Airworthiness Directives; Rockwell International (Aircraft Specification No. A-2-575 previously held by North American and recently purchased by Boeing) Models AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B, AT-6C (SNJ-4), AT-6D (SNJ-5), AT-6F (SNJ-6), BC-1A, SNJ-7, and T-6G Airplanes; and Autair Ltd. (Aircraft Specification No. AR-11 previously held by Noorduyn Aviation Ltd.) Model Harvard (Army AT-16) Airplanes, 35519-35523 [05-12151]

Download as PDF Federal Register / Vol. 70, No. 118 / Tuesday, June 21, 2005 / Rules and Regulations (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. 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. DEPARTMENT OF TRANSPORTATION (f) Within 6 months after the effective date of this AD: Modify the APU exhaust duct in the ECS bay; install new, improved insulation on this APU exhaust duct; and replace the existing drain pipe with a new exhaust drain pipe blank; by doing all of the actions in the Accomplishment Instructions of BAE Systems (Operations) Limited Modification Service Bulletin SB.49–072– 36244A, dated October 11, 2004. Where the Accomplishment Instructions of the service bulletin specify submitting an Advice Note to the manufacturer, this AD does not require that action. Accordingly, under the authority delegated to me by the Administrator, the FAA 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. 2005–13–06 Bae Systems (Operations) Limited (Formerly British Aerospace Regional Aircraft): Amendment 39– 14142. Docket No. FAA–2005–20757; Directorate Identifier 2004–NM–192–AD. Effective Date (a) This AD becomes effective July 26, 2005. Affected ADs (b) None. Applicability (c) This AD applies to BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ airplanes, certificated in any category, on which BAE Systems Modification HCM30373A, or BAE Systems Modification HCM30373A and HCM36166C, are installed. Unsafe Condition (d) This AD was prompted by a determination that the temperature of the skin of the auxiliary power unit (APU) exhaust duct in the environmental control system (ECS) bay is higher than the certificated maximum temperature for this area. We are issuing this AD to prevent the potential for ignition of fuel or hydraulic fluid, which could leak from pipes running through the ECS bay. Ignition of these flammable fluids could result in a fire in the ECS bay. Jkt 205001 [Docket No. FAA–2005–24163; Directorate Identifier 2005–CE–30–AD; Amendment 39– 14144; AD 2005–12–51] RIN 2120–AA64 (g) 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. AGENCY: Alternative Methods of Compliance (AMOCs) (h) British airworthiness directive G–2004– 0031, dated December 22, 2004, also addresses the subject of this AD. (i) You must use BAE Systems (Operations) Limited Modification Service Bulletin SB.49– 072–36244A, dated October 11, 2004, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of the service information, contact British Aerospace Regional Aircraft American Support, 13850 Mclearen Road, Herndon, Virginia 20171. To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC. To review copies of the service information, go to 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 June 9, 2005. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–12004 Filed 6–20–05; 8:45 am] BILLING CODE 4910–13–P 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. 15:18 Jun 20, 2005 14 CFR Part 39 Airworthiness Directives; Rockwell International (Aircraft Specification No. A–2–575 previously held by North American and recently purchased by Boeing) Models AT–6 (SNJ–2), AT–6A (SNJ–3), AT–6B, AT–6C (SNJ–4), AT– 6D (SNJ–5), AT–6F (SNJ–6), BC–1A, SNJ–7, and T–6G Airplanes; and Autair Ltd. (Aircraft Specification No. AR–11 previously held by Noorduyn Aviation Ltd.) Model Harvard (Army AT–16) Airplanes Material Incorporated by Reference [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): VerDate jul<14>2003 Federal Aviation Administration Related Information Adoption of the Amendment § 39.13 Modification 35519 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. SUMMARY: The FAA is adopting a new airworthiness directive (AD) for Rockwell International (Aircraft Specification No. A–2–575 previously held by North American and recently purchased by Boeing) Models AT–6 (SNJ–2), AT–6A (SNJ–3), AT–6B, AT– 6C (SNJ–4), AT–6D (SNJ–5), AT–6F (SNJ–6), BC–1A, SNJ–7, and T–6G airplanes; and Autair Ltd. (Aircraft Specification No. AR–11 previously held by Noorduyn Aviation Ltd.) Model Harvard (Army AT–16) airplanes. This AD contains the same information as emergency AD 2005–12–51 and publishes the action in the Federal Register. It requires immediate and repetitive inspections of the inboard and outboard, upper and lower wing attach angles (except for the nose angles) of both wings for fatigue cracks; and, if any crack is found, replacement of the cracked angle with a new angle. This AD is the result of a report of a Rockwell International