Airworthiness Directives; Raytheon Aircraft Company Models 1900, 1900C, and 1900D Airplanes, 70297-70300 [E6-20326]

Download as PDF Federal Register / Vol. 71, No. 232 / Monday, December 4, 2006 / Rules and Regulations the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 14 CFR part 39 as follows: I 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 FAA amends § 39.13 by removing Amendment 39–13183 (68 FR 33621, June 5, 2003) and by adding a new airworthiness directive, Amendment 39–14841, to read as follows: I 2006–25–01 International Aero Engines AG: Amendment 39–14841; Docket No. FAA–2006–26013; Directorate Identifier 2003–NE–21–AD. Effective Date (a) This airworthiness directive (AD) becomes effective January 8, 2007. Affected ADs (b) This AD supersedes AD 2003–11–23, Amendment 39–13183. mstockstill on PROD1PC61 with RULES Applicability (c) This AD applies to International Aero Engines AG (IAE) V2522–A5, V2524–A5, V2527–A5, V2527E–A5, V2527M–A5, V2530–A5, and V2533–A5 turbofan engines with engine serial numbers V10601 through V11335 inclusive and bearings part number (P/N) 2A1165 installed. These engines are installed on, but not limited to, Airbus Industrie A319, A320, and A321 series airplanes. Unsafe Condition (d) This AD results from IAE developing a terminating action to the repetitive inspections of the chip detectors, and from expanding the applicability to include additional serial-numbered engines with certain No. 3 bearings installed. We are issuing this AD to prevent failure of the No. 3 bearing, which could result in an IFSD and smoke in the cockpit and cabin. The smoke is a result of oil escaping from the bearing compartment due to a fracture of the No. 3 bearing race. 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. VerDate Aug<31>2005 12:11 Dec 01, 2006 Jkt 211001 Inspection of the Master Magnetic Chip Detector (MCD) or the No. 1, 2, 3 Bearing Chamber MCD (f) For engines listed in Table 1 of Appendix 1 of IAE Service Bulletin (SB) No. V2500–ENG–72–0452, Revision 4, dated September 30, 2005, and that have a No. 3 bearing, P/N 2A1165, installed at new production build, do the following: (1) Within 125 hours time-in-service (TIS) after the effective date of this AD, inspect the master MCD or the No. 1, 2, 3 bearing chamber MCD. (2) Thereafter, within 125 hours timesince-last inspection, inspect the master MCD or the No. 1, 2, 3 bearing chamber MCD. (3) If you find bearing material on the master MCD or No. 1, 2, 3 bearing chamber MCD, remove the engine from service before further flight. Inspection Recommendation (g) We recommend the inspection of the master MCD or the No. 1, 2, 3 bearing chamber MCD, using paragraphs (f) through (f)(3) of this AD, on all engines installed on the same airplane, not be done by the same individual before the same flight. This is to minimize the chances of maintenance error on multiple engine airplanes. Removal of No. 3 Bearing (h) At the next shop visit, for engines listed in Table 1 of Appendix 1 of IAE SB No. V2500–ENG–72–0452, Revision 4, dated September 30, 2005, that have a serial number (SN) from V10601 through V11335 inclusive, and that have a No. 3 bearing, P/N 2A1165 installed at new production, remove the No. 3 bearing. (i) After the effective date of this AD, do not install any No. 3 bearing, P/N 2A1165, removed in paragraph (h) of this AD, into any engine. Removal of High Pressure Compressor (HPC) Stubshaft (j) At the next shop visit, for engines listed in Table 1 of Appendix 1 of IAE SB No. V2500–ENG–72–0452, Revision 4, dated September 30, 2005, that have a SN from V10601 through V11335 inclusive, remove the HPC stubshaft that has a low-energy plasma coating. Terminating Action (k) Performing the requirements specified in paragraph (h) and (j) of this AD is terminating action to the repetitive MCD inspections specified in paragraphs (f) through (f)(3) of this AD. Alternative Methods of Compliance (l) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Material Incorporated by Reference (m) For identifying engines within the engine SN range of V10601 to V11335 inclusive, known to have had P/N 2A1165 installed, you must use Table 1 of Appendix 1 of International Aero Engines Service Bulletin No. V2500–ENG–72–0452, Revision 4, dated September 30, 2005. The Director of PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 70297 the Federal Register approved the incorporation by reference of Table 1 of Appendix 1 of International Aero Engines Service Bulletin No. V2500–ENG–72–0452, Revision 4, dated September 30, 2005, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact International Aero Engines AG, 400 Main Street, East Hartford, CT 06108; telephone: (860) 565–5515; fax: (860) 565–5510, for a copy of this service information. You may review copies at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federalregister/cfr/ibr-locations.html. Related Information (n) The following SBs contain additional information and procedures: (1) You can find information on inspecting the master MCD and the No. 1, 2, 3 bearing chamber MCD in section 79–00–00–601 of the Aircraft Maintenance Manual. (2) Additional information on inspection procedures is included in IAE SB No. V2500– ENG–72–0452, Revision 4, dated September 30, 2005. (3) You can find information on replacing the No. 3 bearing in IAE SB No. V2500–ENG– 72–0459, Revision 3, dated April 12, 2003. (4) You can find information on replacing HPC stubshafts that have a low-energy plasma coating, (all engines) in IAE SB No. V2500–ENG–72–0460, Revision 2, dated March 4, 2006. (o) Airworthiness directive 2003–10–14 and AD 2003–13–02, which revise the Limitation section of the airplane flight manual to incorporate new procedures to follow in the event of smoke in the cockpit and cabin, are related to the subject of this AD. Issued in Burlington, Massachusetts, on November 27, 2006. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E6–20323 Filed 12–1–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26258; Directorate Identifier 2006–CE–67–AD; Amendment 39– 14840; AD 2006–24–11] RIN 2120–AA64 Airworthiness Directives; Raytheon Aircraft Company Models 1900, 1900C, and 1900D Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: E:\FR\FM\04DER1.SGM 04DER1 70298 Federal Register / Vol. 71, No. 232 / Monday, December 4, 2006 / Rules and Regulations SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Raytheon Aircraft Company (RAC) Models 1900, 1900C, and 1900D airplanes. This AD requires you to repetitively inspect the forward, vertical, and aft flanges of both the left and right wing rear spar lower caps for cracks, repair any cracks found, and report the inspection results to RAC. This AD results from additional fatigue cracks found in this area since inspections were performed to comply with Emergency AD 2006–18–51, which required immediate visual inspections of this area. We are issuing this AD for the purpose of performing a more rigorous inspection requiring cleaning and paint stripping of this section of the wing rear spar to detect and correct cracking in the wing spar lower caps of the affected airplanes before the cracks lead to failure. These wing rear spar cracks may result in wing failure which could result in the wing separating from the airplane with consequent loss of control. This AD becomes effective on December 11, 2006. As of December 11, 2006, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation. We must receive any comments on this AD by February 2, 2007. ADDRESSES: Use one of the following addresses to comment on this AD. • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking web site: Go to http://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. To get the service information identified in this AD, contact Raytheon Aircraft Company (RAC), Post Office Box 85, Wichita, Kansas 67201–0085, Phone 1–800–429–5372 or 1–316–676– 2000, Fax: 1–316–676–8745. To view the comments to this AD, go to http://dms.dot.gov. The docket number is FAA–2006–26258; Directorate Identifier 2006–CE–67–AD. FOR FURTHER INFORMATION CONTACT: Steven E. Potter, FAA, 1801 Airport mstockstill on PROD1PC61 with RULES DATES: VerDate Aug<31>2005 12:11 Dec 01, 2006 Jkt 211001 Road, Wichita, Kansas 67209; telephone: (316) 946–4124; fax: (316) 946–4107. SUPPLEMENTARY INFORMATION: Discussion Due to significant cracks found in the wing rear spar of RAC Model 1900D airplanes, we issued Emergency AD 2006–18–51 on August 31, 2006. AD 2006–18–51 required an immediate visual inspection of both the left and right wing rear spars near the outboard edge of the engine nacelle. This AD was then published in the Federal Register as Amendment 39–14757 (71 FR 52983, September 8, 2006). Additional fatigue cracks in the affected area of the wing rear spar have been found since the AD 2006–18–51 inspections were performed. One of the airplanes had accumulated 168 hours time-in-service (TIS) since the visual inspections required by AD 2006–18–51 were done. The FAA has determined a more rigorous and detailed inspection is necessary to find such fatigue cracks. Cracking in the wing rear spar lower caps and adjacent structure, if not corrected, could result in wing failure. Such a wing failure could result in the wing separating from the airplane with consequent loss of control. Relevant Service Information We reviewed Raytheon Aircraft Company Service Bulletin No. 57–3815, Issued: October, 2006. The service information describes procedures for the left and right rear wing spar lower cap inspection. FAA’s Determination and Requirements of This AD We are issuing this AD because we have evaluated all known and available information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design. This AD requires a rigorous and detailed inspection of the wing rear spar lower caps to find the fatigue cracks. The preparation and procedural requirements for these inspections are included in RAC Mandatory Service Bulletin 57–3815. RAC is developing a modification that, if approved by the FAA, would terminate the repetitive inspection requirement of this AD. The FAA may take future rulemaking action on this subject. FAA’s Determination of the Effective Date Since an unsafe condition exists that requires the immediate adoption of this AD, we determined that notice and PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 opportunity for public comment before issuing this AD are