Airworthiness Directives; Lockheed Model 382, 382B, 382E, 382F, and 382G Series Airplanes, 23614-23617 [E9-11590]

Download as PDF 23614 Federal Register / Vol. 74, No. 96 / Wednesday, May 20, 2009 / Rules and Regulations Amendment 25–61 (51 FR 26206, July 21, 1986), specifically note that seats were excluded ‘‘because the recentlyadopted standards for flammability of seat cushions will greatly inhibit involvement of the seats.’’ Subsequently, the Final Rule at Amendment 25–83 (60 FR 6615, March 6, 1995) clarified the definition of minimum panel size: ‘‘It is not possible to cite a specific size that will apply in all installations; however, as a general rule, components with exposed-surface areas of one square foot or less may be considered small enough that they do not have to meet the new standards. Components with exposed-surface areas greater than two square feet may be considered large enough that they do have to meet the new standards. Those with exposed-surface areas greater than one square foot, but less than two square feet, must be considered in conjunction with the areas of the cabin in which they are installed before a determination could be made.’’ On October 17, 1997, the FAA issued Policy Memorandum 97–112–39, Guidance for Flammability Testing of Seat/Console Installations, (https:// rgl.faa.gov). That memo was issued when it became clear that seat designs were evolving to include large, nonmetallic panels with surface areas that would impact survivability during a cabin-fire event, comparable to partitions or galleys. The memo noted that large-surface-area panels must comply with heat-release and smokeemission requirements, even if they were attached to a seat. If the FAA had not issued such policy, seat designs could have been viewed as a loophole to the airworthiness standards that would result in an unacceptable decrease in survivability during a cabinfire event. In October 2004, we focused attention on the appropriate flammability standards for passenger seats that incorporated non-traditional, large, nonmetallic panels in lieu of the traditional fabric-covered metal. The Seattle Aircraft Certification Office and Transport Standards Staff reviewed this design and determined that it represented the kind and quantity of material that should be required to pass the heat-release and smoke-emissions requirements. We have determined that special conditions would be issued to apply the standards defined in § 25.853(d) to seats designed with large, non-metallic panels. Applicability As discussed above, these special conditions are applicable to Boeing Model 757 series airplanes. It is not our VerDate Nov<24>2008 14:51 May 19, 2009 Jkt 217001 intent, however, to require seats with large, non-metallic panels to meet § 25.853, Appendix F, parts IV and V, if they are installed in cabins of airplanes that otherwise are not required to meet these standards. Because the heatrelease and smoke-emission testing requirements of § 25.853 per Appendix F, parts IV and V, are not part of the type-certification basis of the Model 757, these special conditions are only applicable if the Model 757 series airplanes are in 14 CFR part 121 operations. Section 121.312 requires compliance with the heat-release and smoke-emission testing requirements of § 25.853, for certain airplanes, irrespective of the type-certification bases of those airplanes. For Model 757 series airplanes, these are the airplanes that would be affected by these special conditions. Should NAT apply at a later date for a supplemental type certificate to modify any other model included on Type Certificate No. A2NM to incorporate the same novel or unusual design feature, the special conditions would apply to that model as well. Conclusion This action affects only certain novel or unusual design features on one model series of airplanes. It is not a rule of general applicability and it affects only the applicant who applied to the FAA for approval of these features on the airplane. Under standard practice, the effective date of final special conditions would be 30 days after the date of publication in the Federal Register; however, as the return-to-service date for the Boeing Model 757 series airplane, modified by NAT, is imminent, the FAA finds that good cause exists to make these special conditions effective upon issuance. List of Subjects in 14 CFR Part 25 metallic panels that may either be a single component or multiple components in a concentrated area in their design. 2. The applicant may designate up to and including 1.5 square feet of nontraditional, non-metallic panel material per seat place that does not have to comply with special condition (1), above. A triple-seat assembly may have a total of 4.5 square feet excluded on any portion of the assembly (e.g., outboard-seat place 1 square foot; middle, 1 square foot; and inboard, 2.5 square feet). 