Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model L-1011 Series Airplanes, 58416-58420 [2011-24270]

Download as PDF 58416 Proposed Rules Federal Register Vol. 76, No. 183 Wednesday, September 21, 2011 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0919; Directorate Identifier 2010–NM–088–AD] RIN 2120–AA64 Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model L–1011 Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Model L–1011 series airplanes. This proposed AD would require repetitive inspections for cracking of the wing rear spar and upper surface zones, and repair if necessary. This proposed AD results from a damage tolerance analysis conducted by the manufacturer indicating that fatigue cracking could occur in those areas. We are proposing this AD to detect and correct such fatigue cracking, which could result in cracking that grows large enough to reduce the wing strength below certificated requirements and possibly cause fracture of the rear spar, resulting in extensive damage to the wing and possible fuel leaks. DATES: We must receive comments on this proposed AD by November 7, 2011. 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 mstockstill on DSK4VPTVN1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 17:46 Sep 20, 2011 Jkt 223001 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 proposed AD, contact Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, Airworthiness Office, Dept. 6A0M, Zone 0252, Column P–58, 86 S. Cobb Drive, Marietta, Georgia 30063; telephone 770–494– 5444; fax 770–494–5445; e-mail ams.portal@lmco.com; Internet https:// www.lockheedmartin.com/ams/tools/ TechPubs.html. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone 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 (ACO), 1701 Columbia Avenue, College Park, Georgia 30337; phone: 404–474–5554; fax: 404– 474–5606; e-mail: Carl.W.Gray@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2011–0919; Directorate Identifier PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 2010–NM–088–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed 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 proposed AD. Discussion We previously issued AD 94–05–01, Amendment 39–8839 (59 FR 10275, March 4, 1994), and AD 2000–21–01, Amendment 39–11933 (65 FR 62994, October 20, 2000), which require modifications to extend the life of the wing rear spar inboard area. The modifications required by those two ADs removed cracks in the wing upper skin and installed repair bushings as necessary. The lower spar cap was modified by adding nested angles and cold working the attachment holes. Based upon a damage tolerance analysis, additional inspections are required to ensure the structural integrity of the structure modified in accordance with those two ADs as well as the adjoining baseline structure. If cracking is undetected and unrepaired, it could result in cracking that grows large enough to reduce the wing strength below certificated requirements and possibly cause fracture of the rear spar, resulting in extensive damage to the wing and possible fuel leaks. Relevant Service Information We have reviewed Lockheed Service Bulletin 093–57–226, dated August 31, 2009. This service bulletin describes procedures for repetitive eddy current non-destructive inspections (NDI) and detailed inspections for cracking of the wing rear spar and upper surface zones. The service bulletin identifies inspections for the airplane models in the zones identified in the following table, titled ‘‘Inspections.’’ E:\FR\FM\21SEP1.SGM 21SEP1 Federal Register / Vol. 76, No. 183 / Wednesday, September 21, 2011 / Proposed Rules 58417 TABLE—INSPECTIONS Airplane models Inspection type L–1011–385–1, L–1011–385–1–14, and L–1011–385– 1–15. Non-destructive ............................................................ 1A through 1E. Detailed Visual ............................................................. 1F. Non-destructive ............................................................ Detailed Visual ............................................................. 3A through 3E. 3F. L–1011–385–3 ............................................................... For airplanes on which cracking is found during any inspection, this service information specifies a bolt hole eddy current inspection to verify the cracking. The corrective actions for cracking include repairing cracking if the cracking is within specified limits, or contacting the manufacturer for repair instructions if the cracking is not within specified limits. Related Rulemaking AD 94–05–01, Amendment 39–8839 (59 FR 10275, March 4, 1994), and AD 2000–21–01, Amendment 39–11933 (65 FR 62994, October 20, 2000), specify structural modification installations on Model L–1011 series airplanes. This proposed AD would not change the requirements of AD 94–05–01 and AD 2000–21–01. However, this proposed AD would require new inspections for structures affected by the modifications required by those two ADs. Zone(s) FAA’s Determination and Requirements of this Proposed AD We are proposing this AD because we evaluated all relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of