impracticable, and that good cause exists for making this amendment effective in fewer than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and an opportunity for public comment. We invite you to send any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number ‘‘FAA– 2006–26258; Directorate Identifier 2006–CE–67–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD. We will consider all comments received by the closing date and may amend the AD in light of those comments. We will post all comments we receive, without change, to http:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive concerning this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. E:\FR\FM\04DER1.SGM 04DER1 Federal Register / Vol. 71, No. 232 / Monday, December 4, 2006 / Rules and Regulations 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. 70299 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. not supersede or revise that AD. Both ADs are necessary to address the unsafe condition. Adoption of the Amendment (c) This AD applies to the following airplane models and serial numbers that are certificated in any category: Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Applicability Models Serial numbers (1) 1900 ..................... (2) 1900C (C–12J) .... UA–3. UB–1 through UB– 74, UC–1 through UC–174, and UD– 1 through UD–6. UE–1 through UE– 439. (3) 1900D .................. Authority: 49 U.S.C. 106(g), 40113, 44701. Examining the AD Docket § 39.13 You may examine the AD docket that contains the AD, the regulatory evaluation, any comments received, and other information on the Internet at http://dms.dot.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The 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. I [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): 2006–24–11 Raytheon Aircraft Company (RAC): Amendment 39–14840; Docket No. FAA–2006–26258; Directorate Identifier 2006–CE–67–AD. Effective Date (a) This AD becomes effective on December 11, 2006. Affected ADs (b) AD 2006–18–51, Amendment 39–14757 (71 FR 52983, September 8, 2006), relates to the subject of this AD. However, this AD does Unsafe Condition (d) This AD is the result of additional fatigue cracks found in the wing rear spar lower caps on a Raytheon Model 1900 airplane shortly after complying with AD 2006–18–51. We are issuing this AD to require a more rigorous and detailed inspection to find the fatigue cracks which are the unsafe condition. Failure to detect cracking in the wing rear spar lower caps of the affected airplanes could result in a wing failure. Such a wing failure could result in the wing separating from the airplane with consequent loss of control. Compliance (e) To address this problem, you must do the following, unless already done: Compliance Procedures (1) Repetitively inspect both the left and right wing rear spar lower caps for cracks and other damage such as loose or missing fasteners. Initially inspect within 100 hours time-in-service (TIS) or 30 days after December 11, 2006 (the effective date of this AD), whichever occurs first. Repetitively inspect thereafter at intervals not to exceed 200 hours TIS. Follow the procedures in Raytheon Mandatory Service Bulletin 57–3815, dated Issued: October, 2006. (2) If cracks are found repair all cracks by obtaining and incorporating an FAA-approved repair scheme from RAC. Before further flight after any inspection required by paragraph (e)(1) of this AD where cracks are found. Contact RAC at Post Office Box 85, Wichita, Kansas 67201–0085; phone: 316–676– 8366; fax: (316) 676–8745; e-mail: tom_peay@rac.ray.com. (3) Report the inspection results to Raytheon Aircraft Company using the instructions and forms in the service bulletin. Complete all sections of the required forms. Reporting requirements have been approved by the Office of Management and Budget (OMB) and assigned OMB control number 2120–0056. Report the initial inspection within 10 days after the inspection or 10 days after the effective date of this AD, whichever occurs later. Report the repetitive inspections within 30 days after the inspection. Follow the procedures in Raytheon Mandatory Service Bulletin 57–3815, dated Issued: October, 2006. Alternative Methods of Compliance (AMOCs) mstockstill on PROD1PC61 with RULES Actions 2006, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Raytheon Aircraft Company (RAC), Post Office Box 85, Wichita, Kansas 67201–0085, Phone 1–800–429–5372 or 1– 316–676–2000, Fax: 1–316–676–8745. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. (f) The Manager, Wichita Aircraft Certification Office, FAA, ATTN: Steven E. Potter, FAA, 1801 Airport Road, Wichita, Kansas 67209; telephone: (316) 946–4124; fax: (316) 946–4107, has the authority to approve AMOCs for this AD, if requested using the procedures in 14 CFR 39. Material Incorporated by Reference (g) You must use Raytheon Mandatory Service Bulletin 57–3815, Issued: October, VerDate Aug<31>2005 12:11 Dec 01, 2006 Jkt 211001 PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 E:\FR\FM\04DER1.SGM 04DER1 70300 Federal Register / Vol. 71, No. 232 / Monday, December 4, 2006 / Rules and Regulations Issued in Kansas City, Missouri, on November 24, 2006. Sandra J. Campbell, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–20326 Filed 12–1–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25810; Directorate Identifier 2006–CE–49–AD; Amendment 39– 14838; AD 2006–24–09] RIN 2120–AA64 Airworthiness Directives; PZL-Bielsko Model SZD–50–3 ‘‘Puchacz’’ Gliders Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: mstockstill on PROD1PC61 with RULES VerDate Aug<31>2005 12:11 Dec 01, 2006 Jkt 211001 Streamlined Issuance of AD The FAA is implementing a new process for streamlining the issuance of ADs related to MCAI. The streamlined process will allow us to adopt MCAI safety requirements in a more efficient manner and will reduce safety risks to the public. This process continues to follow all FAA AD issuance processes to meet legal, economic, Administrative Procedure Act, and Federal Register requirements. We also continue to meet our technical decision-making responsibilities to identify and correct unsafe conditions on U.S.-certificated products. This AD references the MCAI and related service information that we considered in forming the engineering basis to correct the unsafe condition. The AD contains text copied from the MCAI and for this reason might not follow our plain language principles. Discussion We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a discrepancy between the design documentation and the Technical Service Manual. In 1981, a castellated nut with cotter pin was introduced to secure the rudder, replacing the self-locking nut through PZL-Bielsko Bulletin No. BE–06/50–3/ 81. This change has not been introduced to the Technical Service Manual and use of a self-locking nut, in accordance with the Manual, is still possible. We are issuing this AD to require actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective January 8, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 8, 2007. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, Room PL–401, Washington, DC. FOR FURTHER INFORMATION CONTACT: Gregory Davison, Glider Program Manager, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4130; fax: (816) 329–4090. SUMMARY: SUPPLEMENTARY INFORMATION: We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on September 27, 2006 (71 FR 56416). That NPRM proposed to correct an unsafe condition for the specific products. The MCAI states that a discrepancy between the design documentation and the Technical Service Manual has been identified. In 1981, a castellated nut with cotter pin was introduced to secure the rudder, replacing the self-locking nut through PZL-Bielsko Bulletin No BE–06/50–3/ 81. This change has not been introduced to the Technical Service Manual and use of a self-locking nut, in accordance with the Manual, is still possible. This was probably the reason of rudder disconnection during flight which occurred recently. If not corrected, loss of the nut could result and allow the rudder to slip out of its hinges, separate from the glider, and lead to loss of control. This AD requires you to inspect and, if necessary, replace the Rudder Attachment parts in accordance with the instruction contained in the Allstar PZL Glider Sp. z o.o. Mandatory Bulletin No. BE–058/SZD–50–3/2006 ‘‘PUCHACZ’’, dated August 10, 2006. Concurrently, changes in the Technical Service Manual must be introduced in accordance with the referenced bulletin. Comments We gave the public the opportunity to participate in developing this AD. We have considered the comments received. PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 Jack Buster with the Modification and Replacement Parts Association (MARPA) provides comments to the MCAI AD process pertaining to how the FAA addresses publishing manufacturer service information as part of a proposed AD action. Mr. Buster states that the rule, as proposed, attempts to require compliance with a public law by reference to a private writing (as referenced in paragraph (e) of the proposed AD). Mr. Buster would like the FAA to incorporate by reference (IBR) the Allstar PZL Glider Sp. z o.o. Mandatory Bulletin. We agree with Mr. Buster. However, we do not IBR any document in a proposed AD action, instead we IBR the document in the final rule. Since we are issuing the proposal as a final rule AD action, Allstar PZL Glider Sp. z o.o. Mandatory Bulletin No. BE–058/SZD– 50–3/2006 ‘‘PUCHACZ’’, dated August 10, 2006, is incorporated by reference. Mr. Buster requests that IBR documents be made available to the public by publication in the Federal Register or in the Docket Management System (DMS). We are currently reviewing issues surrounding the posting of service bulletins in the Department of Transportation’s DMS as part of the AD docket. Once we have thoroughly examined all aspects of this issue and have made a final determination, we will consider whether our current practice needs to be revised. Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD as proposed. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable in a U.S. court of law. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are described in a separate paragraph of the AD. These requirements, if any, take precedence over the actions copied from the MCAI. E:\FR\FM\04DER1.SGM 04DER1