3. Seats do not have to meet the test requirements of Title 14 CFR part 25, Appendix F, parts IV and V, when installed in compartments that are not otherwise required to meet these requirements. Examples include: a. Airplanes with passenger capacities of 19 or less, b. Airplanes that do not have § 25.853, Amendment 25–61 or later, in their certification basis and do not need to comply with the requirements of 14 CFR 121.312, and c. Airplanes exempted from § 25.853, Amendment 25–61 or later. Issued in Renton, Washington, on May 11, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–11723 Filed 5–19–09; 8:45 am] BILLING CODE P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0462; Directorate Identifier 2009–NM–063–AD; Amendment 39–15913; AD 2009–11–03] Aircraft, Aviation safety, Reporting and recordkeeping requirements. RIN 2120–AA64 The authority citation for these special conditions is as follows: Airworthiness Directives; Lockheed Model 382, 382B, 382E, 382F, and 382G Series Airplanes ■ Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. The Special Conditions Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type-certification basis for Boeing Model 757 series airplanes modified by NAT. 1. Except as provided in paragraph 3 of these special conditions, compliance with Title 14 CFR part 25, Appendix F, parts IV and V, heat release and smoke emission, is required for seats that incorporate non-traditional, large, non- ■ PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. SUMMARY: We are adopting a new airworthiness directive (AD) for all Lockheed Model 382, 382B, 382E, 382F, and 382G series airplanes. This AD requires an inspection to identify discrepant barrel nuts in the upper wing joint, engine truss, and rear beam pylon support; and replacement of any discrepant barrel nut with a new barrel nut, if necessary. This AD results from E:\FR\FM\20MYR1.SGM 20MYR1 Federal Register / Vol. 74, No. 96 / Wednesday, May 20, 2009 / Rules and Regulations a report of severe cracking of multiple barrel nuts in the wing station (WS) 220 upper wing joint found during scheduled maintenance. We are issuing this AD to prevent cracking of the barrel nuts in the upper wing joint, engine truss, and rear beam pylon support, which could result in reduced structural integrity of the affected part and consequent detachment of the wing or engine from the airplane. DATES: This AD is effective June 4, 2009. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of June 4, 2009. We must receive comments on this AD by July 20, 2009. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Lockheed Continued Airworthiness Project Office, Attention Airworthiness, 86 South Cobb Drive, Marietta, Georgia 30063–0567; telephone 770–494–5444; fax 770–494– 5445; e-mail ams.portal@lmco.com; Internet https:// www.lockheedmartin.com/ams/tools/ TechPubs.html. SUPPLEMENTARY INFORMATION: Discussion We received a report of severe cracking of multiple barrel nuts in the wing station (WS) 220 upper wing joint found during scheduled maintenance. Deformed thread locking barrel nuts having a certain part number were identified as having greater potential for cracking during routine service. The affected nut might also be installed at the quick engine change (QEC) lower attachment to the truss mount and at the outer wing station (OWS) 330 rear beam pylon attach fitting. This condition, if not corrected, could result in reduced structural integrity of the affected part and consequent detachment of the wing or engine from the airplane. Relevant Service Information We reviewed Lockheed Alert Service Bulletin A382–57–91, Revision 1, dated March 25, 2009. The service bulletin describes procedures for an inspection to identify discrepant barrel nuts (with deformed thread locking, impression stamp ‘‘K,’’ no impression stamp, or cracking) in the upper wing joint, engine truss, and rear beam pylon support; and replacement of any discrepant barrel nut with a new barrel nut, if necessary. Examining the AD Docket FAA’s Determination and Requirements of This AD We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of these same type designs. This AD requires accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between the AD and the Service Information.’’ You may examine the AD docket on the Internet at https:// www.regulations.