these same type designs. This proposed AD would require accomplishing the actions specified in Lockheed Service Bulletin 093–57–226, dated August 31, 2009, described previously. Differences Between the Proposed AD and the Service Information This proposed AD specifies initial compliance times and repetitive inspection intervals that differ from those contained in Lockheed Service Bulletin 093–57–226, dated August 31, 2009. The changes have been coordinated with Lockheed Martin and they concur with the FAA’s position. The compliance times were changes to simplify the inspection requirements. We also propose that all crack findings be repaired before further flight. We have determined that the compliance times, as proposed, represent the maximum interval of time allowable for the affected airplanes to continue to safely operate before the inspections and repairs, if necessary, are done. Although that service bulletin specifies that operators may contact the manufacturer for disposition of certain repairs, this proposed AD would require operators to repair those conditions in accordance with a method approved by the FAA. Interim Action We consider this proposed AD interim action. If final action is later identified, we might consider further rulemaking then. Costs of Compliance We estimate that this proposed AD affects 4 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Parts cost mstockstill on DSK4VPTVN1PROD with PROPOSALS Models: L–1011–385–1, L–1011–385–1– 21 work-hours × $85 per 14, L–1011–385–1–15, Zones 1A hour = $1,785 per inspecthrough 1E (Non-destructive Inspection). tion cycle. Models: L–1011–385–1, L–1011–385–1– 5 work-hours × $85 per hour 14, L–1011–385–1–15, Zone 1F (De= $425 per inspection tailed Inspection). cycle. Model: L–1011–385–3, Zones 1A through 24 work-hours × $85 per 1E (Non-destructive Inspection). hour = $2,040 per inspection cycle. Model: L–1011–385–3, Zone 1F (Detailed 5 work-hours × $85 per hour Inspection). = $425 per inspection cycle. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed 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 VerDate Mar<15>2010 17:46 Sep 20, 2011 Jkt 223001 Cost per product $0 $1,785 per inspection cycle. $3,570 per inspection cycle (2 airplanes). 0 $425 per inspection cycle. $850 per inspection cycle (2 airplanes). 0 $2,040 per inspection cycle. $4,080 per inspection cycle (2 airplanes). 0 $425 per inspection cycle. $850 per inspection cycle (2 airplanes). 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 PO 00000 Frm 00002 Fmt 4702 Cost on U.S. operators Sfmt 4702 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on E:\FR\FM\21SEP1.SGM 21SEP1 58418 Federal Register / Vol. 76, No. 183 / Wednesday, September 21, 2011 / Proposed Rules 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 proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Lockheed Martin Corporation/Lockheed Martin Aeronautics Company: Docket No. FAA–2011–0919; Directorate Identifier 2010–NM–088–AD. Comments Due Date (a) We must receive comments by November 7, 2011. Affected ADs (b) None. Applicability (c) This AD applies to Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model L–1011–385–1, L–1011– 385–1–14, L–1011–385–1–15, and L–1011– 385–3 airplanes, certificated in any category, serial numbers 1002 through 1250 inclusive. Subject (d) Air Transport Association (ATA) of America Code 57, Wings. Unsafe Condition (e) This AD results from a damage tolerance analysis conducted by the manufacturer that indicates fatigue cracking could occur in the wing rear spar and upper surface zones. The Federal Aviation Administration is issuing this AD to detect and correct such fatigue cracking, which could result in cracking that grows large enough to reduce the wing strength below certificated requirements and possibly cause fracture of the rear spar, resulting in extensive damage to the wing and possible fuel leaks. 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. Inspections of Wing Rear Spar and Upper Surface Zones, and Corrective Actions (g) At the applicable time specified in paragraph (k) of this AD, do eddy current non-destructive inspections (NDI) and detailed inspections for cracking at the applicable zones specified in paragraph (g)(1) or (g)(2) of this AD, in accordance with the Accomplishment Instructions of Lockheed Service Bulletin 093–57–226, dated August 31, 2009. Repeat the inspections thereafter at the applicable interval specified in Table 1 of this AD. (1) For Model L–1011–385–1, L–1011–385– 1–14, and L–1011–385–1–15 airplanes: Zones 1A through 1E, and Zone 1F. (2) For Model L–1011–385–3 airplanes: Zones 3A through 3E, and Zone 3F. Additional Inspection if Cracking is Found (h) Except as specified in paragraph (j) of this AD, if any cracking is detected during any inspection required by paragraph (g) of this AD: Before further flight, remove the fastener(s) at the suspect area, as defined in Lockheed Service Bulletin 093–57–226, dated August 31, 2009; and do a secondary eddy current inspection to detect cracking of fastener holes with suspected crack indications; in accordance with the Accomplishment Instructions