Agencies

[Federal Register Volume 71, Number 232 (Monday, December 4, 2006)]
[Rules and Regulations]
[Pages 70297-70300]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-20326]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26258; Directorate Identifier 2006-CE-67-AD; 
Amendment 39-14840; AD 2006-24-11]
RIN 2120-AA64


Airworthiness Directives; Raytheon Aircraft Company Models 1900, 
1900C, and 1900D Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

[[Page 70298]]

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Raytheon Aircraft Company (RAC) Models 1900, 1900C, and 1900D 
airplanes. This AD requires you to repetitively inspect the forward, 
vertical, and aft flanges of both the left and right wing rear spar 
lower caps for cracks, repair any cracks found, and report the 
inspection results to RAC. This AD results from additional fatigue 
cracks found in this area since inspections were performed to comply 
with Emergency AD 2006-18-51, which required immediate visual 
inspections of this area. We are issuing this AD for the purpose of 
performing a more rigorous inspection requiring cleaning and paint 
stripping of this section of the wing rear spar to detect and correct 
cracking in the wing spar lower caps of the affected airplanes before 
the cracks lead to failure. These wing rear spar cracks may result in 
wing failure which could result in the wing separating from the 
airplane with consequent loss of control.

DATES: This AD becomes effective on December 11, 2006.
    As of December 11, 2006, the Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulation.
    We must receive any comments on this AD by February 2, 2007.