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 AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Carl Gray, Aerospace Engineer, Airframe Branch, ACE–117A, FAA, Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia 30349; telephone (770) 703–6131; fax (770) 703–6097. Differences Between the AD and the Service Information Although the Accomplishment Instructions of Lockheed Alert Service Bulletin A382–57–91, Revision 1, dated March 25, 2009, specify that operators may contact the manufacturer for disposition of certain repair conditions, this AD would require operators to repair those conditions using a method approved by the FAA. The Accomplishment Instructions of Lockheed Alert Service Bulletin A382– 57–91, Revision 1, dated March 25, 2009, recommend inspecting to identify discrepant barrel nuts before further flight, but we have determined that this compliance time would not give operators enough time to inspect all affected airplanes. In developing an VerDate Nov<24>2008 14:51 May 19, 2009 Jkt 217001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 23615 appropriate compliance time for this AD, we considered the manufacturer’s recommendation, the degree of urgency associated with the subject unsafe condition, the average utilization of the affected fleet, and the time necessary to perform the inspection (1 work-hour). In light of all these factors, we find that a 30-day compliance time represents an appropriate time for affected airplanes to continue to operate without compromising safety. These differences have been coordinated with the manufacturer. FAA’s Justification and Determination of the Effective Date Because of our requirement to promote safe flight of civil aircraft and thus the critical need to prevent cracking of certain barrel nuts which could result in reduced structural integrity of the affected part and consequent detachment of the wing or engine, and the short compliance time involved with this action, this AD must be issued immediately. Because an unsafe condition exists that requires the immediate adoption of this AD, we find that notice and opportunity for prior public comment hereon are impracticable and that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments before it becomes effective. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2009–0462; Directorate Identifier 2009– NM–063–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about 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: E:\FR\FM\20MYR1.SGM 20MYR1 23616 Federal Register / Vol. 74, No. 96 / Wednesday, May 20, 2009 / Rules and Regulations 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 This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. You can find our regulatory evaluation and the estimated costs of compliance in the AD Docket. 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 FAA amends 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2009–11–03 Lockheed: Amendment 39– 15913. Docket No. FAA–2009–0462; Directorate Identifier 2009–NM–063–AD. VerDate Nov<24>2008 14:51 May 19, 2009 Jkt 217001 Effective Date (a) This airworthiness directive (AD) is effective June 4, 2009. Affected ADs (b) None. Applicability (c) This AD applies to all Lockheed Model 382, 382B, 382E, 382F, and 382G series airplanes, certificated in any category. Subject (d) Air Transport Association (ATA) of America Code 57: Wings. Unsafe Condition (e) This AD results from a report of severe cracking of multiple barrel nuts in the wing station (WS) 220 upper wing joint found during scheduled maintenance. We are issuing this AD to prevent cracking of the barrel nuts in the upper wing joint, engine truss, and rear beam pylon support, which could result in reduced structural integrity of the affected part and consequent detachment of the wing or engine from the airplane. Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspection/Replacement if Necessary (g) Within 30 days after the effective date of this AD: Do a general visual inspection to identify discrepant barrel nuts in the upper wing joint, engine truss, and rear beam pylon support, in accordance with the Accomplishment Instructions of Lockheed Alert Service Bulletin A382–57–91, Revision 1, dated March 25, 2009. Except as provided by paragraph (h) of this AD, if any discrepant barrel nut is found, before further flight, replace the barrel nut with a new barrel nut in accordance with the service bulletin. Note 1: For the purposes of this AD, a general visual inspection is: ‘‘A visual 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.’’ Exception to Corrective Action Instructions (h) If any discrepant barrel nut is found during the inspection required by this AD, and Lockheed Alert Service Bulletin A382– 57–91, Revision 1, dated March 25, 2009, specifies contacting Lockheed for appropriate action: Before further flight, replace the discrepant barrel nut using a method approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA. For a repair method to be approved by the Manager, Atlanta ACO, as required by this paragraph, PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 the Manager’s approval letter must specifically refer to this AD. Credit for Actions Done Using Previous Service Information (i) Actions done before the effective date of this AD in accordance with Lockheed Alert Service Bulletin A382–57–91, dated March 6, 2009, are acceptable for compliance with the corresponding requirements of this AD. Reporting Not Required (j) Although Lockheed Alert Service