Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model L-1011 Series Airplanes, 48049-48053 [2011-19968]

Download as PDF Federal Register / Vol. 76, No. 152 / Monday, August 8, 2011 / Proposed Rules For the reasons described above, this new AD requires repetitive tests and inspections of the air brake control system torsion tube and applicable corrective actions, depending on findings. emcdonald on DSK2BSOYB1PROD with PROPOSALS Actions and Compliance (f) Unless already done, do the following actions: (1) Within the next 6 months after the effective date of this AD, remove, test, and inspect the air brake control system torsion tube for corrosion damage following Diamond Aircraft Industries GmbH Work Instruction WI–MSB 36–105, dated April 21, 2011, as specified in Diamond Aircraft Industries GmbH Service Bulletin No. MSB 36–105/1, dated May 2, 2011. (2) If corrosion damage is found during the inspection required in paragraph (f)(1) of this AD or during any repetitive inspection required in paragraphs (f)(2) and (f)(3) of this AD, before further flight after the inspection in which corrosion damage is found, replace the affected torsion tube with a serviceable part. Before installation, apply an anticorrosive agent to the inside of the torsion tube. Do these required actions following Diamond Aircraft Industries GmbH Work Instruction WI–MSB 36–105, dated April 21, 2011. After replacement, repetitively thereafter at intervals not to exceed 60 months, remove, test, and inspect the newly installed air brake control system torsion tube for corrosion damage following the procedures specified in paragraph (f)(1) of this AD. (3) If no corrosion damage is found during the inspection required in paragraph (f)(1) of this AD or during any repetitive inspection required in paragraphs (f)(2) and (f)(3) of this AD, before reinstalling the torsion tube, apply an anticorrosive agent to the inside of the torsion tube. Do these required actions following Diamond Aircraft Industries GmbH Work Instruction WI–MSB 36–105, dated April 21, 2011. Repetitively thereafter at intervals not to exceed 60 months, remove, test, and inspect the air brake control system torsion tube for corrosion damage following the procedures specified in paragraph (f)(1) of this AD. (4) As of the effective date of this AD, do not install an air brake control system torsion tube on an affected airplane unless it has been inspected following the procedures specified in paragraph (f)(1) of this AD, is found to be corrosion free, and an anticorrosive agent has been applied to the inside of the tube as specified in Diamond Aircraft Industries GmbH Work Instruction WI–MSB 36–105, dated April 21, 2011. Note 1: Credit will be given for the initial test and inspection required in paragraph (f)(1) of this AD and the corrective actions required in paragraphs (f)(2) and (f)(3) of this AD if already done before the effective date of this AD following Diamond Aircraft Industries GmbH Service Bulletin No. MSB 36–105, original issue. FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows: No differences. VerDate Mar<15>2010 18:42 Aug 05, 2011 Jkt 223001 Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, 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: Jim Rutherford, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4165; fax: (816) 329– 4090; e-mail: jim.rutherford@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, a Federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. Related Information (h) Refer to MCAI European Aviation Safety Agency (EASA) AD No. 2011–0110, dated June 16, 2011; Diamond Aircraft Industries GmbH Service Bulletin No. MSB 36–105/1, dated May 2, 2011; and Diamond Aircraft Industries GmbH Work Instruction WI–MSB 36–105, dated April 21, 2011, for related information. For service information related to this AD, contact Diamond Aircraft Industries GmbH, N.A. Otto-Stra+e 5, A–2700 Wiener Neustadt, Austria, telephone: +43 2622 26700; fax: +43 2622 26780; e-mail: office@diamond-air.at; Internet: https:// www.diamond-air.at. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 48049 Issued in Kansas City, Missouri, on July 26, 2011. Steven W. Thompson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–20038 Filed 8–5–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0723; Directorate Identifier 2010–NM–080–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 supersede an existing airworthiness directive (AD) that applies to Model L–1011–385–1, L– 1011–385–1–14, and L–1011–385–1–15 airplanes. The existing AD currently requires implementation of a Supplemental Inspection Document (SID) program of structural inspections to detect fatigue cracking, and repair, if necessary, to ensure continued airworthiness of these airplanes as they approach the manufacturer’s original fatigue design life goal. Since we issued that AD, an evaluation by the manufacturer of usage and flight data provided additional information about certain Structurally Significant Details (SSDs) where fatigue damage is likely to occur. This proposed AD would add airplanes to the applicability, change certain inspection thresholds, add three new SSDs, and remove an SSD that has been addressed by a different AD. We are proposing this AD to prevent fatigue cracking that could compromise the structural integrity of these airplanes. DATES: We must receive comments on this