Airworthiness Directives; Raytheon Aircraft Company (The Beech Aircraft Company and BEECH Previously Held Type Certificate Nos. 3A15, 3A16, 5A3, and A-777) Models 35-33, 35-A33, 35-B33, 35-C33, E33, F33, G33, 35-C33A, E33A, F33A, E33C, F33C, 35, A35, B35, C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35, V35A, V35B, 36, A36, A45 (T-34A, B45), D45 (T-34B), 95-55, 95-A55, 95-B55, 95-B55A, 95-B55B (T-42A), 95-C55, 95-C55A, D55, D55A, E55, E55A, 56TC, A56TC, 58, 95, B95, B95A, D95A, and E95 Airplanes, 71494-71497 [E6-20970]

Download as PDF 71494 Federal Register / Vol. 71, No. 237 / Monday, December 11, 2006 / Proposed Rules examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.’’ Actions Accomplished in Accordance With Previous Revision of Service Bulletin (g) Actions done before the effective date of this AD in accordance with Bombardier Service Bulletin 8–24–83, dated December 23, 2004, are acceptable for compliance with the corresponding requirements in paragraph (f) of this AD. Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, New York Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (i) Canadian airworthiness directive CF– 2006–15, dated June 14, 2006, also addresses the subject of this AD. Issued in Renton, Washington, on December 1, 2006. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–20969 Filed 12–8–06; 8:45 am] mstockstill on PROD1PC61 with PROPOSALS BILLING CODE 4910–13–P VerDate Aug<31>2005 14:58 Dec 08, 2006 Jkt 211001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26075; Directorate Identifier 2006–CE–55–AD] RIN 2120–AA64 Airworthiness Directives; Raytheon Aircraft Company (The Beech Aircraft Company and BEECH Previously Held Type Certificate Nos. 3A15, 3A16, 5A3, and A–777) Models 35–33, 35–A33, 35– B33, 35–C33, E33, F33, G33, 35–C33A, E33A, F33A, E33C, F33C, 35, A35, B35, C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35, V35A, V35B, 36, A36, A45 (T–34A, B45), D45 (T– 34B), 95–55, 95–A55, 95–B55, 95–B55A, 95–B55B (T–42A), 95–C55, 95–C55A, D55, D55A, E55, E55A, 56TC, A56TC, 58, 95, B95, B95A, D95A, and E95 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: We propose to supersede Airworthiness Directive (AD) 72–22–01, which applies to certain Raytheon Aircraft Company (RAC) (The Beech Aircraft Company and BEECH previously held Type Certificate Nos. 3A15, 3A16, 5A3, and A–777) Models 33, 35, 36, 45, and 95 series airplanes. AD 72–22–01 currently requires you to determine if each uplock roller is of the greasible type (one having a drilled and grooved inner race), replace any nongreasible uplock roller (one having a solid inner race) with the greasible type before further flight, install hollow zerkended mounting bolts on the uplock rollers, and repetitively lubricate the uplock mechanism. Since we issued AD 72–22–01, there was a recent incident involving a RAC Model 95–B55B (T– 42A) airplane where a seizure of the uplock rollers occurred. This malfunction of the uplock rollers is addressed in AD 72–22–01. Thus, the FAA has determined that the actions of AD 72–22–01 should also apply to certain serial numbers of the Model 95– B55B (T–42A) airplanes. Consequently, this proposed AD would retain all the actions of AD 72–22–01, would add those Model 95–B55B (T–42A) airplanes to the applicability of this proposed AD, and would list out the specific serial numbers. We are proposing this AD to decrease the possibility of gear-up landings caused by seizure of the uplock rollers. PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 We must receive comments on this proposed AD by February 9, 2007. ADDRESSES: Use one of the following addresses to comment on this proposed AD: • DOT Docket web site: Go to https:// dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201–0085; telephone: (800) 429–5372 or (316) 676–3140. FOR FURTHER INFORMATION CONTACT: Anthony Flores, Aerospace Engineer, Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Wichita, Kansas 67209; telephone: (316) 946–4174; facsimile: (316) 946–4107. SUPPLEMENTARY INFORMATION: DATES: Comments Invited We invite you to send any written relevant data, views, or arguments regarding this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number, ‘‘FAA–2006–26075; Directorate Identifier 2006–CE–55–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive concerning this proposed AD. Discussion Reports of RAC 33, 35, 36, 45, and 95 series airplanes equipped with nongreasible uplock rollers having a solid inner race that renders lubrication of the uplock roller mechanism ineffective E:\FR\FM\11DEP1.SGM 11DEP1 Federal Register / Vol. 71, No. 237 / Monday, December 11, 2006 / Proposed Rules caused us to issue AD 72–22–01, Amendment 39–1544 (37 FR 22371, October 19, 1972). AD 72–22–01 currently requires the following on certain RAC 33, 35, 36, 45, and 95 series airplanes: • Determining if each uplock roller is of the greasible type (one having a drilled and grooved inner race); • Replacing any nongreasible uplock roller (one having a solid inner race) with the greasible type before further flight; • Installing a hollow zerk-ended mounting bolts on the uplock rollers; and • Repetitively lubricating the uplock mechanism. Since we issued AD 72–22–01, there was a recent incident involving a RAC Model 95–B55B (T–42A) airplane where a seizure of the uplock rollers occurred. The design of the uplock rollers is the same as those uplock rollers on the airplanes addressed by AD 72–22–01. This condition, if not corrected, could result in a gear-up landing. Relevant Service Information We have reviewed Beechcraft Service Instructions No. 0448–211, Rev. I, and Beechcraft Service Instructions No. 0448–211. The service information describes procedures for: • Determining if each uplock roller is of the greasible type (one having a drilled and grooved inner race); • Replacing any nongreasible uplock roller (one having a solid inner race) with the greasible type before further flight; • Installing a hollow zerk-ended mounting bolts on the uplock rollers; and • Repetitively lubricating the uplock mechanism. FAA’s Determination and Requirements of the Proposed AD We are proposing this AD because we evaluated all information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design. This proposed AD would supersede AD 72–22–01 with a new AD that would retain all the actions of AD 71495 72–22–01, would add those Model 95– B55B (T–42A) airplanes to the applicability of this proposed AD, and would list out the specific serial numbers. This proposed AD would require you to use the service information described previously to perform these actions. Costs of Compliance We estimate that this proposed AD would affect 9,714 airplanes in the U.S. registry. The differences in costs between this proposed AD and AD 72–22–01 are the costs associated with the number of Model 95–B55B (T–42A) airplanes that were not affected by AD 72–22–01. We estimate the following costs to do the proposed actions to determine if each uplock roller is of the greasible type (one having a drilled and grooved inner race), replace any nongreasible uplock roller (one having a solid inner race) with the greasible type before further flight, install hollow zerk-ended mounting bolts on the uplock rollers, and initially lubricate the uplock mechanism: Labor cost Parts cost Total cost per airplane Total cost on U.S. operators 2 work-hours × $80 per hour = $160 ........................................................................................................ $30 $190 $1,845,660 Labor cost Parts cost Total cost per airplane Total cost on U.S. operators 1 work-hour × $80 per hour = $80 ............................................................................................................ None $80 $777,120 We estimate the following costs for each lubrication of the uplock mechanism. mstockstill on PROD1PC61 with PROPOSALS 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 VerDate Aug<31>2005 14:58 Dec 08, 2006 Jkt 211001 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 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 regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket that contains the proposed AD, the regulatory evaluation, any comments received, and other information on the Internet at https://dms.dot.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., E:\FR\FM\11DEP1.SGM 11DEP1 71496 Federal Register / Vol. 71, No. 237 / Monday, December 11, 2006 / Proposed Rules Identifier 2006–CE–55–AD; Supersedes AD 72–22–01; Amendment 39–1544. Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. PART 39—AIRWORTHINESS DIRECTIVES List of Subjects in 14 CFR Part 39 § 39.13 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 72–22–01, Amendment 39–1544, and adding the following new AD: Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: Raytheon Aircraft Company (The Beech Aircraft Company and BEECH previously held Type Certificate Nos. 3A15, 3A16, 5A3, and A–777): Docket No. FAA–2006–26075; Directorate 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] Comments Due Date (a) We must receive comments on this airworthiness directive (AD) action by February 9, 2007. Affected ADs (b) This AD supersedes AD 72–22–01, Amendment 39–1544. Unsafe Condition (c) This AD applies to the following airplane models and serial numbers (SNs) that are certificated in any category: (1) Group 1 (maintains the actions from AD 72–22–01): Model SNs (i) 35–33, 35–A33, 35–B33, 35–C33, E33, F33, and G33 ............................................................................................ (ii) 35–C33A, E33A, and F33A ....................................................................................................................................... (iii) E33C and F33C ........................................................................................................................................................ (iv) 35, A35, B35, C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35, V35A, and V35B ............... (v) 36 and A36 ................................................................................................................................................................ (vi) A45 (T–34A, B45) and D45 (T–34B) ....................................................................................................................... (vii) 95–55, 95–A55, 95–B55, and 95–B55A .................................................................................................................. (viii) 95–C55, 95–C55A, D55, D55A, E55, and E55A .................................................................................................... (ix) 56TC and A56TC ..................................................................................................................................................... (x) 58 ............................................................................................................................................................................... (xi) 95, B95, B95A, D95A, and E95 ............................................................................................................................... (2) Group 2: Model 95-B55B (T–42A) airplanes, SNs TF–1 through TF–70. Unsafe Condition (d) This AD results from a recent incident involving a Raytheon Aircraft Company (RAC) Model 95–B55B (T–42A) airplane where a seizure of the uplock rollers occurred. We are issuing this AD to decrease the possibility of gear-up landings caused by seizure of the uplock rollers. CD–1 through CD–1256. CE–1 through CE–349. CJ–1 through CJ–30. D–1 through D–9287. E1 through E–283. All. TC–1 through TC–1402. TE–1 through TE–846. TG–1 through TG–94. TH–1 through TH–174. TD–2 through TD–721. Compliance (e) To address this problem, you must do the following, unless already done: Actions Compliance Procedures (1) Determine if each uplock roller is of the greasible type (one having a drilled and grooved inner race). (A) For Group 1 airplanes: Within 300 hours time-in-service (TIS) after October 25, 1972 (the effective date of AD 72–22–01). (B) For Group 2 airplanes: Within 300 hours TIS after the effective date of this AD. (A) For Group 1 airplanes: Before further flight after the determination required by paragraph (e)(1)(A) of this AD. (B) For Group 2 airplanes: Before further flight after the determination required by paragraph (e)(1)(B) of this AD. (A) For Group 1 airplanes: Within 300 hours TIS after October 25, 1972 (the effective date of AD 72–22–01). (B) For Group 2 airplanes: Within 300 hours TIS after the effective date of this AD. (A) For Group 1 airplanes: Initially within 300 hours TIS after October 25, 1972 (the effective date of AD 72–22–01). Repetitively lubricate thereafter at intervals not to exceed 100 hours TIS. (B) For Group 2 airplanes: Initially within 300 hours TIS after the effective date of this AD. Repetitively lubricate thereafter at intervals not to exceed 100 hours TIS. Follow Beechcraft Service Instructions No. 0448–211, Rev. I, or Beechcraft Service Instructions No. 0448–211. (2) Replace any nongreasible uplock roller (one having a solid inner race) with the greasible type. (3) Install hollow zerk-ended mounting bolts on the uplock rollers. mstockstill on PROD1PC61 with PROPOSALS (4) Lubricate the uplock mechanism .................. Alternative Methods of Compliance (AMOCs) (f) The Manager, Wichita Aircraft Certification Office, FAA, ATTN: Anthony VerDate Aug<31>2005 14:58 Dec 08, 2006 Jkt 211001 Flores, Aerospace Engineer, 1801 Airport Road, Wichita, Kansas 67209; telephone: (316) 946–4174; facsimile: (316) 946–4107, has the authority to approve AMOCs for this PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Follow Beechcraft Service Instructions No. 