Bulletin A382–57–91, Revision 1, dated March 25, 2009, specifies to submit certain information to the manufacturer, this AD does not include that requirement. Parts Installation (k) As of the time specified in paragraph (k)(1) or (k)(2) of this AD, as applicable, no person may install, on any airplane, a barrel nut in the upper wing joint, engine truss, and rear beam pylon support unless the barrel nut has been modified in accordance with the Accomplishment Instructions of Lockheed Alert Service Bulletin A382–57–91, Revision 1, dated March 25, 2009. (1) For unmarked barrel nuts with a deformed thread locking style: As of 30 days after the effective date of this AD. (2) For all other discrepant barrel nuts: As of the effective date of this AD. Alternative Methods of Compliance (AMOCs) (l)(1) The Manager, Atlanta ACO, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Carl Gray, Aerospace Engineer, Airframe Branch, ACE–117A, Atlanta ACO, FAA, One Crown Center, 1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia 30349; telephone (770) 703– 6131; fax (770) 703–6097. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. Material Incorporated by Reference (m) You must use Lockheed Alert Service Bulletin A382–57–91, Revision 1, dated March 25, 2009, 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 Lockheed Continued Airworthiness Project Office, Attention Airworthiness, 86 South Cobb Drive, Marietta, Georgia 30063–0567; telephone 770–494–5444; fax 770–494–5445; e-mail ams.portal@lmco.com; Internet https:// www.lockheedmartin.com/ams/tools/ TechPubs.html. (3) You may review copies of the service information at the FAA, Transport Airplane E:\FR\FM\20MYR1.SGM 20MYR1 Federal Register / Vol. 74, No. 96 / Wednesday, May 20, 2009 / Rules and Regulations Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (4) You may also review copies of the service information that is incorporated by reference 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: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on May 7, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–11590 Filed 5–19–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0035; Directorate Identifier 2008–NM–096–AD; Amendment 39–15909; AD 2009–10–13] RIN 2120–AA64 Airworthiness Directives; Saab AB, Saab Aerosystems Model 340A (SAAB/ SF340A) and SAAB 340B Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM– 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1112; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion 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 February 17, 2009 (74 FR 7384). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Field experiences have revealed cracks in the frames and closing angle on the forward engine cowl door NS STA [nacelle station] 203 and 250. In case of a damaged frame and/or closing angle, the forward engine cowl door can loosen during flight and depart from the aircraft. This AD is issued to require a detailed inspection to find out if there are any cracks [or deformations or wear damage] in the frames and/or the closing angles. The inspection is on four points on each of the forward engine cowl doors. The corrective action depends on if the crack, deformation, or wear damage is within or outside certain defined limits, and includes doing a repair either in accordance with the specified service information, or contacting Saab for repair instructions and doing the repair. You may obtain further information by examining the MCAI in the AD docket. We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. * We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. VerDate Nov<24>2008 14:51 May 19, 2009 Jkt 217001 Conclusion 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 PO 00000 Frm 00009 to ensure the AD is clear for U.S. operators and is enforceable. 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 our FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance We estimate that this AD will affect 141 products of U.S. registry. We also estimate that it will take about 2 workhours per product to comply with the basic requirements of this AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $22,560, or $160 per product. 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 Comments Field experiences have revealed cracks in the frames and closing angle on the forward engine cowl door * * *. In case of a damaged frame and/or closing angle, the forward engine cowl door can loosen during flight and depart from the aircraft. * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective June 24, 2009. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 24, 2009. ADDRESSES: You may examine the AD docket on the Internet at https:// 23617 Fmt 4700 Sfmt 4700 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. For the reasons discussed above, I certify 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 E:\FR\FM\20MYR1.SGM 20MYR1