proposed AD by September 22, 2011. SUMMARY: 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. ADDRESSES: E:\FR\FM\08AUP1.SGM 08AUP1 48050 Federal Register / Vol. 76, No. 152 / Monday, August 8, 2011 / Proposed Rules • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this 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; phone: 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. emcdonald on DSK2BSOYB1PROD with PROPOSALS 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–2011–0723; Directorate Identifier 2010–NM–080–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. VerDate Mar<15>2010 18:42 Aug 05, 2011 Jkt 223001 Discussion On December 5, 1995, we issued AD 95–20–04 R1, Amendment 39–9454 (60 FR 63414, December 11, 1995), for all Lockheed Model L–1011–385–1 series airplanes. That AD requires implementation of a Supplemental Inspection Document (SID) program of structural inspections to detect fatigue cracking, and repair, if necessary, to ensure continued airworthiness of these airplanes as they approach the manufacturer’s original fatigue design life goal. That AD resulted from a structural re-evaluation by the manufacturer that identified certain structural details where fatigue damage is likely to occur. We issued that AD to prevent fatigue cracking that could compromise the structural integrity of these airplanes. describes procedures for supplemental inspections of SSDs for all Model L– 1011 series airplanes. The Lockheed Document identifies SSDs in fuselage, stabilizer, and wing-critical areas. The Lockheed Document changes certain inspection thresholds, adds Model L– 1011–353–3 airplanes to the effectivity, adds SSDs 57–3–10, 57–3–11, 57–4–1C, and removes SSD 53–4–3. The Lockheed Document also specifies that operators submit the results of these inspections to Lockheed. FAA’s Determination We are proposing 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 the same type design. Actions Since Existing AD Was Issued Proposed AD Requirements Since we issued AD 95–20–04 R1, an evaluation by the manufacturer of usage and flight data provided additional information about certain SSDs where fatigue damage is likely to occur. Therefore, this proposed AD changes certain inspection thresholds and intervals for Model L–1011–385–1, L– 1011–385–1–14, and L–1011–385–1–15 airplanes, adds three new SSDs, and removes an SSD that has been addressed by AD 99–08–20, amendment 39–11128 (64 FR 18324, April 14, 1999). AD 99– 08–20 requires repetitive inspections to detect cracking of the bulkhead web and cap at fuselage station 1363, and repair if necessary. When we issued AD 95–20–04 R1, Model L–1011–385–3 airplanes were not included in the applicability. These long-range airplanes flew less frequently and were neither imminently approaching nor had exceeded the manufacturer’s original fatigue design life goal. In the NPRM for AD 95–20–04, Amendment 39–9382 (60 FR 51713, October 3, 1995) we stated that as these airplanes accumulated more hours timein-service, and as the critical area selection was developed and identified, we anticipated that these airplanes would be addressed in future rulemaking actions. We now have determined that further rulemaking is indeed necessary for these airplanes, and we have added them to the applicability of this proposed AD. This proposed AD would retain all requirements of AD 95–20–04 R1. This proposed AD would add Model L– 1011–385–3 airplanes to the applicability, change certain inspection thresholds and intervals for Model L– 1011–385–1, L–1011–385–1–14, and L– 1011–385–1–15 airplanes, add three new SSDs for Model L–1011–385–3 airplanes, and remove an SSD that has been addressed by a different AD action. This proposed AD would also require accomplishing the actions specified in the service information described previously. This proposed AD would also require sending the inspection results to the manufacturer. Relevant Service Information We reviewed Lockheed Document Number LG92ER0060, ‘‘L–1011–385 Series Supplemental Inspection Document,’’ revised April 2009 (hereafter referred to as ‘‘the Lockheed Document’’). The Lockheed Document PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 Change to Existing AD This proposed AD would retain all requirements of AD 95–20–04 R1. Since AD 95–20–04 R1 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this proposed AD, as listed in the following table: REVISED PARAGRAPH IDENTIFIERS Requirement in AD 95–20–04 Corresponding requirement in this proposed AD paragraph (a) paragraph (b) paragraph (c) paragraph (g) paragraph (n) paragraph (o) Costs of Compliance We estimate that this proposed AD affects 26 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: E:\FR\FM\08AUP1.SGM 08AUP1 Federal Register / Vol. 76, No. 152 / Monday, August 8, 2011 / Proposed Rules 48051 ESTIMATED COSTS Labor cost Incorporate SID into maintenance program [retained actions from existing AD]. Initial inspections [retained actions from existing AD]. Repetitive inspections [retained actions from existing AD]. Incorporate SID into maintenance program [new proposed action for Model L–1011–385–3 airplanes]. Initial inspections [new proposed action for Model L–1011–385–3 airplanes]. Repetitive inspections [new proposed action for Model L–1011–385–3 airplanes]. 550 work-hours × $85 per hour = $46,750. $0 $46,750 ............................. 26 $1,215,500. 