which could result in smoke and a burning smell in the cockpit. This failure could lead to reduced ability to control the airplane. 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 The Cessna Aircraft Company, Product Support P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517–5800; facsimile: (316) 942–9006. 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. FOR FURTHER INFORMATION CONTACT: Gerald Pilj, Aerospace Engineer, FAA, Wichita ACO, 1801 Airport Road, MidContinent Airport, Wichita, Kansas 67209; telephone: (316) 946–4151; facsimile: (316) 946–4107. SUPPLEMENTARY INFORMATION: Discussion What events have caused this AD? We have received failure reports of certain Tyco Electronics circuit breaker switches installed on the master avionics bus of Cessna Models 401, 401A, 401B, 402, 402A, 402B, 402C, 404, 411, 411A, 414, 414A, 421, 421A, 421B, 421C, 425, and 441 airplanes. Failure of these circuit breaker switches causes smoke and a burning smell in the cockpit. Analysis of the circuit breaker switch revealed the copper braid inside the switch had frayed. Continued use causes an internal short. The internal short could result in the internal switch components or external wiring melting because it is no longer protected by the circuit breaker. The affected circuit breaker switches have a date code earlier than 0434 or do not have a date code on them. The date code consists of four digits. The first two represent the year and the last two represent the week of the year the part was made. What is the potential impact if FAA took no action? If not prevented, failure of the avionics bus circuit breaker switch could cause smoke and a burning smell in the cockpit. This failure could lead to reduced ability to control the airplane. 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 Cessna Models 401, 401A, 401B, 402, 402A, 402B, 402C, 404, 411, 411A, 414, 414A, 421, 421A, 421B, 421C, 425, and 441 airplanes equipped with certain avionics bus circuit breaker switches. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on June 9, 2005 (70 FR 33720). The NPRM proposed to require you to: linspect the avionics bus circuit breaker switch to determine the date code; lreplace all avionics bus circuit breaker switches without a date code; and limplement a 1,000-hour safe life limit for all avionics bus circuit breaker switches with a date code earlier than 0434. 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: lare consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and ldo 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 7,125 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 accomplish the inspection and replacement: For Models 401, 401A, 401B, 402, 402A, 402B, 402C, 404, 411, 411A, 414, 414A, 421, 421A, 421B, and 421C airplanes: Labor cost Parts cost Total cost per airplane 4 work hours × $65 an hour = $260. ......... $119 each. $498 (if 2 switches are required). ............. Labor cost Parts cost Total cost per airplane 8 work hours × $65 an hour = $520. ......... $119 each. $758 (if 2 switches are required). ............. Total cost on U.S. operators $498 × 6,527 = $3,250,446. For Models 425 and 441 airplanes: VerDate Aug<31>2005 16:47 Oct 11, 2005 Jkt 208001 PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 Total cost on U.S. operators $758 × 598 = $453,284. E:\FR\FM\12OCR1.SGM 12OCR1 Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations 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 this summary by sending a request to us at the address listed under ADDRESSES. Include ‘‘Docket No. FAA–2005–21173; Directorate Identifier 2005–CE–22–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, I 59239 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: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] I 2. FAA amends § 39.13 by adding a new AD to read as follows: 2005–20–25 The Cessna Aircraft Company: Amendment 39–14321; Docket No. FAA–2005–21173; Directorate Identifier 2005–CE–22–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 airplane models and serial numbers that are: (1) Equipped with an avionics bus circuit breaker switch, part number (P/N) CM3589– 50, 593–250–101, 593–250–102, W31– X2M5A–50, or W31–X1000–50; and (2) certificated in any category: Model Serial numbers 401 ... 401A 401B 402 ... 402A 402B 655 and 401–0001 through 401–0322. 655 and 401A0001 through 401A0132. 401B0001 through 401B0221. 402–0001 through 402–0322. 402A0001 through 402A0129. 402B0001 through 402B0122, 402B0201 through 402B0249, 402B0301 through 402B0455, 402B0501 through 402B0640, 402B0801 through 402B0935, 402B1001 through 402B1100, 402B1201 through 402B1250, and 402B1301 through 402B1384. 689, 402C0001 through 402C0125, 402C0201 through 402C0355, 402C0401 through 402C0528, 402C0601 through 402C0653, 402C0801 through 402C0807, and 402C0808 through 402C1020. 682, 404–0001 through 404–0136, 404–0201 through 404–0246, 404–0401 through 404–0460, 404–0601 through 404–0695, and 404– 0801 through 404–0859. 642 and 411–0001 through 411–0250. 411–0251 through 411–0300. 667, 414–0001 through 414–0099, 414–0151 through 414–0175, 414–0251 through 414–0280, 414–0351 through 414–0437, 414–0451 through 414–0550, 414–0601 through 414–0655, 414–0801 through 414–0855, and 414–0901 through 414–0965. 414A0001 through 414A0121, 414A0201 through 414A0340, 414A0401 through 414A0535, 414A0601 through 414A0680, 414A0801 through 414A0858, and 414A1001 through 414A1212. 693 and 421–0001 through 421–0200. 421A0001 through 421A0158. 421B0001 through 421B0056, 421B0101 through 421B0147, 421B0201 through 421B0275, 421B0301 through 421B0486, 421B0501 through 421B0665, and 421B0801 through 421B0970. 421C0001 through 421C0171, 421C0201 through 421C0350, 421C0401 through 421C0525, 421C0601 through 421C0715, 421C0801 through 421C0910, 421C1001 through 421C1115, 421C1201 through 421C1257, 421C1401 through 421C1413, and 421C1801 through 421C1807. 425–0001 through 425–0236. 698 and 441–0001 through 441–0362. 402C 404 ... 411 ... 411A 414 ... 414A 421 ... 421A 421B 421C 425 ... 441 ... What is the Unsafe Condition Presented in This AD? (d) This AD is the result of reports of smoke and a burning smell in the cockpit. The actions specified in this AD are intended VerDate Aug<31>2005 16:47 Oct 11, 2005 Jkt 208001 to prevent failure of the avionics bus circuit breaker switch, which could result in smoke and a burning smell in the cockpit. This failure could lead to reduced ability to control the airplane. PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 What Must I do to Address This Problem? (e) To address this problem, you must do the following: E:\FR\FM\12OCR1.SGM 12OCR1 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