Agencies

[Federal Register Volume 74, Number 96 (Wednesday, May 20, 2009)]
[Rules and Regulations]
[Pages 23614-23617]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-11590]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0462; Directorate Identifier 2009-NM-063-AD; 
Amendment 39-15913; AD 2009-11-03]
RIN 2120-AA64


Airworthiness Directives; Lockheed Model 382, 382B, 382E, 382F, 
and 382G Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Lockheed Model 382, 382B, 382E, 382F, and 382G series airplanes. This 
AD requires an inspection to identify discrepant barrel nuts in the 
upper wing joint, engine truss, and rear beam pylon support; and 
replacement of any discrepant barrel nut with a new barrel nut, if 
necessary. This AD results from

[[Page 23615]]

a report of severe cracking of multiple barrel nuts in the wing station 
(WS) 220 upper wing joint found during scheduled maintenance. We are 
issuing this AD to prevent cracking of the barrel nuts in the upper 
wing joint, engine truss, and rear beam pylon support, which could 
result in reduced structural integrity of the affected part and 
consequent detachment of the wing or engine from the airplane.

DATES: This AD is effective June 4, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of June 4, 2009.
    We must receive comments on this AD by July 20, 2009.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Lockheed 
Continued Airworthiness Project Office, Attention Airworthiness, 86 
South Cobb Drive, Marietta, Georgia 30063-0567; telephone 770-494-5444; 
fax 770-494-5445; e-mail ams.portal@lmco.com; Internet https://www.lockheedmartin.com/ams/tools/TechPubs.html.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.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 AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Carl Gray, Aerospace Engineer, 
Airframe Branch, ACE-117A, FAA, Atlanta Aircraft Certification Office, 
One Crown Center, 1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia 
30349; telephone (770) 703-6131; fax (770) 703-6097.

SUPPLEMENTARY INFORMATION: 

Discussion

    We received a report of severe cracking of multiple barrel nuts in 
the wing station (WS) 220 upper wing joint found during scheduled 
maintenance. Deformed thread locking barrel nuts having a certain part 
number were identified as having greater potential for cracking during 
routine service. The affected nut might also be installed at the quick 
engine change (QEC) lower attachment to the truss mount and at the 
outer wing station (OWS) 330 rear beam pylon attach fitting. This 
condition, if not corrected, could result in reduced structural 
integrity of the affected part and consequent detachment of the wing or 
engine from the airplane.

Relevant Service Information

    We reviewed Lockheed Alert Service Bulletin A382-57-91, Revision 1, 
dated March 25, 2009. The service bulletin describes procedures for an 
inspection to identify discrepant barrel nuts (with deformed thread 
locking, impression stamp ``K,'' no impression stamp, or cracking) in 
the upper wing joint, engine truss, and rear beam pylon support; and 
replacement of any discrepant barrel nut with a new barrel nut, if 
necessary.

FAA's Determination and Requirements of This AD

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of these same type 
designs. This AD requires accomplishing the actions specified in the 
service information described previously, except as discussed under 
``Differences Between the AD and the Service Information.''

Differences Between the AD and the Service Information

    Although the Accomplishment Instructions of Lockheed Alert Service 
Bulletin A382-57-91, Revision 1, dated March 25, 2009, specify that 
operators may contact the manufacturer for disposition of certain 
repair conditions, this AD would require operators to repair those 
conditions using a method approved by the FAA.
    The Accomplishment Instructions of Lockheed Alert Service Bulletin 
A382-57-91, Revision 1, dated March 25, 2009, recommend inspecting to 
identify discrepant barrel nuts before further flight, but we have 
determined that this compliance time would not give operators enough 
time to inspect all affected airplanes. In developing an appropriate 
compliance time for this AD, we considered the manufacturer's 
recommendation, the degree of urgency associated with the subject 
unsafe condition, the average utilization of the affected fleet, and 
the time necessary to perform the inspection (1 work-hour). In light of 
all these factors, we find that a 30-day compliance time represents an 
appropriate time for affected airplanes to continue to operate without 
compromising safety. These differences have been coordinated with the 
manufacturer.

FAA's Justification and Determination of the Effective Date

    Because of our requirement to promote safe flight of civil aircraft 
and thus the critical need to prevent cracking of certain barrel nuts 
which could result in reduced structural integrity of the affected part 
and consequent detachment of the wing or engine, and the short 
compliance time involved with this action, this AD must be issued 
immediately.
    Because an unsafe condition exists that requires the immediate 
adoption of this AD, we find that notice and opportunity for prior 
public comment hereon are impracticable and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments before it becomes effective. However, we invite 
you to send any written data, views, or arguments about this AD. Send 
your comments to an address listed under the ADDRESSES section. Include 
``Docket No. FAA-2009-0462; Directorate Identifier 2009-NM-063-AD'' at 
the beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of this 
AD. We will consider all comments received by the closing date and may 
amend this AD because of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about 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:

[[Page 23616]]

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

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979), and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

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 amends 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 AD:

2009-11-03 Lockheed: Amendment 39-15913. Docket No. FAA-2009-0462; 
Directorate Identifier 2009-NM-063-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective June 4, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Lockheed Model 382, 382B, 382E, 382F, 
and 382G series airplanes, certificated in any category.