0448–211, Rev. I, or Beechcraft Service Instructions No. 0448–211. Follow Beechcraft Service Instructions No. 0448–211, Rev. I, or Beechcraft Service Instructions No. 0448–211. Follow Beechcraft Service Instructions No. 0448–211, Rev. I, or Beechcraft Service Instructions No. 0448–211. AD, if requested using the procedures found in 14 CFR 39.19. (g) AMOCs approved for AD 72–22–01 are approved for this AD. E:\FR\FM\11DEP1.SGM 11DEP1 Federal Register / Vol. 71, No. 237 / Monday, December 11, 2006 / Proposed Rules Related Information (h) To get copies of the service information referenced in this AD, contact Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201–0085; telephone: (800) 429– 5372 or (316) 676–3140. 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, or on the Internet at https://dms.dot.gov. The docket number is Docket No. FAA–2006–26075; Directorate Identifier 2006–CE–55–AD. Issued in Kansas City, Missouri, on December 4, 2006. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–20970 Filed 12–8–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26371; Directorate Identifier 2006–CE–70–AD] RIN 2120–AA64 Airworthiness Directives; Pilatus Aircraft Limited PC–12 and PC–12/45 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). mstockstill on PROD1PC61 with PROPOSALS AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as executive seats equipped with pedestal legs that were produced using a material that deviates from the approved design data. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by January 10, 2007. ADDRESSES: You may send comments by any of the following methods: • DOT Docket Web Site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Fax: (202) 493–2251. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, VerDate Aug<31>2005 14:58 Dec 08, 2006 Jkt 211001 71497 Room PL–401, Washington, DC 20590– 0001. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Federal eRulemaking Portal: https:// www.regulations.gov. Follow the instructions for submitting comments. closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Examining the AD Docket You may examine the AD docket on the Internet at https://dms.dot.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647– 5227) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, 901 Locust, Room 301; telephone (816) 329– 4059; fax (816) 329–4090. SUPPLEMENTARY INFORMATION: Discussion The Federal Office of Civil Aviation (FOCA), which is the aviation authority for Switzerland, has issued FOCA AD HB–2006–444, dated November 7, 2006 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states that executive seats equipped with pedestal legs were produced using a material that deviates from the approved design data. As a consequence the pedestal legs may not perform as intended under emergency landing conditions. In order to correct and control the situation, this AD requires a one time inspection to identify the Vendor Part Number (VPN) of the pedestal legs and the Serial Number (S/N) of the executive seat and the replacement of the pedestal legs if necessary. You may obtain further information by examining the MCAI in the AD docket. Streamlined Issuance of AD The FAA is implementing a new process for streamlining the issuance of ADs related to MCAI. The streamlined process will allow us to adopt MCAI safety requirements in a more efficient manner and will reduce safety risks to the public. This process continues to follow all FAA AD issuance processes to meet legal, economic, Administrative Procedure Act, and Federal Register requirements. We also continue to meet our technical decision-making responsibilities to identify and correct unsafe conditions on U.S.-certificated products. This proposed AD references the MCAI and related service information that we considered in forming the engineering basis to correct the unsafe condition. The proposed AD contains text copied from the MCAI and for this reason might not follow our plain language principles. Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2006–26371; Directorate Identifier 2006–CE–70–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 Relevant Service Information Pilatus Aircraft Limited has issued Service Bulletin No.: 25–032, dated October 2, 2006, and DeCrane Aircraft Seating Company, Inc. has issued Mandatory Service Bulletin SB05147 Revision B, dated June 26, 2006. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of the Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between This Proposed AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in E:\FR\FM\11DEP1.SGM 11DEP1