245 work-hours × $85 per hour = $20,825. 0 $20,825 ............................. 26 $541,450. 52 work-hours × $85 per hour = $4,420 per inspection cycle. 1 work-hour × $85 = $85 .. 0 $4,420 per inspection cycle. 26 $114,920 per inspection cycle. 0 $85 .................................... 2 $170. 48 work-hours × $85 per hour = $4,080. 0 $4,080 ............................... 2 $8,160. 44 work-hours × $85 per hour = $3,740 per inspection cycle. 0 $3,740 per inspection cycle. 2 $7,480 per inspection cycle. emcdonald on DSK2BSOYB1PROD with PROPOSALS Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, VerDate Mar<15>2010 18:42 Aug 05, 2011 Jkt 223001 Parts cost Number of airplanes affected Action Cost per product (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 removing airworthiness directive (AD) 95–20–04 R1, Amendment 39–9454 (60 FR 63414, December 11, 1995), and adding the following new AD: Lockheed Martin Corporation/Lockheed Martin Aeronautics Company: Docket No. FAA–2011–0723; Directorate Identifier 2010–NM–080–AD. PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 Cost for U.S. operators Comments Due Date (a) The FAA must receive comments on this AD action by September 22, 2011. Affected ADs (b) This AD supersedes AD 95–20–04 R1, Amendment 39–9454. Applicability (c) All 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. Subject (d) Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 53, Fuselage. Unsafe Condition (e) This AD was prompted by an evaluation by the manufacturer of usage and flight data that provided additional information about certain Structurally Significant Details (SSDs) where fatigue damage is likely to occur. We are issuing this AD to prevent fatigue cracking that could compromise the structural integrity of these airplanes. Compliance (f) Comply with this AD within the compliance times specified, unless already done. Restatement of the Requirements of AD 95– 20–04 R1: Revision and Inspections (g) For Model L–1011–385–1, L–1011–385– 1–14, and L–1011–385–1–15 airplanes: Within 12 months after November 2, 1995 (the effective date of AD 95–20–04 R1), incorporate a revision into the maintenance inspection program which provides for inspection(s) of the structurally significant details (SSD) defined in Lockheed Document E:\FR\FM\08AUP1.SGM 08AUP1 48052 Federal Register / Vol. 76, No. 152 / Monday, August 8, 2011 / Proposed Rules emcdonald on DSK2BSOYB1PROD with PROPOSALS Number LG92ER0060, ‘‘L–1011–385 Series Supplemental Inspection Document,’’ revised January 1994. Doing the revision required by paragraph (h) of this AD terminates the requirement to revise the maintenance inspections program specified in this paragraph. Doing the inspections required by paragraph (i) of this AD terminates the corresponding inspection requirements of this paragraph. (1) The initial inspection for each SSD must be performed at the later of the times specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD. (i) Within one repeat interval measured from November 2, 1996 (12 months after November 2, 1995). (ii) Prior to the threshold specified in Lockheed Document Number LG92ER0060, ‘‘L–1011–385 Series Supplemental Inspection Document,’’ revised January 1994, for that SSD. (2) A 10 percent deviation from the repetitive interval specified in Lockheed Document Number LG92ER0060, ‘‘L–1011– 385 Series Supplemental Inspection Document,’’ revised January 1994, for that SSD is acceptable to allow for planning and scheduling time. (3) If Lockheed Document Number LG92ER0060, ‘‘L–1011–385 Series Supplemental Inspection Document,’’ revised January 1994, specifies that inspection of any SSD be performed at every ‘‘C’’ check, those inspections must be performed at intervals not to exceed 5,000 hours time-in-service or 2,500 flight cycles, whichever occurs earlier. (4) If Lockheed Document Number LG92ER0060, ‘‘L–1011–385 Series Supplemental Inspection Document,’’ revised January 1994, specifies either the initial inspection or the repetitive inspection intervals for any SSD in terms of flight hours or flight cycles, the inspection shall be performed prior to the earlier of the terms (whichever occurs first on the airplane: either accumulated number of flight hours, or accumulated number of flight cycles). (5) The non-destructive inspection techniques referenced in Appendix VI of Lockheed Document Number LG92ER0060, ‘‘L–1011–385 Series Supplemental Inspection Document,’’ revised January 1994, provide acceptable methods for accomplishing the inspections required by paragraph (g) of this AD. New Requirements of this AD: New Revision (h) For all airplanes: Within 12 months after the effective date of this AD, incorporate a revision into the maintenance inspection program which provides for inspection(s) of the SSDs defined in Lockheed Document Number LG92ER0060, ‘‘L–1011–385 Series Supplemental Inspection Document,’’ revised April 2009. Doing this revision terminates the requirement to revise the maintenance inspection program as specified in paragraph (g) of this AD. Threshold and Intervals (i) For all airplanes: Do all applicable inspections specified in Lockheed Document Number LG92ER0060, ‘‘L–1011–385 Series Supplemental Inspection Document,’’ revised April 2009. Do the initial inspection or next VerDate Mar<15>2010 18:42 Aug 05, 2011 Jkt 223001 repetitive inspection at the applicable time specified in