of Lockheed Service Bulletin 093–57–226, dated August 31, 2009. Repair (i) Except as specified in paragraph (j) of this AD, if a crack finding is confirmed by the inspection required by paragraph (h) of this AD and the cracking is within the allowable repair limits specified in Lockheed Martin Repair Drawing LCC7622–369, Revision March 30, 1995: Before further flight, repair the cracking, in accordance with Lockheed Martin Repair Drawing LCC7622– 369, Revision March 30, 1995. If a crack finding confirmed by the inspection required by paragraph (h) of this AD is not within the allowable repair limits specified in Lockheed Martin Repair Drawing LCC7622–369, Revision March 30, 1995: Before further flight, repair the cracking, in accordance with 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. Exception to Service Bulletin (j) If any cracking is found during any inspection required by this AD, and Lockheed Service Bulletin 093–57–226, dated August 31, 2009; or Lockheed Martin Repair Drawing LCC7622–369, Revision March 30, 1995; specifies contacting Lockheed for appropriate action: Before further flight, repair the cracking in accordance with a method approved by the Manager, Atlanta 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. Compliance Times for Inspections (k) Do the inspections required by paragraph (g) of this AD at the applicable time specified in table 1 of this AD. TABLE 1—COMPLIANCE TIMES FOR INSPECTIONS mstockstill on DSK4VPTVN1PROD with PROPOSALS Airplane models and zones Compliance time (whichever occurs later) L–1011–385–1 having accumulated Within 7,000 flight cycles or 10 fewer than 7,000 flight cycles years after the accomplishment of after the accomplishment of LockLockheed Martin Service Bulletin heed Martin Service Bulletin 093– 093–57–184, 093–57–196, or 57–184, 093–57–196, or 093–57– 093–57–215, whichever occurs 215; as of the effective date of first. this AD; Zones 1A through 1E (Non-destructive Inspection (NDI)). VerDate Mar<15>2010 17:46 Sep 20, 2011 Jkt 223001 PO 00000 Frm 00003 Fmt 4702 Repetitive interval (not to exceed) Within 1,000 flight cycles after the effective date of this AD. Sfmt 4702 E:\FR\FM\21SEP1.SGM 21SEP1 1,100 flight cycles. Federal Register / Vol. 76, No. 183 / Wednesday, September 21, 2011 / Proposed Rules mstockstill on DSK4VPTVN1PROD with PROPOSALS TABLE 1—COMPLIANCE TIMES FOR INSPECTIONS—Continued L–1011–385–1 having accumulated fewer than 7,000 flight cycles after the accomplishment of Lockheed Martin Service Bulletin 093– 57–184, 093–57–196, or 093–57– 215; as of the effective date of this AD; Zone 1F (Detailed Inspection). L–1011–385–1 having accumulated 7,000 flight cycles or more flight cycles after the accomplishment of Lockheed Martin Service Bulletin 093–57–184, 093–57–196, or 093–57–215; as of the effective date of this AD; Zones 1A through 1E (NDI). L–1011–385–1 having accumulated 7,000 flight cycles or more after the accomplishment of Lockheed Martin Service Bulletin 093–57– 184, 093–57–196, or 093–57– 215; as of the effective date of this AD; Zone 1F (Detailed Inspection). L–1011–385–1–14 having accumulated fewer than 6,900 flight cycles after the accomplishment of Lockheed Martin Service Bulletin 093–57–184, 093–57–196, or 093–57–215; as of the effective date of this AD; Zones 1A through 1E (NDI). L–1011–385–1–14 having accumulated fewer than 6,900 flight cycles after the accomplishment of Lockheed Martin Service Bulletin 093–57–184, 093–57–196, or 093–57–215; as of the effective date of this AD; Zone 1F (Detailed Inspection). L–1011–385–1–14 having accumulated 6,900 or more flight cycles after the accomplishment of Lockheed Martin Service Bulletin 093– 57–184, 093–57–196, or 093–57– 215; as of the effective date of this AD; Zones 1A through 1E (NDI). L–1011–385–1–14 having accumulated 6,900 or more flight cycles after the accomplishment of Lockheed Martin Service Bulletin 093– 57–184, 093–57–196, or 093–57– 215; as of the effective date of this AD; Zone 1F (Detailed Inspection). L–1011–385–1–15 having accumulated fewer than 5,600 flight cycles after the accomplishment of Lockheed Martin Service Bulletin 093–57–184, 093–57–196, or 093–57–215; as of the effective date of this AD; Zones 1A through 1E (NDI). L–1011–385–1–15 having accumulated fewer than 5,600 flight cycles after the accomplishment of Lockheed Martin Service Bulletin 093–57–184, 093–57–196, or 093–57–215; as of the effective date of this AD; Zone 1F (Detailed Inspection). VerDate Mar<15>2010 17:46 Sep 20, 2011 Within 7,000 flight cycles or 10 years after the accomplishment of Lockheed Martin Service Bulletin 093–57–184, 093–57–196, or 093–57–215, whichever occurs first. Within 90 flight cycles or 30 days after the effective date of this AD, whichever occurs later. 90 flight cycles. Within 1,000 flight cycles or 12 months after the effective date of this AD, whichever occurs first. N/A ................................................... 