Agencies

[Federal Register Volume 71, Number 237 (Monday, December 11, 2006)]
[Proposed Rules]
[Pages 71494-71497]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-20970]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26075; Directorate Identifier 2006-CE-55-AD]

RIN 2120-AA64


Airworthiness Directives; Raytheon Aircraft Company (The Beech 
Aircraft Company and BEECH Previously Held Type Certificate Nos. 3A15, 
3A16, 5A3, and A-777) Models 35-33, 35-A33, 35-B33, 35-C33, E33, F33, 
G33, 35-C33A, E33A, F33A, E33C, F33C, 35, A35, B35, C35, D35, E35, F35, 
G35, H35, J35, K35, M35, N35, P35, S35, V35, V35A, V35B, 36, A36, A45 
(T-34A, B45), D45 (T-34B), 95-55, 95-A55, 95-B55, 95-B55A, 95-B55B (T-
42A), 95-C55, 95-C55A, D55, D55A, E55, E55A, 56TC, A56TC, 58, 95, B95, 
B95A, D95A, and E95 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 72-22-01, 
which applies to certain Raytheon Aircraft Company (RAC) (The Beech 
Aircraft Company and BEECH previously held Type Certificate Nos. 3A15, 
3A16, 5A3, and A-777) Models 33, 35, 36, 45, and 95 series airplanes. 
AD 72-22-01 currently requires you to determine if each uplock roller 
is of the greasible type (one having a drilled and grooved inner race), 
replace any nongreasible uplock roller (one having a solid inner race) 
with the greasible type before further flight, install hollow zerk-
ended mounting bolts on the uplock rollers, and repetitively lubricate 
the uplock mechanism. Since we issued AD 72-22-01, there was a recent 
incident involving a RAC Model 95-B55B (T-42A) airplane where a seizure 
of the uplock rollers occurred. This malfunction of the uplock rollers 
is addressed in AD 72-22-01. Thus, the FAA has determined that the 
actions of AD 72-22-01 should also apply to certain serial numbers of 
the Model 95-B55B (T-42A) airplanes. Consequently, this proposed AD 
would retain all the actions of AD 72-22-01, would add those Model 95-
B55B (T-42A) airplanes to the applicability of this proposed AD, and 
would list out the specific serial numbers. We are proposing this AD to 
decrease the possibility of gear-up landings caused by seizure of the 
uplock rollers.

DATES: We must receive comments on this proposed AD by February 9, 
2007.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD:
     DOT Docket web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085; 
telephone: (800) 429-5372 or (316) 676-3140.

FOR FURTHER INFORMATION CONTACT: Anthony Flores, Aerospace Engineer, 
Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 
Airport Road, Wichita, Kansas 67209; telephone: (316) 946-4174; 
facsimile: (316) 946-4107.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include the docket number, ``FAA-
2006-26075; Directorate Identifier 2006-CE-55-AD'' at the beginning of 
your comments. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the proposed 
AD. We will consider all comments received by the closing date and may 
amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact we 
receive concerning this proposed AD.

Discussion

    Reports of RAC 33, 35, 36, 45, and 95 series airplanes equipped 
with non-greasible uplock rollers having a solid inner race that 
renders lubrication of the uplock roller mechanism ineffective

[[Page 71495]]

caused us to issue AD 72-22-01, Amendment 39-1544 (37 FR 22371, October 
19, 1972). AD 72-22-01 currently requires the following on certain RAC 
33, 35, 36, 45, and 95 series airplanes:
     Determining if each uplock roller is of the greasible type 
(one having a drilled and grooved inner race);
     Replacing any nongreasible uplock roller (one having a 
solid inner race) with the greasible type before further flight;
     Installing a hollow zerk-ended mounting bolts on the 
uplock rollers; and
     Repetitively lubricating the uplock mechanism.
    Since we issued AD 72-22-01, there was a recent incident involving 
a RAC Model 95-B55B (T-42A) airplane where a seizure of the uplock 
rollers occurred. The design of the uplock rollers is the same as those 
uplock rollers on the airplanes addressed by AD 72-22-01.
    This condition, if not corrected, could result in a gear-up 
landing.