Subject

    (d) Air Transport Association (ATA) of America Code 57: Wings.

Unsafe Condition

    (e) This AD results from a report of severe cracking of multiple 
barrel nuts in the wing station (WS) 220 upper wing joint found 
during scheduled maintenance. We are issuing this AD to prevent 
cracking of the barrel nuts in the upper wing joint, engine truss, 
and rear beam pylon support, which could result in reduced 
structural integrity of the affected part and consequent detachment 
of the wing or engine from the airplane.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Inspection/Replacement if Necessary

    (g) Within 30 days after the effective date of this AD: Do a 
general visual inspection to identify discrepant barrel nuts in the 
upper wing joint, engine truss, and rear beam pylon support, in 
accordance with the Accomplishment Instructions of Lockheed Alert 
Service Bulletin A382-57-91, Revision 1, dated March 25, 2009. 
Except as provided by paragraph (h) of this AD, if any discrepant 
barrel nut is found, before further flight, replace the barrel nut 
with a new barrel nut in accordance with the service bulletin.

    Note 1: For the purposes of this AD, a general visual inspection 
is: ``A visual 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.''

Exception to Corrective Action Instructions

    (h) If any discrepant barrel nut is found during the inspection 
required by this AD, and Lockheed Alert Service Bulletin A382-57-91, 
Revision 1, dated March 25, 2009, specifies contacting Lockheed for 
appropriate action: Before further flight, replace the discrepant 
barrel nut using a method approved by the Manager, Atlanta Aircraft 
Certification Office (ACO), FAA. For a repair method to be approved 
by the Manager, Atlanta ACO, as required by this paragraph, the 
Manager's approval letter must specifically refer to this AD.

Credit for Actions Done Using Previous Service Information

    (i) Actions done before the effective date of this AD in 
accordance with Lockheed Alert Service Bulletin A382-57-91, dated 
March 6, 2009, are acceptable for compliance with the corresponding 
requirements of this AD.

Reporting Not Required

    (j) Although Lockheed Alert Service Bulletin A382-57-91, 
Revision 1, dated March 25, 2009, specifies to submit certain 
information to the manufacturer, this AD does not include that 
requirement.

Parts Installation

    (k) As of the time specified in paragraph (k)(1) or (k)(2) of 
this AD, as applicable, no person may install, on any airplane, a 
barrel nut in the upper wing joint, engine truss, and rear beam 
pylon support unless the barrel nut has been modified in accordance 
with the Accomplishment Instructions of Lockheed Alert Service 
Bulletin A382-57-91, Revision 1, dated March 25, 2009.
    (1) For unmarked barrel nuts with a deformed thread locking 
style: As of 30 days after the effective date of this AD.
    (2) For all other discrepant barrel nuts: As of the effective 
date of this AD.

Alternative Methods of Compliance (AMOCs)

    (l)(1) The Manager, Atlanta ACO, FAA, has the authority to 
approve AMOCs for this AD, if requested using the procedures found 
in 14 CFR 39.19. Send information to ATTN: Carl Gray, Aerospace 
Engineer, Airframe Branch, ACE-117A, Atlanta ACO, FAA, One Crown 
Center, 1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia 30349; 
telephone (770) 703-6131; fax (770) 703-6097.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.

Material Incorporated by Reference

    (m) You must use Lockheed Alert Service Bulletin A382-57-91, 
Revision 1, dated March 25, 2009, 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 
Lockheed Continued Airworthiness Project Office, Attention 
Airworthiness, 86 South Cobb Drive, Marietta, Georgia 30063-0567; 
telephone 770-494-5444; fax 770-494-5445; e-mail 
ams.portal@lmco.com; Internet https://www.lockheedmartin.com/ams/tools/TechPubs.html.
    (3) You may review copies of the service information at the FAA, 
Transport Airplane

[[Page 23617]]

Directorate, 1601 Lind Avenue, SW., Renton, Washington. For 
information on the availability of this material at the FAA, call 
425-227-1221 or 425-227-1152.
    (4) You may also review copies of the service information that 
is incorporated by reference 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: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on May 7, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-11590 Filed 5-19-09; 8:45 am]
BILLING CODE 4910-13-P
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