1,100 flight cycles. Within 90 flight cycles after the effective date of this AD. Within 30 days after the effective date of this AD. 90 flight cycles. Within 6,900 flight cycles or 10 years after the accomplishment of Lockheed Martin Service Bulletin 093–57–184, 093–57–196, or 093–57–215, whichever occurs first. Within 1,000 flight cycles after the effective date of this AD. 900 flight cycles. Within 6,900 flight cycles or 10 years after the accomplishment of Lockheed Martin Service Bulletin 093–57–184, 093–57–196, or 093–57–215, whichever occurs first. Within 90 flight cycles or 30 days after the effective date of this AD, whichever occurs later. 90 flight cycles. Within 1,000 flight cycles or 12 months after the effective date of this AD, whichever occurs first. N/A ................................................... 900 flight cycles. Within 90 flight cycles after the effective date of this AD. Within 30 days after the effective date of this AD. 90 flight cycles. Within 5,600 flight cycles or 10 years after the accomplishment of Lockheed Martin Service Bulletin 093–57–184, 093–57–196, or 093–57–215, whichever occurs first. Within 1,000 flight cycles after the effective date of this AD. 500 flight cycles. Within 5,600 flight cycles or 10 years after the accomplishment of Lockheed Martin Service Bulletin 093–57–184, 093–57–196, or 093–57–215, whichever occurs first. Within 60 flight cycles or 30 days after the effective date of this AD, whichever occurs later. 60 flight cycles. Jkt 223001 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 E:\FR\FM\21SEP1.SGM 21SEP1 58419 58420 Federal Register / Vol. 76, No. 183 / Wednesday, September 21, 2011 / Proposed Rules TABLE 1—COMPLIANCE TIMES FOR INSPECTIONS—Continued mstockstill on DSK4VPTVN1PROD with PROPOSALS L–1011–385–1–15 having accumulated 5,600 or more flight cycles after the accomplishment of Lockheed Martin Service Bulletin 093– 57–184, 093–57–196, or 093–57– 215; as of the effective date of this AD; Zones 1A through 1E (NDI). L–1011–385–1–15 having accumulated 5,600 or more flight cycles after the accomplishment of Lockheed Martin Service Bulletin 093– 57–184, 093–57–196, or 093–57– 215; as of the effective date of this AD; Zone 1F (Detailed Inspection). L–1011–385–3 having accumulated fewer than 8,400 flight cycles after the accomplishment of Lockheed Martin Service Bulletin 093– 57–184, 093–57–196, or 093–57– 215; as of the effective date of this AD; Zones 1A through 1E (NDI). L–1011–385–3 having accumulated fewer than 8,400 flight cycles after the accomplishment of Lockheed Martin Service Bulletin 093– 57–184, 093–57–196, or 093–57– 215; as of the effective date of this AD; Zone 1F (Detailed Inspection). L–1011–385–3 having accumulated 8,400 or more flight cycles after the accomplishment of Lockheed Martin Service Bulletin 093–57– 184, 093–57–196, or 093–57– 215; as of the effective date of this AD; Zones 1A through 1E (NDI). L–1011–385–3 having accumulated 8,400 or more flight cycles after the accomplishment of Lockheed Martin Service Bulletin 093–57– 184, 093–57–196, or 093–57– 215; as of the effective date of this AD; Zone 1F (Detailed Inspection). Within 1,000 flight cycles or 12 months after the effective date of this AD, whichever occurs first. N/A ................................................... 500 flight cycles. Within 60 flight cycles after the effective date of this AD. Within 30 days after the effective date of this AD. 60 flight cycles. Within 8,400 flight cycles or 10 years after the accomplishment of Lockheed Martin Service Bulletin 093–57–184, 093–57–196, or 093–57–215, whichever occurs first. Within 1,000 flight cycles after the effective date of this AD. 1,200 flight cycles. Within 90 flight cycles or 30 days after the effective date of this AD, whichever occurs later. Within 85 flight cycles or 30 days after the effective date of this AD, whichever occurs later. 85 flight cycles. Within 1,000 flight cycles or 12 months after the effective date of this AD, whichever occurs first. N/A ................................................... 1,200 flight cycles. Within 85 flight cycles after the effective date of this AD. Within 30 days after the effective date of this AD. 85 flight cycles. 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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. Georgia 30337; phone: 404–474–5554; fax: 404–474–5606; e-mail: Carl.W.Gray@faa.gov. Issued in Renton, Washington, on September 14, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. 17:46 Sep 20, 2011 Jkt 223001 Bureau of Economic Analysis 15 CFR Part 806 [Docket No. 110822526–1525–01] RIN 0691–AA80 [FR Doc. 2011–24270 Filed 9–20–11; 8:45 am] Direct Investment Surveys: BE–12, Benchmark Survey of Foreign Direct Investment in the United States BILLING CODE 4910–13–P Bureau of Economic Analysis, Commerce. ACTION: Notice of proposed rulemaking. AGENCY: This proposed rule would amend regulations of the Department of Commerce’s Bureau of Economic Analysis (BEA) to set forth the reporting requirements for the 2012 BE–12, SUMMARY: Related Information (m) For more information about this AD, contact Carl Gray, Aerospace Engineer, Airframe Branch, ACE–117A, FAA, Atlanta ACO, 1701 Columbia Avenue, College Park, VerDate Mar<15>2010 DEPARTMENT OF COMMERCE PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 E:\FR\FM\21SEP1.SGM 21SEP1