Agencies

[Federal Register Volume 70, Number 196 (Wednesday, October 12, 2005)]
[Rules and Regulations]
[Pages 59237-59240]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-19928]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21173; Directorate Identifier 2005-CE-22-AD; 
Amendment 39-14321; AD 2005-20-25]
RIN 2120-AA64


Airworthiness Directives; The Cessna Aircraft Company Models 401, 
401A, 401B, 402, 402A, 402B, 402C, 404, 411, 411A, 414, 414A, 421, 
421A, 421B, 421C, 425, and 441 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain 
The Cessna Aircraft Company (Cessna) Models 401, 401A, 401B, 402, 402A, 
402B, 402C, 404, 411, 411A, 414, 414A, 421, 421A, 421B, 421C, 425, and 
441 airplanes equipped with certain avionics bus circuit breaker 
switches.

[[Page 59238]]

This AD requires you to inspect the avionics bus circuit breaker switch 
to determine the date code and replace any without a date code. This AD 
also imposes a 1,000-hour safe life limit on avionics bus circuit 
breaker switches with a date code earlier than 0434. This AD results 
from reports of smoke and a burning smell in the cockpit. We are 
issuing this AD to prevent failure of the avionics bus circuit breaker 
switch, which could result in smoke and a burning smell in the cockpit. 
This failure could lead to reduced ability to control the airplane.

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 The Cessna Aircraft Company, Product Support P.O. Box 7706, 
Wichita, Kansas 67277; telephone: (316) 517-5800; facsimile: (316) 942-
9006.
    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.

FOR FURTHER INFORMATION CONTACT: Gerald Pilj, Aerospace Engineer, FAA, 
Wichita ACO, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 
67209; telephone: (316) 946-4151; facsimile: (316) 946-4107.