paragraphs (i)(1) and (i)(2) of this AD, except as provided by paragraphs (j), (k), and (l) of this AD. Repeat the inspections thereafter in accordance with the intervals and actions specified in Lockheed Document Number LG92ER0060, ‘‘L–1011–385 Series Supplemental Inspection Document,’’ revised April 2009, except as provided by paragraphs (j), (k), and (l) of this AD. The nondestructive inspection techniques referenced in Lockheed Document Number LG92ER0060, ‘‘L–1011–385 Series Supplemental Inspection Document,’’ revised April 2009, provide acceptable methods for accomplishing the inspections required by this AD. Doing the inspections required by this paragraph of this AD terminates the corresponding inspection requirements of paragraph (g) of this AD. (1) For Model L–1011–385–3 airplanes; and for Model L–1011–385–1, L–1011–385– 1–14, and L–1011–385–1–15 airplanes on which the initial inspection required by paragraph (g) of this AD has not been accomplished before the effective date of this AD: Do the initial inspection at the later of the times specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD. (i) Within one repeat interval measured from a date 12 months after the effective date of this AD. (ii) Before the threshold specified for that SSD in Lockheed Document Number LG92ER0060, ‘‘L–1011–385 Series Supplemental Inspection Document,’’ revised April 2009. (2) For Model L–1011–385–1, L–1011–385– 1–14, and L–1011–385–1–15 airplanes on which the initial inspection required by paragraph (g) of this AD has been accomplished before the effective date of this AD: Do the next repetitive inspection at the earlier of the times specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD. (i) Within the next repetitive inspection interval specified in Lockheed Document Number LG92ER0060, ‘‘L–1011–385 Series Supplemental Inspection Document,’’ revised January 1994, for that SSD. (ii) Within one repeat interval measured from a date 12 months after the effective date of this AD; or within the next repetitive interval specified in Lockheed Document Number LG92ER0060, ‘‘L–1011–385 Series Supplemental Inspection Document,’’ revised April 2009, for that SSD; whichever occurs later. Exceptions to Threshold and Intervals (j) For all airplanes: A 10 percent deviation from the repetitive interval specified in Lockheed Document Number LG92ER0060, ‘‘L–1011–385 Series Supplemental Inspection Document,’’ revised April 2009, for that SSD is acceptable to allow for planning and scheduling time. (k) For all airplanes: Where Lockheed Document Number LG92ER0060, ‘‘L–1011– 385 Series Supplemental Inspection Document,’’ revised April 2009, specifies that inspection of any SSD be performed at every ‘‘C’’ check, those inspections must be performed at intervals not to exceed 5,000 flight hours or 2,500 flight cycles, whichever occurs earlier. PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 (l) For all airplanes: Where Lockheed Document Number LG92ER0060, ‘‘L–1011– 385 Series Supplemental Inspection Document,’’ revised April 2009, specifies either the initial inspection or the repetitive inspection intervals for any SSD in terms of flight hours or flight cycles, the inspection must be performed prior to the earlier of the terms (whichever occurs first on the airplane: either accumulated number of flight hours, or accumulated number of flight cycles). Exception to Inspection Procedure (m) For all airplanes: There should be no repair or modification work done in the inspection area before the initial inspections required by paragraph (i) of this AD; any changes in the inspection area could affect the inspection procedure. Repair (n) For all airplanes: If any cracking is found in any SSD during any inspection required by this AD, prior to further flight, repair in accordance with paragraph (n)(1), (n)(2), or (n)(3) of this AD: (1) In accordance with the applicable service bulletin referenced in Lockheed Document Number LG92ER0060, ‘‘L–1011– 385 Series Supplemental Inspection Document,’’ revised January 1994; or revised April 2009. After doing the revision required by paragraph (h) of this AD, repair in accordance with the applicable service bulletin referenced in Lockheed Document Number LG92ER0060, ‘‘L–1011–385 Series Supplemental Inspection Document,’’ revised April 2009. (2) In accordance with the Structural Repair Manual or in accordance with Lockheed L–1011 Structural Repair Manual, Revision 80, dated December 15, 2009. As of the effective date of this AD, use Lockheed L–1011 Structural Repair Manual, Revision 80, dated December 15, 2009. (3) In accordance with a method approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA. Reporting (o) For all airplanes: At the later of the times specified in paragraphs (o)(1) and (o)(2) of this AD, submit a report of the results (positive or negative) of the inspection(s) to Lockheed in accordance with Section V., Data Reporting System (DRS), of the applicable Lockheed Document specified in paragraph (o)(1) of this AD. Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120–0056. (1) Within 30 days after returning the airplane to service, subsequent to accomplishment of the inspection(s) specified in Lockheed Document Number LG92ER0060, ‘‘L–1011–385 Series Supplemental Inspection Document,’’ revised January 1994; or Lockheed Document Number LG92ER0060, ‘‘L–1011–385 Series Supplemental Inspection Document,’’ revised April 2009. (2) Within 30 days after the effective date of this AD. E:\FR\FM\08AUP1.SGM 08AUP1 Federal Register / Vol. 76, No. 152 / Monday, August 8, 2011 / Proposed Rules Paperwork Reduction Act Burden Statement (p) A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. Alternative Methods of Compliance (AMOCs) (q)(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. emcdonald on DSK2BSOYB1PROD with PROPOSALS Related Information (r) For more information about this AD, 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. (s) For service information identified in this 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; phone: 770–494– 5444; fax: 770–494–5445; e-mail: ams.portal@lmco.com; Internet https:// www.lockheedmartin.com/ams/tools/ TechPubs.htm. 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. Issued in Renton, Washington, on July 29, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–19968 Filed 8–5–11; 8:45 am] BILLING CODE 4910–13–P VerDate Mar<15>2010 18:42 Aug 05, 2011 Jkt 223001 CONSUMER PRODUCT SAFETY COMMISSION [CPSC Docket No. CPSC–2011–0053] Consumer Registration of Durable Infant or Toddler Products Consumer Product Safety Commission. ACTION: Notice of proposed rulemaking. AGENCY: In accordance with section 104(d) of the Consumer Product Safety Improvement Act of 2008 (‘‘CPSIA’’) the Consumer Product Safety Commission (‘‘Commission,’’ ‘‘CPSC,’’ or ‘‘we’’) issued a final consumer product safety rule requiring manufacturers of durable infant or toddler products to establish a consumer registration program. The Commission is proposing an amendment to clarify and correct some of the requirements of the rule. DATES: Written comments must be received by October 24, 2011. ADDRESSES: You may submit comments, identified by Docket No. CPSC–2011– 0053, by any of the following methods: SUMMARY: Electronic Submissions Submit electronic comments in the following way: Federal eRulemaking Portal: https:// www.regulations.gov. Follow the instructions for submitting comments. To ensure timely processing of comments, the Commission is no longer accepting comments submitted by electronic mail (e-mail), except through https://www.regulations.gov. Written Submissions Submit written submissions in the following way: Mail/Hand delivery/Courier (for paper, disk, or CD–ROM submissions), preferably in five copies, to: Office of the Secretary, Consumer Product Safety Commission, Room 820, 4330 East West Highway, Bethesda, MD 20814; telephone (301) 504–7923. Instructions: All submissions received must include the agency name and docket number for this rulemaking. All comments received may be posted without change, including any personal identifiers, contact information, or other personal information provided to https:// www.regulations.gov. Do not submit confidential business information, trade secret information, or other sensitive or protected information electronically. Such information should be submitted in writing. Docket: For access to the docket to read background documents or Frm 00009 Fmt 4702 comments received go to https:// www.regulations.gov. FOR FURTHER INFORMATION CONTACT: 16 CFR Part 1130 PO 00000 48053 Sfmt 4702 Celestine T. Kiss, Project Manager, Division of Human Factors, Directorate for Engineering Sciences, Consumer Product Safety Commission, 4330 East West Highway, Bethesda, MD 20814; telephone (301) 504–7739; ckiss@cpsc.gov. SUPPLEMENTARY INFORMATION: A. Background On December 29, 2009, we published a final rule requiring manufacturers of durable infant or toddler products to: (1) Provide with each product a postagepaid consumer registration form; (2) keep records of consumers who register such products with the manufacturer; and (3) permanently place the manufacturer’s name and contact information, model name and number, and the date of manufacture on each such product. 74 FR 68668. The rule specified formatting and text requirements for the registration forms. Subsequently, we published a correction notice on February 22, 2010. 75 FR 7550. Since December 29, 2010, registration forms have been required for all durable infant or toddler products covered by the rule. Some manufacturers and testing laboratories have brought to our attention the need to clarify or correct certain aspects of the rule. We are proposing this amendment for that purpose. We note that, although manufacturers of durable infant or toddler products must comply with the registration requirements, they are not required to have a third party testing laboratory ‘‘test’’ their product’s compliance with the registration requirements. B. Proposed Clarifications and Corrections 1. Simplifying the Provisions for the Format and Text of Registration Forms (Proposed § 1130.6) The rule specifies requirements for the format of registration forms in § 1130.6 and requirements for the text of registration forms in § 1130.7. Given the geometry of the registration forms, which have four surfaces (front, back, top, and bottom), we believe that it is confusing to explain the requirements in this way. Therefore, the proposed amendment would eliminate this framework, essentially collapsing the requirements from §§ 1130.6 and 1130.7 into one section and clarifying them. Proposed § 1130.6 would describe the registration form more clearly, moving logically from the front top of the form E:\FR\FM\08AUP1.SGM 08AUP1