Agencies

[Federal Register Volume 76, Number 183 (Wednesday, September 21, 2011)]
[Proposed Rules]
[Pages 58416-58420]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-24270]

========================================================================
Proposed Rules
Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.

========================================================================

Federal Register / Vol. 76, No. 183 / Wednesday, September 21, 2011 /
Proposed Rules

[[Page 58416]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0919; Directorate Identifier 2010-NM-088-AD]
RIN 2120-AA64

Airworthiness Directives; Lockheed Martin Corporation/Lockheed
Martin Aeronautics Company Model L-1011 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Model L-1011 series airplanes. This proposed AD would require
repetitive inspections for cracking of the wing rear spar and upper
surface zones, and repair if necessary. This proposed AD results from a
damage tolerance analysis conducted by the manufacturer indicating that
fatigue cracking could occur in those areas. We are proposing this AD
to detect and correct such fatigue cracking, which could result in
cracking that grows large enough to reduce the wing strength below
certificated requirements and possibly cause fracture of the rear spar,
resulting in extensive damage to the wing and possible fuel leaks.

DATES: We must receive comments on this proposed AD by November 7,
2011.

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 proposed AD, contact
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company,
Airworthiness Office, Dept. 6A0M, Zone 0252, Column P-58, 86 S. Cobb
Drive, Marietta, Georgia 30063; telephone 770-494-5444; fax 770-494-
5445; e-mail ams.portal@lmco.com; Internet https://www.lockheedmartin.com/ams/tools/TechPubs.html. You may review copies
of the referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information
on the availability of this material at the FAA, call 425-227-1221.

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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (phone 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
(ACO), 1701 Columbia Avenue, College Park, Georgia 30337; phone: 404-
474-5554; fax: 404-474-5606; e-mail: Carl.W.Gray@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2011-0919;
Directorate Identifier 2010-NM-088-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed 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 proposed AD.

Discussion

We previously issued AD 94-05-01, Amendment 39-8839 (59 FR 10275,
March 4, 1994), and AD 2000-21-01, Amendment 39-11933 (65 FR 62994,
October 20, 2000), which require modifications to extend the life of
the wing rear spar inboard area. The modifications required by those
two ADs removed cracks in the wing upper skin and installed repair
bushings as necessary. The lower spar cap was modified by adding nested
angles and cold working the attachment holes.
Based upon a damage tolerance analysis, additional inspections are
required to ensure the structural integrity of the structure modified
in accordance with those two ADs as well as the adjoining baseline
structure. If cracking is undetected and unrepaired, it could result in
cracking that grows large enough to reduce the wing strength below
certificated requirements and possibly cause fracture of the rear spar,
resulting in extensive damage to the wing and possible fuel leaks.

Relevant Service Information

We have reviewed Lockheed Service Bulletin 093-57-226, dated August
31, 2009. This service bulletin describes procedures for repetitive
eddy current non-destructive inspections (NDI) and detailed inspections
for cracking of the wing rear spar and upper surface zones. The service
bulletin identifies inspections for the airplane models in the zones
identified in the following table, titled ``Inspections.''

[[Page 58417]]

Table--Inspections
------------------------------------------------------------------------
Airplane models Inspection type Zone(s)
------------------------------------------------------------------------
L-1011-385-1, L-1011-385-1-14, Non-destructive....... 1A through 1E.
and L-1011-385-1-15.
-----------------------------------------
Detailed Visual....... 1F.
------------------------------------------------------------------------
L-1011-385-3.................. Non-destructive....... 3A through 3E.
Detailed Visual....... 3F.
------------------------------------------------------------------------

For airplanes on which cracking is found during any inspection,
this service information specifies a bolt hole eddy current inspection
to verify the cracking. The corrective actions for cracking include
repairing cracking if the cracking is within specified limits, or
contacting the manufacturer for repair instructions if the cracking is
not within specified limits.

Related Rulemaking

AD 94-05-01, Amendment 39-8839 (59 FR 10275, March 4, 1994), and AD
2000-21-01, Amendment 39-11933 (65 FR 62994, October 20, 2000), specify
structural modification installations on Model L-1011 series airplanes.
This proposed AD would not change the requirements of AD 94-05-01 and
AD 2000-21-01. However, this proposed AD would require new inspections
for structures affected by the modifications required by those two ADs.