ADDRESSES: Use one of the following addresses to comment on this AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking web site: Go to http://
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.
    To get the service information identified in this AD, contact 
Raytheon Aircraft Company (RAC), Post Office Box 85, Wichita, Kansas 
67201-0085, Phone 1-800-429-5372 or 1-316-676-2000, Fax: 1-316-676-
8745.
    To view the comments to this AD, go to http://dms.dot.gov. The 
docket number is FAA-2006-26258; Directorate Identifier 2006-CE-67-AD.

FOR FURTHER INFORMATION CONTACT: Steven E. Potter, FAA, 1801 Airport 
Road, Wichita, Kansas 67209; telephone: (316) 946-4124; fax: (316) 946-
4107.

SUPPLEMENTARY INFORMATION:

Discussion

    Due to significant cracks found in the wing rear spar of RAC Model 
1900D airplanes, we issued Emergency AD 2006-18-51 on August 31, 2006. 
AD 2006-18-51 required an immediate visual inspection of both the left 
and right wing rear spars near the outboard edge of the engine nacelle. 
This AD was then published in the Federal Register as Amendment 39-
14757 (71 FR 52983, September 8, 2006).
    Additional fatigue cracks in the affected area of the wing rear 
spar have been found since the AD 2006-18-51 inspections were 
performed. One of the airplanes had accumulated 168 hours time-in-
service (TIS) since the visual inspections required by AD 2006-18-51 
were done.
    The FAA has determined a more rigorous and detailed inspection is 
necessary to find such fatigue cracks.
    Cracking in the wing rear spar lower caps and adjacent structure, 
if not corrected, could result in wing failure. Such a wing failure 
could result in the wing separating from the airplane with consequent 
loss of control.

Relevant Service Information

    We reviewed Raytheon Aircraft Company Service Bulletin No. 57-3815, 
Issued: October, 2006. The service information describes procedures for 
the left and right rear wing spar lower cap inspection.

FAA's Determination and Requirements of This AD

    We are issuing this AD because we have evaluated all known and 
available information and determined the unsafe condition described 
previously is likely to exist or develop on other products of the same 
type design. This AD requires a rigorous and detailed inspection of the 
wing rear spar lower caps to find the fatigue cracks. The preparation 
and procedural requirements for these inspections are included in RAC 
Mandatory Service Bulletin 57-3815.
    RAC is developing a modification that, if approved by the FAA, 
would terminate the repetitive inspection requirement of this AD. The 
FAA may take future rulemaking action on this subject.

FAA's Determination of the Effective Date

    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we determined that notice and opportunity for 
public comment before issuing this AD are impracticable, and that good 
cause exists for making this amendment effective in fewer than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and an opportunity for 
public comment. We invite you to send any written relevant data, views, 
or arguments regarding this AD. Send your comments to an address listed 
under the ADDRESSES section. Include the docket number ``FAA-2006-
26258; Directorate Identifier 2006-CE-67-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD. We will consider 
all comments received by the closing date and may amend the AD in light 
of those comments.
    We will post all comments we receive, without change, to http://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact we 
receive concerning this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.

[[Page 70299]]

    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.

Examining the AD Docket

    You may examine the AD docket that contains the AD, the regulatory 
evaluation, any comments received, and other information on the 
Internet at http://dms.dot.gov; or in person at the Docket Management 
Facility between 9 a.m. and 5 p.m., Monday through Friday, except 
Federal holidays. The 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
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

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. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2006-24-11 Raytheon Aircraft Company (RAC): Amendment 39-14840; 
Docket No. FAA-2006-26258; Directorate Identifier 2006-CE-67-AD.

Effective Date

    (a) This AD becomes effective on December 11, 2006.

Affected ADs

    (b) AD 2006-18-51, Amendment 39-14757 (71 FR 52983, September 8, 
2006), relates to the subject of this AD. However, this AD does not 
supersede or revise that AD. Both ADs are necessary to address the 
unsafe condition.