SUPPLEMENTARY INFORMATION:

Discussion

    What events have caused this AD? We have received failure reports 
of certain Tyco Electronics circuit breaker switches installed on the 
master avionics bus of Cessna Models 401, 401A, 401B, 402, 402A, 402B, 
402C, 404, 411, 411A, 414, 414A, 421, 421A, 421B, 421C, 425, and 441 
airplanes. Failure of these circuit breaker switches causes smoke and a 
burning smell in the cockpit.
    Analysis of the circuit breaker switch revealed the copper braid 
inside the switch had frayed. Continued use causes an internal short. 
The internal short could result in the internal switch components or 
external wiring melting because it is no longer protected by the 
circuit breaker.
    The affected circuit breaker switches have a date code earlier than 
0434 or do not have a date code on them.
    The date code consists of four digits. The first two represent the 
year and the last two represent the week of the year the part was made.
    What is the potential impact if FAA took no action? If not 
prevented, failure of the avionics bus circuit breaker switch could 
cause smoke and a burning smell in the cockpit. This failure could lead 
to reduced ability to control the airplane.
    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 Cessna Models 401, 401A, 
401B, 402, 402A, 402B, 402C, 404, 411, 411A, 414, 414A, 421, 421A, 
421B, 421C, 425, and 441 airplanes equipped with certain avionics bus 
circuit breaker switches. This proposal was published in the Federal 
Register as a notice of proposed rulemaking (NPRM) on June 9, 2005 (70 
FR 33720). The NPRM proposed to require you to:

--inspect the avionics bus circuit breaker switch to determine the date 
code;
--replace all avionics bus circuit breaker switches without a date 
code; and
--implement a 1,000-hour safe life limit for all avionics bus circuit 
breaker switches with a date code earlier than 0434.

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 7,125 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 accomplish the 
inspection and replacement:
    For Models 401, 401A, 401B, 402, 402A, 402B, 402C, 404, 411, 411A, 
414, 414A, 421, 421A, 421B, and 421C airplanes:

----------------------------------------------------------------------------------------------------------------
                                                                                            Total cost on U.S.
              Labor cost                     Parts cost         Total cost per airplane         operators
----------------------------------------------------------------------------------------------------------------
4 work hours x $65 an hour = $260....  $119 each.............  $498 (if 2 switches are   $498 x 6,527 =
                                                                required)..               $3,250,446.
----------------------------------------------------------------------------------------------------------------

    For Models 425 and 441 airplanes:

----------------------------------------------------------------------------------------------------------------
                                                                                            Total cost on U.S.
              Labor cost                     Parts cost         Total cost per airplane         operators
----------------------------------------------------------------------------------------------------------------
8 work hours x $65 an hour = $520....  $119 each.............  $758 (if 2 switches are   $758 x 598 = $453,284.
                                                                required)..
----------------------------------------------------------------------------------------------------------------


[[Page 59239]]

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 this summary by sending a 
request to us at the address listed under ADDRESSES. Include ``Docket 
No. FAA-2005-21173; Directorate Identifier 2005-CE-22-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:

2005-20-25 The Cessna Aircraft Company: Amendment 39-14321; Docket 
No. FAA-2005-21173; Directorate Identifier 2005-CE-22-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 airplane models and serial 
numbers that are:
    (1) Equipped with an avionics bus circuit breaker switch, part 
number (P/N) CM3589-50, 593-250-101, 593-250-102, W31-X2M5A-50, or 
W31-X1000-50; and
    (2) certificated in any category:

------------------------------------------------------------------------
       Model                           Serial numbers
------------------------------------------------------------------------
401...............  655 and 401-0001 through 401-0322.
401A..............  655 and 401A0001 through 401A0132.
401B..............  401B0001 through 401B0221.
402...............  402-0001 through 402-0322.
402A..............  402A0001 through 402A0129.
402B..............  402B0001 through 402B0122, 402B0201 through
                     402B0249, 402B0301 through 402B0455, 402B0501
                     through 402B0640, 402B0801 through 402B0935,
                     402B1001 through 402B1100, 402B1201 through
                     402B1250, and 402B1301 through 402B1384.
402C..............  689, 402C0001 through 402C0125, 402C0201 through
                     402C0355, 402C0401 through 402C0528, 402C0601
                     through 402C0653, 402C0801 through 402C0807, and
                     402C0808 through 402C1020.
404...............  682, 404-0001 through 404-0136, 404-0201 through 404-
                     0246, 404-0401 through 404-0460, 404-0601 through
                     404-0695, and 404-0801 through 404-0859.
411...............  642 and 411-0001 through 411-0250.
411A..............  411-0251 through 411-0300.
414...............  667, 414-0001 through 414-0099, 414-0151 through 414-
                     0175, 414-0251 through 414-0280, 414-0351 through
                     414-0437, 414-0451 through 414-0550, 414-0601
                     through 414-0655, 414-0801 through 414-0855, and
                     414-0901 through 414-0965.
414A..............  414A0001 through 414A0121, 414A0201 through
                     414A0340, 414A0401 through 414A0535, 414A0601
                     through 414A0680, 414A0801 through 414A0858, and
                     414A1001 through 414A1212.
421...............  693 and 421-0001 through 421-0200.
421A..............  421A0001 through 421A0158.
421B..............  421B0001 through 421B0056, 421B0101 through
                     421B0147, 421B0201 through 421B0275, 421B0301
                     through 421B0486, 421B0501 through 421B0665, and
                     421B0801 through 421B0970.
421C..............  421C0001 through 421C0171, 421C0201 through
                     421C0350, 421C0401 through 421C0525, 421C0601
                     through 421C0715, 421C0801 through 421C0910,
                     421C1001 through 421C1115, 421C1201 through
                     421C1257, 421C1401 through 421C1413, and 421C1801
                     through 421C1807.
425...............  425-0001 through 425-0236.
441...............  698 and 441-0001 through 441-0362.
------------------------------------------------------------------------

What is the Unsafe Condition Presented in This AD?

    (d) This AD is the result of reports of smoke and a burning 
smell in the cockpit. The actions specified in this AD are intended 
to prevent failure of the avionics bus circuit breaker switch, which 
could result in smoke and a burning smell in the cockpit. This 
failure could lead to reduced ability to control the airplane.

What Must I do to Address This Problem?

    (e) To address this problem, you must do the following:

[[Page 59240]]



------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Inspect the avionics bus  Within the next 200   For Models 425 and
 circuit breaker switch to     hours time-in-        441 airplanes,
 determine the part number     service (TIS), the    follow the
 (P/N) and date code. (i) If   next 12 months, or    procedures in
 the P/N is CM3589-50, 593-    at the next           Cessna Conquest
 250-101, 593-250-102, W31-    scheduled             Service Bulletin
 X2M5A-50, or W31-X1000-50;    inspection, after     CQB05-2, dated
 and (ii) The date code is     November 9, 2005      February 21, 2005,
 0434 or later; then (iii)     (the effective date   and the applicable
 No further action is          of this AD),          maintenance manual.
 required.                     whichever occurs      For all other
                               first.                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,  Before further        For Models 425 and
 593-250-101, 593-250-102,     flight after the      441 airplanes,
 W31-X2M5A-50, or W31-X1000-   inspection required   follow the
 50 and there is no date       in paragraph (e)(1)   procedures in
 code, replace the avionics    of this AD.           Cessna Conquest
 bus circuit breaker switch                          Service Bulletin
 with a P/N CM3589-50 that                           CQB05-2, dated
 has a date code of 0434 or                          February 21, 2005,
 later.                                              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,  Within the 1,000-     For Models 425 and
 593-250-101, 593-250-102,     hour TIS safe life    441 airplanes,
 W31-X2M5A-50, or W31-X1000-   limit.                follow the
 50, or W31-X1000-50 and the                         procedures in
 date code is earlier than                           Cessna Conquest
 0434, the part has a safe                           Service Bulletin
 life limit of 1,000 hours                           CQB05-2, dated
 TIS and must be replaced                            February 21, 2005,
 within the 1,000-hour time                          and the applicable
 limit with a P/N CM3589-50                          maintenance manual.
 that has a date code of                             For all other
 0434 or later.                                      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      As of November 9,     Not applicable.
 CM3589-50, 593-250-101, 593-  2005 (the effective
 250-102, W31-X2M5A-50, or     date of this AD).
 W31-X1000-50 that does not
 have a date code or has a
 date code earlier than 0434.
------------------------------------------------------------------------

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, Mid-
Continent 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