FAA's Determination and Requirements of this Proposed AD

We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of these same type
designs. This proposed AD would require accomplishing the actions
specified in Lockheed Service Bulletin 093-57-226, dated August 31,
2009, described previously.

Differences Between the Proposed AD and the Service Information

This proposed AD specifies initial compliance times and repetitive
inspection intervals that differ from those contained in Lockheed
Service Bulletin 093-57-226, dated August 31, 2009. The changes have
been coordinated with Lockheed Martin and they concur with the FAA's
position. The compliance times were changes to simplify the inspection
requirements. We also propose that all crack findings be repaired
before further flight. We have determined that the compliance times, as
proposed, represent the maximum interval of time allowable for the
affected airplanes to continue to safely operate before the inspections
and repairs, if necessary, are done.
Although that service bulletin specifies that operators may contact
the manufacturer for disposition of certain repairs, this proposed AD
would require operators to repair those conditions in accordance with a
method approved by the FAA.

Interim Action

We consider this proposed AD interim action. If final action is
later identified, we might consider further rulemaking then.

Costs of Compliance

We estimate that this proposed AD affects 4 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:

Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Models: L-1011-385-1, L-1011-385- 21 work-hours x $85 $0 $1,785 per $3,570 per
1-14, L-1011-385-1-15, Zones 1A per hour = $1,785 inspection cycle. inspection cycle
through 1E (Non-destructive per inspection (2 airplanes).
Inspection). cycle.
Models: L-1011-385-1, L-1011-385- 5 work-hours x $85 0 $425 per inspection $850 per inspection
1-14, L-1011-385-1-15, Zone 1F per hour = $425 cycle. cycle
(Detailed Inspection). per inspection (2 airplanes).
cycle.
Model: L-1011-385-3, Zones 1A 24 work-hours x $85 0 $2,040 per $4,080 per
through 1E (Non-destructive per hour = $2,040 inspection cycle. inspection cycle
Inspection). per inspection (2 airplanes).
cycle.
Model: L-1011-385-3, Zone 1F 5 work-hours x $85 0 $425 per inspection $850 per inspection
(Detailed Inspection). per hour = $425 cycle. cycle
per inspection (2 airplanes).
cycle.
----------------------------------------------------------------------------------------------------------------

We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on

[[Page 58418]]

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 proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

The Proposed Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

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

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by adding the following new AD:

Lockheed Martin Corporation/Lockheed Martin Aeronautics Company:
Docket No. FAA-2011-0919; Directorate Identifier 2010-NM-088-AD.

Comments Due Date

(a) We must receive comments by November 7, 2011.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Lockheed Martin Corporation/Lockheed
Martin Aeronautics Company Model L-1011-385-1, L-1011-385-1-14, L-
1011-385-1-15, and L-1011-385-3 airplanes, certificated in any
category, serial numbers 1002 through 1250 inclusive.

Subject

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

Unsafe Condition

(e) This AD results from a damage tolerance analysis conducted
by the manufacturer that indicates fatigue cracking could occur in
the wing rear spar and upper surface zones. The Federal Aviation
Administration is issuing this AD to detect and correct such fatigue
cracking, which could result in cracking that grows large enough to
reduce the wing strength below certificated requirements and
possibly cause fracture of the rear spar, resulting in extensive
damage to the wing and possible fuel leaks.

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.

Inspections of Wing Rear Spar and Upper Surface Zones, and Corrective
Actions

(g) At the applicable time specified in paragraph (k) of this
AD, do eddy current non-destructive inspections (NDI) and detailed
inspections for cracking at the applicable zones specified in
paragraph (g)(1) or (g)(2) of this AD, in accordance with the
Accomplishment Instructions of Lockheed Service Bulletin 093-57-226,
dated August 31, 2009. Repeat the inspections thereafter at the
applicable interval specified in Table 1 of this AD.
(1) For Model L-1011-385-1, L-1011-385-1-14, and L-1011-385-1-15
airplanes: Zones 1A through 1E, and Zone 1F.
(2) For Model L-1011-385-3 airplanes: Zones 3A through 3E, and
Zone 3F.

Additional Inspection if Cracking is Found

(h) Except as specified in paragraph (j) of this AD, if any
cracking is detected during any inspection required by paragraph (g)
of this AD: Before further flight, remove the fastener(s) at the
suspect area, as defined in Lockheed Service Bulletin 093-57-226,
dated August 31, 2009; and do a secondary eddy current inspection to
detect cracking of fastener holes with suspected crack indications;
in accordance with the Accomplishment Instructions of Lockheed
Service Bulletin 093-57-226, dated August 31, 2009.