Agencies

[Federal Register Volume 76, Number 152 (Monday, August 8, 2011)]
[Proposed Rules]
[Pages 48049-48053]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-19968]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0723; Directorate Identifier 2010-NM-080-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 supersede an existing airworthiness directive 
(AD) that applies to Model L-1011-385-1, L-1011-385-1-14, and L-1011-
385-1-15 airplanes. The existing AD currently requires implementation 
of a Supplemental Inspection Document (SID) program of structural 
inspections to detect fatigue cracking, and repair, if necessary, to 
ensure continued airworthiness of these airplanes as they approach the 
manufacturer's original fatigue design life goal. Since we issued that 
AD, an evaluation by the manufacturer of usage and flight data provided 
additional information about certain Structurally Significant Details 
(SSDs) where fatigue damage is likely to occur. This proposed AD would 
add airplanes to the applicability, change certain inspection 
thresholds, add three new SSDs, and remove an SSD that has been 
addressed by a different AD. We are proposing this AD to prevent 
fatigue cracking that could compromise the structural integrity of 
these airplanes.

DATES: We must receive comments on this proposed AD by September 22, 
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.

[[Page 48050]]

     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this 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; phone: 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-2011-0723; 
Directorate Identifier 2010-NM-080-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

    On December 5, 1995, we issued AD 95-20-04 R1, Amendment 39-9454 
(60 FR 63414, December 11, 1995), for all Lockheed Model L-1011-385-1 
series airplanes. That AD requires implementation of a Supplemental 
Inspection Document (SID) program of structural inspections to detect 
fatigue cracking, and repair, if necessary, to ensure continued 
airworthiness of these airplanes as they approach the manufacturer's 
original fatigue design life goal. That AD resulted from a structural 
re-evaluation by the manufacturer that identified certain structural 
details where fatigue damage is likely to occur. We issued that AD to 
prevent fatigue cracking that could compromise the structural integrity 
of these airplanes.

Actions Since Existing AD Was Issued

    Since we issued AD 95-20-04 R1, an evaluation by the manufacturer 
of usage and flight data provided additional information about certain 
SSDs where fatigue damage is likely to occur. Therefore, this proposed 
AD changes certain inspection thresholds and intervals for Model L-
1011-385-1, L-1011-385-1-14, and L-1011-385-1-15 airplanes, adds three 
new SSDs, and removes an SSD that has been addressed by AD 99-08-20, 
amendment 39-11128 (64 FR 18324, April 14, 1999). AD 99-08-20 requires 
repetitive inspections to detect cracking of the bulkhead web and cap 
at fuselage station 1363, and repair if necessary.
    When we issued AD 95-20-04 R1, Model L-1011-385-3 airplanes were 
not included in the applicability. These long-range airplanes flew less 
frequently and were neither imminently approaching nor had exceeded the 
manufacturer's original fatigue design life goal. In the NPRM for AD 
95-20-04, Amendment 39-9382 (60 FR 51713, October 3, 1995) we stated 
that as these airplanes accumulated more hours time-in-service, and as 
the critical area selection was developed and identified, we 
anticipated that these airplanes would be addressed in future 
rulemaking actions. We now have determined that further rulemaking is 
indeed necessary for these airplanes, and we have added them to the 
applicability of this proposed AD.

Relevant Service Information

    We reviewed Lockheed Document Number LG92ER0060, ``L-1011-385 
Series Supplemental Inspection Document,'' revised April 2009 
(hereafter referred to as ``the Lockheed Document''). The Lockheed 
Document describes procedures for supplemental inspections of SSDs for 
all Model L-1011 series airplanes. The Lockheed Document identifies 
SSDs in fuselage, stabilizer, and wing-critical areas. The Lockheed 
Document changes certain inspection thresholds, adds Model L-1011-353-3 
airplanes to the effectivity, adds SSDs 57-3-10, 57-3-11, 57-4-1C, and 
removes SSD 53-4-3. The Lockheed Document also specifies that operators 
submit the results of these inspections to Lockheed.

FAA's Determination

    We are proposing 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 the same type design.

Proposed AD Requirements

    This proposed AD would retain all requirements of AD 95-20-04 R1. 
This proposed AD would add Model L-1011-385-3 airplanes to the 
applicability, change certain inspection thresholds and intervals for 
Model L-1011-385-1, L-1011-385-1-14, and L-1011-385-1-15 airplanes, add 
three new SSDs for Model L-1011-385-3 airplanes, and remove an SSD that 
has been addressed by a different AD action. This proposed AD would 
also require accomplishing the actions specified in the service 
information described previously. This proposed AD would also require 
sending the inspection results to the manufacturer.

Change to Existing AD

    This proposed AD would retain all requirements of AD 95-20-04 R1. 
Since AD 95-20-04 R1 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD, as listed in 
the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                      Corresponding requirement in this
     Requirement in AD 95-20-04                  proposed AD
------------------------------------------------------------------------
             paragraph (a)                        paragraph (g)
             paragraph (b)                        paragraph (n)
             paragraph (c)                        paragraph (o)
------------------------------------------------------------------------

Costs of Compliance

    We estimate that this proposed AD affects 26 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

[[Page 48051]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Number of
            Action                  Labor cost      Parts cost   Cost per product   airplanes     Cost for U.S.
                                                                                     affected       operators
----------------------------------------------------------------------------------------------------------------
Incorporate SID into            550 work-hours x            $0  $46,750..........           26  $1,215,500.
 maintenance program [retained   $85 per hour =
 actions from existing AD].      $46,750.
Initial inspections [retained   245 work-hours x             0  $20,825..........           26  $541,450.
 actions from existing AD].      $85 per hour =
                                 $20,825.
Repetitive inspections          52 work-hours x              0  $4,420 per                  26  $114,920 per
 [retained actions from          $85 per hour =                  inspection cycle.               inspection
 existing AD].                   $4,420 per                                                      cycle.
                                 inspection cycle.
Incorporate SID into            1 work-hour x $85            0  $85..............            2  $170.
 maintenance program [new        = $85.
 proposed action for Model L-
 1011-385-3 airplanes].
Initial inspections [new        48 work-hours x              0  $4,080...........            2  $8,160.
 proposed action for Model L-    $85 per hour =
 1011-385-3 airplanes].          $4,080.
Repetitive inspections [new     44 work-hours x              0  $3,740 per                   2  $7,480 per
 proposed action for Model L-    $85 per hour =                  inspection cycle.               inspection
 1011-385-3 airplanes].          $3,740 per                                                      cycle.
                                 inspection cycle.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

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

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (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 removing airworthiness directive 
(AD) 95-20-04 R1, Amendment 39-9454 (60 FR 63414, December 11, 1995), 
and adding the following new AD:

Lockheed Martin Corporation/Lockheed Martin Aeronautics Company: 
Docket No. FAA-2011-0723; Directorate Identifier 2010-NM-080-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by September 
22, 2011.