Relevant Service Information

    We have reviewed Beechcraft Service Instructions No. 0448-211, Rev. 
I, and Beechcraft Service Instructions No. 0448-211.
    The service information describes procedures for:
     Determining if each uplock roller is of the greasible type 
(one having a drilled and grooved inner race);
     Replacing any nongreasible uplock roller (one having a 
solid inner race) with the greasible type before further flight;
     Installing a hollow zerk-ended mounting bolts on the 
uplock rollers; and
     Repetitively lubricating the uplock mechanism.

FAA's Determination and Requirements of the Proposed AD

    We are proposing this AD because we evaluated all information and 
determined the unsafe condition described previously is likely to exist 
or develop on other products of the same type design. This proposed AD 
would supersede AD 72-22-01 with a new AD that would retain all the 
actions of AD 72-22-01, would add those Model 95-B55B (T-42A) airplanes 
to the applicability of this proposed AD, and would list out the 
specific serial numbers. This proposed AD would require you to use the 
service information described previously to perform these actions.

Costs of Compliance

    We estimate that this proposed AD would affect 9,714 airplanes in 
the U.S. registry.
    The differences in costs between this proposed AD and AD 72-22-01 
are the costs associated with the number of Model 95-B55B (T-42A) 
airplanes that were not affected by AD 72-22-01.
    We estimate the following costs to do the proposed actions to 
determine if each uplock roller is of the greasible type (one having a 
drilled and grooved inner race), replace any nongreasible uplock roller 
(one having a solid inner race) with the greasible type before further 
flight, install hollow zerk-ended mounting bolts on the uplock rollers, 
and initially lubricate the uplock mechanism:

------------------------------------------------------------------------
                                              Total cost  Total cost  on
          Labor cost             Parts cost      per           U.S.
                                               airplane      operators
------------------------------------------------------------------------
2 work-hours x $80 per hour =          $30         $190      $1,845,660
 $160.........................
------------------------------------------------------------------------

    We estimate the following costs for each lubrication of the uplock 
mechanism.

------------------------------------------------------------------------
                                              Total cost  Total cost  on
          Labor cost             Parts cost      per           U.S.
                                               airplane      operators
------------------------------------------------------------------------
1 work-hour x $80 per hour =          None          $80        $777,120
 $80..........................
------------------------------------------------------------------------

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    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 regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket that contains the proposed AD, the 
regulatory evaluation, any comments received, and other information on 
the Internet at https://dms.dot.gov; or in person at the Docket 
Management Facility between 9 a.m. and 5 p.m.,

[[Page 71496]]

Monday through Friday, except Federal holidays. The Docket Office 
(telephone (800) 647-5227) is located at the street address stated in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing Airworthiness Directive 
(AD) 72-22-01, Amendment 39-1544, and adding the following new AD:

Raytheon Aircraft Company (The Beech Aircraft Company and BEECH 
previously held Type Certificate Nos. 3A15, 3A16, 5A3, and A-777): 
Docket No. FAA-2006-26075; Directorate Identifier 2006-CE-55-AD; 
Supersedes AD 72-22-01; Amendment 39-1544.

Comments Due Date

    (a) We must receive comments on this airworthiness directive 
(AD) action by February 9, 2007.

Affected ADs

    (b) This AD supersedes AD 72-22-01, Amendment 39-1544.

Unsafe Condition

    (c) This AD applies to the following airplane models and serial 
numbers (SNs) that are certificated in any category:
    (1) Group 1 (maintains the actions from AD 72-22-01):

------------------------------------------------------------------------
               Model                                 SNs
------------------------------------------------------------------------
(i) 35-33, 35-A33, 35-B33, 35-C33,  CD-1 through CD-1256.
 E33, F33, and G33.
(ii) 35-C33A, E33A, and F33A......  CE-1 through CE-349.
(iii) E33C and F33C...............  CJ-1 through CJ-30.
(iv) 35, A35, B35, C35, D35, E35,   D-1 through D-9287.
 F35, G35, H35, J35, K35, M35,
 N35, P35, S35, V35, V35A, and
 V35B.
(v) 36 and A36....................  E1 through E-283.
(vi) A45 (T-34A, B45) and D45 (T-   All.
 34B).
(vii) 95-55, 95-A55, 95-B55, and    TC-1 through TC-1402.
 95-B55A.
(viii) 95-C55, 95-C55A, D55, D55A,  TE-1 through TE-846.
 E55, and E55A.
(ix) 56TC and A56TC...............  TG-1 through TG-94.
(x) 58............................  TH-1 through TH-174.
(xi) 95, B95, B95A, D95A, and E95.  TD-2 through TD-721.
------------------------------------------------------------------------

    (2) Group 2: Model 95-B55B (T-42A) airplanes, SNs TF-1 through 
TF-70.