Model SNJ–6 (AT–6F) airplane crash that occurred on May 9, 2005, resulting in two fatalities. We are issuing this AD to detect and correct any fatigue crack in the inboard and outboard, upper and lower wing attach angles (except for the nose angles) of either wing, which could result in failure of the wing. This failure could lead to loss of control of the aircraft. DATES: This AD becomes effective on June 23, 2005, to all affected persons who did not receive emergency AD 2005–12–51, issued June 8, 2005. Emergency AD 2005–12–51 contained the requirements of this amendment and E:\FR\FM\21JNR1.SGM 21JNR1 35520 Federal Register / Vol. 70, No. 118 / Tuesday, June 21, 2005 / Rules and Regulations became effective immediately upon receipt. We must receive any comments on this AD by August 15, 2005. ADDRESSES: Use one of the following to submit comments 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– 001. • Fax: 1–202–493–2251. • 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. • The type certificate holders have not issued any service information that addresses this safety issue. To view the comments to this AD, go to http://dms.dot.gov. The docket number is FAA–2005–24163; Directorate Identifier 2005–CE–30–AD. FOR FURTHER INFORMATION CONTACT: Fred Guerin, Aerospace Engineer, FAA, Los Angeles ACO, 3960 Paramount Blvd., Lakewood, CA 90712; telephone: (562) 627–5232; facsimile: (562) 627–5210; email: fred.guerin@faa.gov. SUPPLEMENTARY INFORMATION: Discussion What events caused previous FAA AD action? The FAA has received a report of a Rockwell International Model SNJ– 6 (AT–6F) airplane crash that occurred on May 9, 2005, resulting in two fatalities. The investigation revealed a large fatigue crack in the failed lower inboard wing attach angle. The aircraft was used for hire in aerobatic training. On June 8, 2005, we issued emergency AD 2005–12–51 to require immediate and repetitive inspections of the inboard and outboard, upper and lower wing attach angles (except for the nose angles) of both wings for fatigue cracks; and, if any crack is found, replacement of the cracked angle with a new angle. Why is it important to publish this AD? The FAA found that immediate corrective action was required, that notice and opportunity for prior public comment were impracticable and contrary to the public interest, and that good cause existed to make the AD effective immediately by individual letters issued on June 8, 2005, to all known U.S. operators of Rockwell VerDate jul<14>2003 15:18 Jun 20, 2005 Jkt 205001 International (Aircraft Specification No. A–2–575 previously held by North American and recently purchased by Boeing) Models AT–6 (SNJ–2), AT–6A (SNJ–3), AT–6B, AT–6C (SNJ–4), AT–6D (SNJ–5), AT–6F (SNJ–6), BC–1A, SNJ–7, and T–6G airplanes; and Autair Ltd. (Aircraft Specification No. AR–11 previously held by Noorduyn Aviation Ltd.) Model Harvard (Army AT–16) airplanes. These conditions still exist, and the AD is published in the Federal Register as an amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 39.13) to make it effective to all persons. Will FAA take future rulemaking action on this subject? The National Transportation Safety Board (NTSB) is still investigating the accident. When all information from the investigation becomes available, FAA may take additional AD action to address continued operational safety of the affected airplanes. This could include, but is not limited to, inspections, modifications, and/or replacement of critical components. Comments Invited Will I have the opportunity to comment before you issue the rule? This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–24163; Directorate Identifier 2005–CE–30–AD’’ in the subject line of your comments. If you want us to acknowledge receipt of your mailed comments, send us a self-addressed, stamped postcard with the docket number written on it; we will datestamp your postcard and mail it back to you. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify it. If a person contacts us through a nonwritten communication, and that contact relates to a substantive part of this AD, we will summarize the contact and place the summary in the docket. We will consider all comments received by the closing date and may amend the AD in light of those comments. 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 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 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–2005–24163; Directorate Identifier 2005–CE–30–AD’’ in your request. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I E:\FR\FM\21JNR1.SGM 21JNR1 Federal Register / Vol. 70, No. 118 / Tuesday, June 21, 2005 / Rules and Regulations Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding a new AD to read as follows: I 2005–12–51 Rockwell International (Aircraft Specification No. A–2–575 previously held by North American and recently purchased by Boeing) and Autair Ltd. (Aircraft Specification No. AR–11 previously held by Noorduyn Aviation Ltd.): Amendment 39–14144; Docket No. FAA–2005–24163; Directorate Identifier 2005–CE–30–AD. When Does This AD Become Effective? (a) This AD becomes effective on June 23, 2005, to all affected persons who did not receive emergency AD 2005–12–51, issued June 8, 2005. Emergency AD 2005–12–51 contained the requirements of this amendment and became effective immediately upon receipt. Are Any Other ADs Affected By This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects Models AT–6 (SNJ–2), AT–6A (SNJ–3), AT–6B, AT–6C (SNJ–4), AT– 6D (SNJ–5), AT–6F (SNJ–6), BC–1A, Harvard (Army AT–16), SNJ–7, and T–6G airplanes, 35521 all serial numbers, that are certificated in any category. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of a report of a Rockwell International Model SNJ–6 (AT–6F) airplane crash that occurred on May 9, 2005, resulting in two fatalities. We are issuing this AD to detect and correct cracking in the wing spars before the cracks grow to failure. Such a wing failure could result in the wing separating from the airplane with consequent loss of control of the airplane. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Actions Compliance Procedures (1) Perform a fluorescent penetrant inspection of all inboard and outboard, upper and lower wing attach angles (except for the nose angles) of both wings for cracks. Replace the angles as necessary. (i) Initially inspect before further flight after June 23, 2005 (the effective date of this AD), unless previously done within the last 10 hours time-in-service (TIS), except for those who received emergency AD 2005– 12–51, issued June 8, 2005. Emergency AD 2005–12–51 contained the requirements of this amendment and became effective immediately upon receipt. (ii) Repetitively inspect thereafter every 200 hours TIS. (iii) Replace angles as necessary prior to further flight after the inspection where cracks are found. Follow the Appendix to this AD. (2) For all airplanes: Report to FAA the results of the initial inspection required by paragraph (e)(1) of this AD even if no damage is found and even if the inspection was previously done. The Office of Management and Budget (OMB) approved the information collection requirements contained in this regulation under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 and those following sections) and assigned OMB Control Number 2120–0056. Within 7 days after the inspection required by paragraph (e)(1) of this AD or within 7 days after June 23, 2005 (the effective date of this AD), except that this action was already required upon receipt for those who received emergency AD 2005–12– 51.Therefore, those who sent in a report through emergency AD 2005–12–51 do not have to resend that initial report. Send the form (Figure 1 of this AD) to FAA, Los Angeles ACO, 3960 Paramount Blvd., Lakewood, CA 90712; facsimile: (562) 627– 5210. E-mail: fred.guerin@faa.gov. (3) You may operate the airplane to return/position the airplane to a home base, hangar, maintenance facility, etc., for the purpose of doing the inspection required by this AD provided you follow the limitations in paragraph (f) of this AD. You may operate the airplane up to 10 hours TIS provided the flight(s) occur(s) no later than 30 days after June 8, 2005. This is a one-time provision. Not Applicable. (4) Special flight permits are allowed for this AD. See paragraph (f) of this AD for restrictions. Use the procedures in 14 CFR part 39 and the restrictions in paragraph (f) of this AD. Not Applicable. BILLING CODE 4910–13–P VerDate jul<14>2003 15:18 Jun 20, 2005 Jkt 205001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\21JNR1.SGM 21JNR1 35522 Federal Register / Vol. 70, No. 118 / Tuesday, June 21, 2005 / Rules and Regulations VerDate jul<14>2003 15:18 Jun 20, 2005 Jkt 205001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\21JNR1.SGM 21JNR1 ER21JN05.004</GPH> BILLING CODE 4910–13–C Federal Register / Vol. 70, No. 118 / Tuesday, June 21, 2005 / Rules and Regulations What Are the Flight Restrictions Specified in Paragraphs (e)(3) and (e)(4) of This AD? (f) During the time allowed before compliance with the initial inspection required by paragraph (e)(1) of this AD, or for any approved special flight permit, you must adhere to the following limitations: (1) Acrobatic maneuvers are prohibited. (2) Flight into known or forecast moderate or severe turbulence is prohibited. (3) Day visual flight rules (VFR) operation only. (4) Single pilot operation only (Passengers prohibited). May I Request an Alternative Method of Compliance? (g) 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, Los Angeles Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance or for further information about this AD, contact Fred Guerin, Aerospace Engineer, FAA, Los Angeles ACO, 3960 Paramount Blvd., Lakewood, CA 90712; telephone: (562) 627–5232; facsimile: (562) 627–5210; e-mail: fred.guerin@faa.gov. Where Do I View the AD Docket? (h) 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–2005–24163. Issued in Kansas City, Missouri, on June 14, 2005. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. Appendix to AD 2005–12–51 Wing Attachment Angle Inspection for: Models AT–6 (SNJ–2), AT–6A (SNJ–3), AT– 6B, AT–6C (SNJ–4), AT–6D (SNJ–5), AT–6F (SNJ–6), BC–1A, Harvard (Army AT–16), SNJ–7, and T–6G Airplanes Procedures: (1) Remove all outboard wing attach angle covers. (2) Support outboard wing on appropriate stands to relieve the weight on the wing attach bolts. (3) On the upper wing attach angles, except for the forward and aft five bolts on the angle, remove all of the through bolts that attach the outboard wing (Do not remove bolts in the nose angle). (4) Remove all paint down to the bare metal using solvent on outer surface of affected angles. Do not sand or use media blasting or use any method that would cover up or contaminate a crack. This means not using Scotchbrite or a similar abrasive, which can contaminate a crack for penetrant inspection. (5) Use the penetrant manufacturer’s cleaner, acetone, or 90-percent or more VerDate jul<14>2003 15:18 Jun 20, 2005 Jkt 205001 alcohol solution to do a final surface cleaning preparation step before the fluorescent penetrant inspection. (6) Perform an inspection of the outboard and inboard wing attach angles using a high sensitivity fluorescent dye penetrant inspection procedure per the penetrant manufacturer’s instructions. Pay particular attention to cracks that may be present in the edge of the spot faces closest to the radius of the angle. Also pay attention to any small cracks that may be emanating from the edge of the fasteners in any row of installed fasteners. Choose a commercially available fluorescent inspection method that requires the use of an ultraviolet (black light) in a darkened environment. Do not use dye penetrant, which is read under normal lighting conditions. (7) Check the wing attachment angle for condition and for security of rivets and bolts. (8) If no cracks or major defects are found, replace nuts and bolts following directions in paragraphs (11) and (12) of this appendix of this AD, clean angle, and apply a corrosion protectant coating paint (Alodine alone is not acceptable). (9) On the upper wing, remove the forward and aft five bolts that were previously left in place, and inspect the remaining uninspected portion of the angles following the above procedure. (10) On the lower wings, repeat the inspection on the bottom two attach angles in the same sequence as on the top angles. (11) When replacing bolts in angles, use only nuts, bolts, and torque values as specified in ‘‘Erection and Maintenance No. AN01–60FFA–2’’ or ‘‘Erection and Maintenance No. AN01–60F–2’’ as applicable to the aircraft model. Bolts may be reused if upon inspection they are found to be in airworthy condition. Nuts may be reused as long as the nylon-locking feature is functional, and they cannot be turned onto the bolt with fingers. Torque values for 1⁄4inch bolts are 60–65 inch/lb, and for 5⁄16-inch bolts are 100–105 inch/lb. These torque values supersede those in the manuals. (12) To assure that the nuts do not contact the shoulder of the wing attach bolts and cause an under torque condition, assure that no more than two threads are protruding from nut after torquing. If more than two threads are protruding, replace with a bolt of the correct length. (13) If any cracks are found, replace the angle with a new part. Send all cracked angles to Fred Guerin, Aerospace Engineer, FAA, Los Angeles ACO, 3960 Paramount Blvd., Lakewood, CA 90712. [FR Doc. 05–12151 Filed 6–20–05; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 35523 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21586; Directorate Identifier 2005–NE–16–AD; Amendment 39– 14148; AD 2005–13–11] RIN 2120–AA64 Airworthiness Directives; General Electric Company CT64–820–4 Turboprop Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CT64–820–4 turboprop engines with stage 1 turbine disk and shaft, part number (P/N) 6004T47P03 or 4921T10P02 installed. This AD requires removing from service these stage 1 turbine disk and shafts at reduced compliance times. This AD results from the discovery by the manufacturer of low-cycle-fatigue (LCF) cracks found in stage 1 turbine disk and shafts, P/Ns 6004T47P03 and 4921T10P02. We are issuing this AD to prevent uncontained failure of the stage 1 turbine disk and shaft, resulting in damage to the airplane. DATES: This AD becomes effective July 6, 2005. We must receive any comments on this AD by August 22, 2005. 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. Contact GE Aircraft Engines Customer Support Center, M/D 285, 1 Neumann Way, Evendale, OH 45215, telephone (513) 552–3272; fax (513) 552–3329; email address: GEAE.csc@ae.ge.com, for the service information identified in this AD. E:\FR\FM\21JNR1.SGM 21JNR1