Repair

(i) Except as specified in paragraph (j) of this AD, if a crack
finding is confirmed by the inspection required by paragraph (h) of
this AD and the cracking is within the allowable repair limits
specified in Lockheed Martin Repair Drawing LCC7622-369, Revision
March 30, 1995: Before further flight, repair the cracking, in
accordance with Lockheed Martin Repair Drawing LCC7622-369, Revision
March 30, 1995. If a crack finding confirmed by the inspection
required by paragraph (h) of this AD is not within the allowable
repair limits specified in Lockheed Martin Repair Drawing LCC7622-
369, Revision March 30, 1995: Before further flight, repair the
cracking, in accordance with 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.

Exception to Service Bulletin

(j) If any cracking is found during any inspection required by
this AD, and Lockheed Service Bulletin 093-57-226, dated August 31,
2009; or Lockheed Martin Repair Drawing LCC7622-369, Revision March
30, 1995; specifies contacting Lockheed for appropriate action:
Before further flight, repair the cracking in accordance with a
method approved by the Manager, Atlanta 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.

Compliance Times for Inspections

(k) Do the inspections required by paragraph (g) of this AD at
the applicable time specified in table 1 of this AD.

Table 1--Compliance Times for Inspections
----------------------------------------------------------------------------------------------------------------

----------------------------------------------------------------------------------------------------------------
Airplane models and zones Compliance time Repetitive interval
(whichever occurs later) (not to exceed)
----------------------------------------------------------------------------------------------------------------
L-1011-385-1 having accumulated Within 7,000 flight cycles Within 1,000 flight 1,100 flight cycles.
fewer than 7,000 flight cycles or 10 years after the cycles after the
after the accomplishment of accomplishment of effective date of this
Lockheed Martin Service Bulletin Lockheed Martin Service AD.
093-57-184, 093-57-196, or 093-57- Bulletin 093-57-184, 093-
215; as of the effective date of 57-196, or 093-57-215,
this AD; Zones 1A through 1E (Non- whichever occurs first.
destructive Inspection (NDI)).

[[Page 58419]]

L-1011-385-1 having accumulated Within 7,000 flight cycles Within 90 flight cycles 90 flight cycles.
fewer than 7,000 flight cycles or 10 years after the or 30 days after the
after the accomplishment of accomplishment of effective date of this
Lockheed Martin Service Bulletin Lockheed Martin Service AD, whichever occurs
093-57-184, 093-57-196, or 093-57- Bulletin 093-57-184, 093- later.
215; as of the effective date of 57-196, or 093-57-215,
this AD; Zone 1F (Detailed whichever occurs first.
Inspection).
L-1011-385-1 having accumulated Within 1,000 flight cycles N/A...................... 1,100 flight cycles.
7,000 flight cycles or more or 12 months after the
flight cycles after the effective date of this
accomplishment of Lockheed Martin AD, whichever occurs
Service Bulletin 093-57-184, 093- first.
57-196, or 093-57-215; as of the
effective date of this AD; Zones
1A through 1E (NDI).
L-1011-385-1 having accumulated Within 90 flight cycles Within 30 days after the 90 flight cycles.
7,000 flight cycles or more after after the effective date effective date of this
the accomplishment of Lockheed of this AD. AD.
Martin Service Bulletin 093-57-
184, 093-57-196, or 093-57-215;
as of the effective date of this
AD; Zone 1F (Detailed Inspection).
L-1011-385-1-14 having accumulated Within 6,900 flight cycles Within 1,000 flight 900 flight cycles.
fewer than 6,900 flight cycles or 10 years after the cycles after the
after the accomplishment of accomplishment of effective date of this
Lockheed Martin Service Bulletin Lockheed Martin Service AD.
093-57-184, 093-57-196, or 093-57- Bulletin 093-57-184, 093-
215; as of the effective date of 57-196, or 093-57-215,
this AD; Zones 1A through 1E whichever occurs first.
(NDI).
L-1011-385-1-14 having accumulated Within 6,900 flight cycles Within 90 flight cycles 90 flight cycles.
fewer than 6,900 flight cycles or 10 years after the or 30 days after the
after the accomplishment of accomplishment of effective date of this
Lockheed Martin Service Bulletin Lockheed Martin Service AD, whichever occurs
093-57-184, 093-57-196, or 093-57- Bulletin 093-57-184, 093- later.
215; as of the effective date of 57-196, or 093-57-215,
this AD; Zone 1F (Detailed whichever occurs first.
Inspection).
L-1011-385-1-14 having accumulated Within 1,000 flight cycles N/A...................... 900 flight cycles.
6,900 or more flight cycles after or 12 months after the
the accomplishment of Lockheed effective date of this
Martin Service Bulletin 093-57- AD, whichever occurs
184, 093-57-196, or 093-57-215; first.
as of the effective date of this
AD; Zones 1A through 1E (NDI).
L-1011-385-1-14 having accumulated Within 90 flight cycles Within 30 days after the 90 flight cycles.
6,900 or more flight cycles after after the effective date effective date of this
the accomplishment of Lockheed of this AD. AD.
Martin Service Bulletin 093-57-
184, 093-57-196, or 093-57-215;
as of the effective date of this
AD; Zone 1F (Detailed Inspection).
L-1011-385-1-15 having accumulated Within 5,600 flight cycles Within 1,000 flight 500 flight cycles.
fewer than 5,600 flight cycles or 10 years after the cycles after the
after the accomplishment of accomplishment of effective date of this
Lockheed Martin Service Bulletin Lockheed Martin Service AD.
093-57-184, 093-57-196, or 093-57- Bulletin 093-57-184, 093-
215; as of the effective date of 57-196, or 093-57-215,
this AD; Zones 1A through 1E whichever occurs first.
(NDI).
L-1011-385-1-15 having accumulated Within 5,600 flight cycles Within 60 flight cycles 60 flight cycles.
fewer than 5,600 flight cycles or 10 years after the or 30 days after the
after the accomplishment of accomplishment of effective date of this
Lockheed Martin Service Bulletin Lockheed Martin Service AD, whichever occurs
093-57-184, 093-57-196, or 093-57- Bulletin 093-57-184, 093- later.
215; as of the effective date of 57-196, or 093-57-215,
this AD; Zone 1F (Detailed whichever occurs first.
Inspection).