Applicability

    (c) This AD applies to the following airplane models and serial 
numbers that are certificated in any category:

------------------------------------------------------------------------
                  Models                           Serial numbers
------------------------------------------------------------------------
(1) 1900.................................  UA-3.
(2) 1900C (C-12J)........................  UB-1 through UB-74, UC-1
                                            through UC-174, and UD-1
                                            through UD-6.
(3) 1900D................................  UE-1 through UE-439.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD is the result of additional fatigue cracks found in 
the wing rear spar lower caps on a Raytheon Model 1900 airplane 
shortly after complying with AD 2006-18-51. We are issuing this AD 
to require a more rigorous and detailed inspection to find the 
fatigue cracks which are the unsafe condition. Failure to detect 
cracking in the wing rear spar lower caps of the affected airplanes 
could result in a wing failure. Such a wing failure could result in 
the wing separating from the airplane with consequent loss of 
control.

Compliance

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

------------------------------------------------------------------------
             Actions                  Compliance          Procedures
------------------------------------------------------------------------
(1) Repetitively inspect both     Initially inspect   Follow the
 the left and right wing rear      within 100 hours    procedures in
 spar lower caps for cracks and    time-in-service     Raytheon
 other damage such as loose or     (TIS) or 30 days    Mandatory Service
 missing fasteners.                after December      Bulletin 57-3815,
                                   11, 2006 (the       dated Issued:
                                   effective date of   October, 2006.
                                   this AD),
                                   whichever occurs
                                   first.
                                   Repetitively
                                   inspect
                                   thereafter at
                                   intervals not to
                                   exceed 200 hours
                                   TIS.
------------------------------------------------------------------------
(2) If cracks are found repair    Before further      Contact RAC at
 all cracks by obtaining and       flight after any    Post Office Box
 incorporating an FAA-approved     inspection          85, Wichita,
 repair scheme from RAC.           required by         Kansas 67201-
                                   paragraph (e)(1)    0085; phone: 316-
                                   of this AD where    676-8366; fax:
                                   cracks are found.   (316) 676-8745; e-
                                                       mail: tom_
peay@rac.ray.com.
------------------------------------------------------------------------
(3) Report the inspection         Report the initial  Follow the
 results to Raytheon Aircraft      inspection within   procedures in
 Company using the instructions    10 days after the   Raytheon
 and forms in the service          inspection or 10    Mandatory Service
 bulletin. Complete all sections   days after the      Bulletin 57-3815,
 of the required forms.            effective date of   dated Issued:
 Reporting requirements have       this AD,            October, 2006.
 been approved by the Office of    whichever occurs
 Management and Budget (OMB) and   later. Report the
 assigned OMB control number       repetitive
 2120-0056.                        inspections
                                   within 30 days
                                   after the
                                   inspection.
------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (f) The Manager, Wichita Aircraft Certification Office, FAA, 
ATTN: Steven E. Potter, FAA, 1801 Airport Road, Wichita, Kansas 
67209; telephone: (316) 946-4124; fax: (316) 946-4107, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures in 14 CFR 39.

Material Incorporated by Reference

    (g) You must use Raytheon Mandatory Service Bulletin 57-3815, 
Issued: October, 2006, to do the actions required by this AD, unless 
the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Raytheon Aircraft Company (RAC), Post Office Box 85, Wichita, Kansas 
67201-0085, Phone 1-800-429-5372 or 1-316-676-2000, Fax: 1-316-676-
8745.
    (3) You may review copies at the FAA, Central Region, Office of 
the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at 
the National Archives and Records Administration (NARA). For 
information on the availability of this material at NARA, call 202-
741-6030, or go to: http://www.archives.gov/federal_register/code_
of_federal_regulations/ibr_locations.html.


[[Page 70300]]


    Issued in Kansas City, Missouri, on November 24, 2006.
Sandra J. Campbell,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-20326 Filed 12-1-06; 8:45 am]
BILLING CODE 4910-13-P