Unsafe Condition

    (d) This AD results from a recent incident involving a Raytheon 
Aircraft Company (RAC) Model 95-B55B (T-42A) airplane where a 
seizure of the uplock rollers occurred. We are issuing this AD to 
decrease the possibility of gear-up landings caused by seizure of 
the uplock rollers.

Compliance

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

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Determine if each uplock  (A) For Group 1       Follow Beechcraft
 roller is of the greasible    airplanes: Within     Service
 type (one having a drilled    300 hours time-in-    Instructions No.
 and grooved inner race).      service (TIS) after   0448-211, Rev. I,
                               October 25, 1972      or Beechcraft
                               (the effective date   Service
                               of AD 72-22-01).      Instructions No.
                                                     0448-211.
                              (B) For Group 2
                               airplanes: Within
                               300 hours TIS after
                               the effective date
                               of this AD.
(2) Replace any nongreasible  (A) For Group 1       Follow Beechcraft
 uplock roller (one having a   airplanes: Before     Service
 solid inner race) with the    further flight        Instructions No.
 greasible type.               after the             0448-211, Rev. I,
                               determination         or Beechcraft
                               required by           Service
                               paragraph (e)(1)(A)   Instructions No.
                               of this AD.           0448-211.
                              (B) For Group 2
                               airplanes: Before
                               further flight
                               after the
                               determination
                               required by
                               paragraph (e)(1)(B)
                               of this AD.
(3) Install hollow zerk-      (A) For Group 1       Follow Beechcraft
 ended mounting bolts on the   airplanes: Within     Service
 uplock rollers.               300 hours TIS after   Instructions No.
                               October 25, 1972      0448-211, Rev. I,
                               (the effective date   or Beechcraft
                               of AD 72-22-01).      Service
                                                     Instructions No.
                                                     0448-211.
                              (B) For Group 2
                               airplanes: Within
                               300 hours TIS after
                               the effective date
                               of this AD.
(4) Lubricate the uplock      (A) For Group 1       Follow Beechcraft
 mechanism.                    airplanes:            Service
                               Initially within      Instructions No.
                               300 hours TIS after   0448-211, Rev. I,
                               October 25, 1972      or Beechcraft
                               (the effective date   Service
                               of AD 72-22-01).      Instructions No.
                               Repetitively          0448-211.
                               lubricate
                               thereafter at
                               intervals not to
                               exceed 100 hours
                               TIS.
                              (B) For Group 2
                               airplanes:
                               Initially within
                               300 hours TIS after
                               the effective date
                               of this AD.
                               Repetitively
                               lubricate
                               thereafter at
                               intervals not to
                               exceed 100 hours
                               TIS.
------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (f) The Manager, Wichita Aircraft Certification Office, FAA, 
ATTN: Anthony Flores, Aerospace Engineer, 1801 Airport Road, 
Wichita, Kansas 67209; telephone: (316) 946-4174; facsimile: (316) 
946-4107, has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19.
    (g) AMOCs approved for AD 72-22-01 are approved for this AD.

[[Page 71497]]

Related Information

    (h) To get copies of the service information referenced in this 
AD, contact Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 
67201-0085; telephone: (800) 429-5372 or (316) 676-3140. 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, or on the Internet at https://dms.dot.gov. The 
docket number is Docket No. FAA-2006-26075; Directorate Identifier 
2006-CE-55-AD.

    Issued in Kansas City, Missouri, on December 4, 2006.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-20970 Filed 12-8-06; 8:45 am]
BILLING CODE 4910-13-P