[[Page 58420]]

L-1011-385-1-15 having accumulated Within 1,000 flight cycles N/A...................... 500 flight cycles.
5,600 or more flight cycles after or 12 months after the
the accomplishment of Lockheed effective date of this
Martin Service Bulletin 093-57- AD, whichever occurs
184, 093-57-196, or 093-57-215; first.
as of the effective date of this
AD; Zones 1A through 1E (NDI).
L-1011-385-1-15 having accumulated Within 60 flight cycles Within 30 days after the 60 flight cycles.
5,600 or more flight cycles after after the effective date effective date of this
the accomplishment of Lockheed of this AD. AD.
Martin Service Bulletin 093-57-
184, 093-57-196, or 093-57-215;
as of the effective date of this
AD; Zone 1F (Detailed Inspection).
L-1011-385-3 having accumulated Within 8,400 flight cycles Within 1,000 flight 1,200 flight cycles.
fewer than 8,400 flight cycles or 10 years after the cycles after the
after the accomplishment of accomplishment of effective date of this
Lockheed Martin Service Bulletin Lockheed Martin Service AD.
093-57-184, 093-57-196, or 093-57- Bulletin 093-57-184, 093-
215; as of the effective date of 57-196, or 093-57-215,
this AD; Zones 1A through 1E whichever occurs first.
(NDI).
L-1011-385-3 having accumulated Within 90 flight cycles or Within 85 flight cycles 85 flight cycles.
fewer than 8,400 flight cycles 30 days after the or 30 days after the
after the accomplishment of effective date of this effective date of this
Lockheed Martin Service Bulletin AD, whichever occurs AD, whichever occurs
093-57-184, 093-57-196, or 093-57- later. later.
215; as of the effective date of
this AD; Zone 1F (Detailed
Inspection).
L-1011-385-3 having accumulated Within 1,000 flight cycles N/A...................... 1,200 flight cycles.
8,400 or more flight cycles after or 12 months after the
the accomplishment of Lockheed effective date of this
Martin Service Bulletin 093-57- AD, whichever occurs
184, 093-57-196, or 093-57-215; first.
as of the effective date of this
AD; Zones 1A through 1E (NDI).
L-1011-385-3 having accumulated Within 85 flight cycles Within 30 days after the 85 flight cycles.
8,400 or more flight cycles after after the effective date effective date of this
the accomplishment of Lockheed of this AD. AD.
Martin Service Bulletin 093-57-
184, 093-57-196, or 093-57-215;
as of the effective date of this
AD; Zone 1F (Detailed Inspection).
----------------------------------------------------------------------------------------------------------------

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. In accordance with 14 CFR 39.19, send your request
to your principal inspector or local Flight Standards District
Office, as appropriate. If sending information directly to the
manager of the ACO, send it to the attention of the person
identified in the Related Information section of this AD.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.

Related Information

(m) For more information about this AD, contact Carl Gray,
Aerospace Engineer, Airframe Branch, ACE-117A, FAA, Atlanta ACO,
1701 Columbia Avenue, College Park, Georgia 30337; phone: 404-474-
5554; fax: 404-474-5606; e-mail: Carl.W.Gray@faa.gov.

Issued in Renton, Washington, on September 14, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.

[FR Doc. 2011-24270 Filed 9-20-11; 8:45 am]
BILLING CODE 4910-13-P

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