Agencies

[Federal Register Volume 70, Number 118 (Tuesday, June 21, 2005)]
[Rules and Regulations]
[Pages 35519-35523]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-12151]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-24163; Directorate Identifier 2005-CE-30-AD; 
Amendment 39-14144; AD 2005-12-51]
RIN 2120-AA64


Airworthiness Directives; Rockwell International (Aircraft 
Specification No. A-2-575 previously held by North American and 
recently purchased by Boeing) Models AT-6 (SNJ-2), AT-6A (SNJ-3), AT-
6B, AT-6C (SNJ-4), AT-6D (SNJ-5), AT-6F (SNJ-6), BC-1A, SNJ-7, and T-6G 
Airplanes; and Autair Ltd. (Aircraft Specification No. AR-11 previously 
held by Noorduyn Aviation Ltd.) Model Harvard (Army AT-16) Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Rockwell International (Aircraft Specification No. A-2-575 previously 
held by North American and recently purchased by Boeing) Models AT-6 
(SNJ-2), AT-6A (SNJ-3), AT-6B, AT-6C (SNJ-4), AT-6D (SNJ-5), AT-6F 
(SNJ-6), BC-1A, SNJ-7, and T-6G airplanes; and Autair Ltd. (Aircraft 
Specification No. AR-11 previously held by Noorduyn Aviation Ltd.) 
Model Harvard (Army AT-16) airplanes. This AD contains the same 
information as emergency AD 2005-12-51 and publishes the action in the 
Federal Register. It requires immediate and repetitive inspections of 
the inboard and outboard, upper and lower wing attach angles (except 
for the nose angles) of both wings for fatigue cracks; and, if any 
crack is found, replacement of the cracked angle with a new angle. This 
AD is the result of a report of a Rockwell International Model SNJ-6 
(AT-6F) airplane crash that occurred on May 9, 2005, resulting in two 
fatalities. We are issuing this AD to detect and correct any fatigue 
crack in the inboard and outboard, upper and lower wing attach angles 
(except for the nose angles) of either wing, which could result in 
failure of the wing. This failure could lead to loss of control of the 
aircraft.

DATES: This AD becomes effective on June 23, 2005, to all affected 
persons who did not receive emergency AD 2005-12-51, issued June 8, 
2005. Emergency AD 2005-12-51 contained the requirements of this 
amendment and

[[Page 35520]]

became effective immediately upon receipt.
    We must receive any comments on this AD by August 15, 2005.