Affected ADs

    (b) This AD supersedes AD 95-20-04 R1, Amendment 39-9454.

Applicability

    (c) All 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.

Subject

    (d) Joint Aircraft System Component (JASC)/Air Transport 
Association (ATA) of America Code 53, Fuselage.

Unsafe Condition

    (e) This AD was prompted by an evaluation by the manufacturer of 
usage and flight data that provided additional information about 
certain Structurally Significant Details (SSDs) where fatigue damage 
is likely to occur. We are issuing this AD to prevent fatigue 
cracking that could compromise the structural integrity of these 
airplanes.

Compliance

    (f) Comply with this AD within the compliance times specified, 
unless already done.

Restatement of the Requirements of AD 95-20-04 R1: Revision and 
Inspections

    (g) For Model L-1011-385-1, L-1011-385-1-14, and L-1011-385-1-15 
airplanes: Within 12 months after November 2, 1995 (the effective 
date of AD 95-20-04 R1), incorporate a revision into the maintenance 
inspection program which provides for inspection(s) of the 
structurally significant details (SSD) defined in Lockheed Document

[[Page 48052]]

Number LG92ER0060, ``L-1011-385 Series Supplemental Inspection 
Document,'' revised January 1994. Doing the revision required by 
paragraph (h) of this AD terminates the requirement to revise the 
maintenance inspections program specified in this paragraph. Doing 
the inspections required by paragraph (i) of this AD terminates the 
corresponding inspection requirements of this paragraph.
    (1) The initial inspection for each SSD must be performed at the 
later of the times specified in paragraph (g)(1)(i) or (g)(1)(ii) of 
this AD.
    (i) Within one repeat interval measured from November 2, 1996 
(12 months after November 2, 1995).
    (ii) Prior to the threshold specified in Lockheed Document 
Number LG92ER0060, ``L-1011-385 Series Supplemental Inspection 
Document,'' revised January 1994, for that SSD.
    (2) A 10 percent deviation from the repetitive interval 
specified in Lockheed Document Number LG92ER0060, ``L-1011-385 
Series Supplemental Inspection Document,'' revised January 1994, for 
that SSD is acceptable to allow for planning and scheduling time.
    (3) If Lockheed Document Number LG92ER0060, ``L-1011-385 Series 
Supplemental Inspection Document,'' revised January 1994, specifies 
that inspection of any SSD be performed at every ``C'' check, those 
inspections must be performed at intervals not to exceed 5,000 hours 
time-in-service or 2,500 flight cycles, whichever occurs earlier.
    (4) If Lockheed Document Number LG92ER0060, ``L-1011-385 Series 
Supplemental Inspection Document,'' revised January 1994, specifies 
either the initial inspection or the repetitive inspection intervals 
for any SSD in terms of flight hours or flight cycles, the 
inspection shall be performed prior to the earlier of the terms 
(whichever occurs first on the airplane: either accumulated number 
of flight hours, or accumulated number of flight cycles).
    (5) The non-destructive inspection techniques referenced in 
Appendix VI of Lockheed Document Number LG92ER0060, ``L-1011-385 
Series Supplemental Inspection Document,'' revised January 1994, 
provide acceptable methods for accomplishing the inspections 
required by paragraph (g) of this AD.

New Requirements of this AD: New Revision

    (h) For all airplanes: Within 12 months after the effective date 
of this AD, incorporate a revision into the maintenance inspection 
program which provides for inspection(s) of the SSDs defined in 
Lockheed Document Number LG92ER0060, ``L-1011-385 Series 
Supplemental Inspection Document,'' revised April 2009. Doing this 
revision terminates the requirement to revise the maintenance 
inspection program as specified in paragraph (g) of this AD.