ADDRESSES: Use one of the following to submit comments 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 20590-001.
     Fax: 1-202-493-2251.
     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.
     The type certificate holders have not issued any service 
information that addresses this safety issue.
    To view the comments to this AD, go to http://dms.dot.gov. The 
docket number is FAA-2005-24163; Directorate Identifier 2005-CE-30-AD.

FOR FURTHER INFORMATION CONTACT: Fred Guerin, Aerospace Engineer, FAA, 
Los Angeles ACO, 3960 Paramount Blvd., Lakewood, CA 90712; telephone: 
(562) 627-5232; facsimile: (562) 627-5210; e-mail: fred.guerin@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    What events caused previous FAA AD action? The FAA has received a 
report of a Rockwell International Model SNJ-6 (AT-6F) airplane crash 
that occurred on May 9, 2005, resulting in two fatalities. The 
investigation revealed a large fatigue crack in the failed lower 
inboard wing attach angle. The aircraft was used for hire in aerobatic 
training.
    On June 8, 2005, we issued emergency AD 2005-12-51 to require 
immediate and repetitive inspections of the inboard and outboard, upper 
and lower wing attach angles (except for the nose angles) of both wings 
for fatigue cracks; and, if any crack is found, replacement of the 
cracked angle with a new angle.
    Why is it important to publish this AD? The FAA found that 
immediate corrective action was required, that notice and opportunity 
for prior public comment were impracticable and contrary to the public 
interest, and that good cause existed to make the AD effective 
immediately by individual letters issued on June 8, 2005, to all known 
U.S. operators of Rockwell International (Aircraft Specification No. A-
2-575 previously held by North American and recently purchased by 
Boeing) Models AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B, AT-6C (SNJ-4), AT-6D 
(SNJ-5), AT-6F (SNJ-6), BC-1A, SNJ-7, and T-6G airplanes; and Autair 
Ltd. (Aircraft Specification No. AR-11 previously held by Noorduyn 
Aviation Ltd.) Model Harvard (Army AT-16) airplanes. These conditions 
still exist, and the AD is published in the Federal Register as an 
amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 
39.13) to make it effective to all persons.
    Will FAA take future rulemaking action on this subject? The 
National Transportation Safety Board (NTSB) is still investigating the 
accident. When all information from the investigation becomes 
available, FAA may take additional AD action to address continued 
operational safety of the affected airplanes. This could include, but 
is not limited to, inspections, modifications, and/or replacement of 
critical components.

Comments Invited

    Will I have the opportunity to comment before you issue the rule? 
This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to submit any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-24163; 
Directorate Identifier 2005-CE-30-AD'' in the subject line of your 
comments. If you want us to acknowledge receipt of your mailed 
comments, send us a self-addressed, stamped postcard with the docket 
number written on it; we will date-stamp your postcard and mail it back 
to you. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify it. If a person contacts us through a 
nonwritten communication, and that contact relates to a substantive 
part of this AD, we will summarize the contact and place the summary in 
the docket. We will consider all comments received by the closing date 
and may amend the AD in light of those comments.

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-2005-24163; Directorate Identifier 2005-CE-30-AD'' in your 
request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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:


[[Page 35521]]


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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding a new AD to read as follows:

2005-12-51 Rockwell International (Aircraft Specification No. A-2-
575 previously held by North American and recently purchased by 
Boeing) and Autair Ltd. (Aircraft Specification No. AR-11 previously 
held by Noorduyn Aviation Ltd.): Amendment 39-14144; Docket No. FAA-
2005-24163; Directorate Identifier 2005-CE-30-AD.

When Does This AD Become Effective?

    (a) This AD becomes effective on June 23, 2005, to all affected 
persons who did not receive emergency AD 2005-12-51, issued June 8, 
2005. Emergency AD 2005-12-51 contained the requirements of this 
amendment and became effective immediately upon receipt.

Are Any Other ADs Affected By This Action?

    (b) None.

What Airplanes Are Affected by This AD?

    (c) This AD affects Models AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B, 
AT-6C (SNJ-4), AT-6D (SNJ-5), AT-6F (SNJ-6), BC-1A, Harvard (Army 
AT-16), SNJ-7, and T-6G airplanes, all serial numbers, that are 
certificated in any category.

What Is the Unsafe Condition Presented in This AD?

    (d) This AD is the result of a report of a Rockwell 
International Model SNJ-6 (AT-6F) airplane crash that occurred on 
May 9, 2005, resulting in two fatalities. We are issuing this AD to 
detect and correct cracking in the wing spars before the cracks grow 
to failure. Such a wing failure could result in the wing separating 
from the airplane with consequent loss of control of the airplane.

What Must I Do To Address This Problem?

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

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Perform a fluorescent     (i) Initially         Follow the Appendix
 penetrant inspection of all   inspect before        to this AD.
 inboard and outboard, upper   further flight
 and lower wing attach         after June 23, 2005
 angles (except for the nose   (the effective date
 angles) ofboth wings for      of this AD), unless
 cracks. Replace the angles    previously done
 as necessary.                 within the last 10
                               hours time-in-
                               service (TIS),
                               except for those
                               who received
                               emergency AD 2005-
                               12-51, issued June
                               8, 2005. Emergency
                               AD 2005-12-51
                               contained the
                               requirements of
                               this amendment and
                               became effective
                               immediately upon
                               receipt.
                              (ii) Repetitively
                               inspect thereafter
                               every 200 hours TIS.
                              (iii) Replace angles
                               as necessary prior
                               to further flight
                               after the
                               inspection where
                               cracks are found.
-----------------------------
(2) For all airplanes:        Within 7 days after   Send the form
 Report to FAA the results     the inspection        (Figure 1 of this
 of the initial inspection     required by           AD) to FAA, Los
 required by paragraph         paragraph (e)(1) of   Angeles ACO, 3960
 (e)(1) of this AD even if     this AD or within 7   Paramount Blvd.,
 no damage is found and even   days after June 23,   Lakewood, CA 90712;
 if the inspection was         2005 (the effective   facsimile: (562)
 previously done. The Office   date of this AD),     627-5210. E-mail:
 of Management andBudget       except that this      fred.guerin@faa.gov
 (OMB) approved the            action was already    .
 information collection        required upon
 requirements contained in     receipt for those
 this regulation under the     who received
 provisions of the Paperwork   emergency AD 2005-
 Reduction Act of 1980 (44     12-51.Therefore,
 U.S.C. 3501 and those         those who sent in a
 following sections) and       report through
 assigned OMB Control Number   emergency AD 2005-
 2120-0056.                    12-51 do not have
                               to resend that
                               initial report.
-----------------------------
(3) You may operate the       You may operate the   Not Applicable.
 airplane to return/position   airplane up to 10
 the airplane to a home        hours TIS provided
 base, hangar, maintenance     the flight(s)
 facility, etc., for the       occur(s) no later
 purpose of doing the          than 30 days after
 inspection required by this   June 8, 2005. This
 AD provided you follow the    is a one-time
 limitations in paragraph      provision.
 (f) of this AD.
-----------------------------
(4) Special flight permits    Use the procedures    Not Applicable.
 are allowed for this AD.      in 14 CFR part 39
 See paragraph (f) of this     and the
 AD for restrictions.          restrictions in
                               paragraph (f) of
                               this AD.
------------------------------------------------------------------------

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[GRAPHIC] [TIFF OMITTED] TR21JN05.004

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[[Page 35523]]

What Are the Flight Restrictions Specified in Paragraphs (e)(3) and 
(e)(4) of This AD?

    (f) During the time allowed before compliance with the initial 
inspection required by paragraph (e)(1) of this AD, or for any 
approved special flight permit, you must adhere to the following 
limitations:
    (1) Acrobatic maneuvers are prohibited.
    (2) Flight into known or forecast moderate or severe turbulence 
is prohibited.
    (3) Day visual flight rules (VFR) operation only.
    (4) Single pilot operation only (Passengers prohibited).

May I Request an Alternative Method of Compliance?

    (g) 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, Los Angeles Aircraft 
Certification Office (ACO), FAA. For information on any already 
approved alternative methods of compliance or for further 
information about this AD, contact Fred Guerin, Aerospace Engineer, 
FAA, Los Angeles ACO, 3960 Paramount Blvd., Lakewood, CA 90712; 
telephone: (562) 627-5232; facsimile: (562) 627-5210; e-mail: 
fred.guerin@faa.gov.

Where Do I View the AD Docket?

    (h) 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-2005-24163.

    Issued in Kansas City, Missouri, on June 14, 2005.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.

Appendix to AD 2005-12-51

Wing Attachment Angle Inspection for: Models AT-6 (SNJ-2), AT-6A (SNJ-
3), AT-6B, AT-6C (SNJ-4), AT-6D (SNJ-5), AT-6F (SNJ-6), BC-1A, Harvard 
(Army AT-16), SNJ-7, and T-6G Airplanes

    Procedures:
    (1) Remove all outboard wing attach angle covers.
    (2) Support outboard wing on appropriate stands to relieve the 
weight on the wing attach bolts.
    (3) On the upper wing attach angles, except for the forward and 
aft five bolts on the angle, remove all of the through bolts that 
attach the outboard wing (Do not remove bolts in the nose angle).
    (4) Remove all paint down to the bare metal using solvent on 
outer surface of affected angles. Do not sand or use media blasting 
or use any method that would cover up or contaminate a crack. This 
means not using Scotchbrite or a similar abrasive, which can 
contaminate a crack for penetrant inspection.
    (5) Use the penetrant manufacturer's cleaner, acetone, or 90-
percent or more alcohol solution to do a final surface cleaning 
preparation step before the fluorescent penetrant inspection.
    (6) Perform an inspection of the outboard and inboard wing 
attach angles using a high sensitivity fluorescent dye penetrant 
inspection procedure per the penetrant manufacturer's instructions. 
Pay particular attention to cracks that may be present in the edge 
of the spot faces closest to the radius of the angle. Also pay 
attention to any small cracks that may be emanating from the edge of 
the fasteners in any row of installed fasteners. Choose a 
commercially available fluorescent inspection method that requires 
the use of an ultraviolet (black light) in a darkened environment. 
Do not use dye penetrant, which is read under normal lighting 
conditions.
    (7) Check the wing attachment angle for condition and for 
security of rivets and bolts.
    (8) If no cracks or major defects are found, replace nuts and 
bolts following directions in paragraphs (11) and (12) of this 
appendix of this AD, clean angle, and apply a corrosion protectant 
coating paint (Alodine alone is not acceptable).
    (9) On the upper wing, remove the forward and aft five bolts 
that were previously left in place, and inspect the remaining 
uninspected portion of the angles following the above procedure.
    (10) On the lower wings, repeat the inspection on the bottom two 
attach angles in the same sequence as on the top angles.
    (11) When replacing bolts in angles, use only nuts, bolts, and 
torque values as specified in ``Erection and Maintenance No. AN01-
60FFA-2'' or ``Erection and Maintenance No. AN01-60F-2'' as 
applicable to the aircraft model. Bolts may be reused if upon 
inspection they are found to be in airworthy condition. Nuts may be 
reused as long as the nylon-locking feature is functional, and they 
cannot be turned onto the bolt with fingers. Torque values for \1/
4\-inch bolts are 60-65 inch/lb, and for \5/16\-inch bolts are 100-
105 inch/lb. These torque values supersede those in the manuals.
    (12) To assure that the nuts do not contact the shoulder of the 
wing attach bolts and cause an under torque condition, assure that 
no more than two threads are protruding from nut after torquing. If 
more than two threads are protruding, replace with a bolt of the 
correct length.
    (13) If any cracks are found, replace the angle with a new part. 
Send all cracked angles to Fred Guerin, Aerospace Engineer, FAA, Los 
Angeles ACO, 3960 Paramount Blvd., Lakewood, CA 90712.

[FR Doc. 05-12151 Filed 6-20-05; 8:45 am]
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