Threshold and Intervals

    (i) For all airplanes: Do all applicable inspections specified 
in Lockheed Document Number LG92ER0060, ``L-1011-385 Series 
Supplemental Inspection Document,'' revised April 2009. Do the 
initial inspection or next repetitive inspection at the applicable 
time specified in paragraphs (i)(1) and (i)(2) of this AD, except as 
provided by paragraphs (j), (k), and (l) of this AD. Repeat the 
inspections thereafter in accordance with the intervals and actions 
specified in Lockheed Document Number LG92ER0060, ``L-1011-385 
Series Supplemental Inspection Document,'' revised April 2009, 
except as provided by paragraphs (j), (k), and (l) of this AD. The 
non-destructive inspection techniques referenced in Lockheed 
Document Number LG92ER0060, ``L-1011-385 Series Supplemental 
Inspection Document,'' revised April 2009, provide acceptable 
methods for accomplishing the inspections required by this AD. Doing 
the inspections required by this paragraph of this AD terminates the 
corresponding inspection requirements of paragraph (g) of this AD.
    (1) For Model L-1011-385-3 airplanes; and for Model L-1011-385-
1, L-1011-385-1-14, and L-1011-385-1-15 airplanes on which the 
initial inspection required by paragraph (g) of this AD has not been 
accomplished before the effective date of this AD: Do the initial 
inspection at the later of the times specified in paragraphs 
(i)(1)(i) and (i)(1)(ii) of this AD.
    (i) Within one repeat interval measured from a date 12 months 
after the effective date of this AD.
    (ii) Before the threshold specified for that SSD in Lockheed 
Document Number LG92ER0060, ``L-1011-385 Series Supplemental 
Inspection Document,'' revised April 2009.
    (2) For Model L-1011-385-1, L-1011-385-1-14, and L-1011-385-1-15 
airplanes on which the initial inspection required by paragraph (g) 
of this AD has been accomplished before the effective date of this 
AD: Do the next repetitive inspection at the earlier of the times 
specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD.
    (i) Within the next repetitive inspection interval specified in 
Lockheed Document Number LG92ER0060, ``L-1011-385 Series 
Supplemental Inspection Document,'' revised January 1994, for that 
SSD.
    (ii) Within one repeat interval measured from a date 12 months 
after the effective date of this AD; or within the next repetitive 
interval specified in Lockheed Document Number LG92ER0060, ``L-1011-
385 Series Supplemental Inspection Document,'' revised April 2009, 
for that SSD; whichever occurs later.

Exceptions to Threshold and Intervals

    (j) For all airplanes: A 10 percent deviation from the 
repetitive interval specified in Lockheed Document Number 
LG92ER0060, ``L-1011-385 Series Supplemental Inspection Document,'' 
revised April 2009, for that SSD is acceptable to allow for planning 
and scheduling time.
    (k) For all airplanes: Where Lockheed Document Number 
LG92ER0060, ``L-1011-385 Series Supplemental Inspection Document,'' 
revised April 2009, specifies that inspection of any SSD be 
performed at every ``C'' check, those inspections must be performed 
at intervals not to exceed 5,000 flight hours or 2,500 flight 
cycles, whichever occurs earlier.
    (l) For all airplanes: Where Lockheed Document Number 
LG92ER0060, ``L-1011-385 Series Supplemental Inspection Document,'' 
revised April 2009, specifies either the initial inspection or the 
repetitive inspection intervals for any SSD in terms of flight hours 
or flight cycles, the inspection must be performed prior to the 
earlier of the terms (whichever occurs first on the airplane: either 
accumulated number of flight hours, or accumulated number of flight 
cycles).

Exception to Inspection Procedure

    (m) For all airplanes: There should be no repair or modification 
work done in the inspection area before the initial inspections 
required by paragraph (i) of this AD; any changes in the inspection 
area could affect the inspection procedure.

Repair

    (n) For all airplanes: If any cracking is found in any SSD 
during any inspection required by this AD, prior to further flight, 
repair in accordance with paragraph (n)(1), (n)(2), or (n)(3) of 
this AD:
    (1) In accordance with the applicable service bulletin 
referenced in Lockheed Document Number LG92ER0060, ``L-1011-385 
Series Supplemental Inspection Document,'' revised January 1994; or 
revised April 2009. After doing the revision required by paragraph 
(h) of this AD, repair in accordance with the applicable service 
bulletin referenced in Lockheed Document Number LG92ER0060, ``L-
1011-385 Series Supplemental Inspection Document,'' revised April 
2009.
    (2) In accordance with the Structural Repair Manual or in 
accordance with Lockheed L-1011 Structural Repair Manual, Revision 
80, dated December 15, 2009. As of the effective date of this AD, 
use Lockheed L-1011 Structural Repair Manual, Revision 80, dated 
December 15, 2009.
    (3) In accordance with a method approved by the Manager, Atlanta 
Aircraft Certification Office (ACO), FAA.

Reporting

    (o) For all airplanes: At the later of the times specified in 
paragraphs (o)(1) and (o)(2) of this AD, submit a report of the 
results (positive or negative) of the inspection(s) to Lockheed in 
accordance with Section V., Data Reporting System (DRS), of the 
applicable Lockheed Document specified in paragraph (o)(1) of this 
AD. Under the provisions of the Paperwork Reduction Act (44 U.S.C. 
3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements contained in this 
AD and has assigned OMB Control Number 2120-0056.
    (1) Within 30 days after returning the airplane to service, 
subsequent to accomplishment of the inspection(s) specified in 
Lockheed Document Number LG92ER0060, ``L-1011-385 Series 
Supplemental Inspection Document,'' revised January 1994; or 
Lockheed Document Number LG92ER0060, ``L-1011-385 Series 
Supplemental Inspection Document,'' revised April 2009.
    (2) Within 30 days after the effective date of this AD.

[[Page 48053]]

Paperwork Reduction Act Burden Statement

    (p) A federal agency may not conduct or sponsor, and a person is 
not required to respond to, nor shall a person be subject to a 
penalty for failure to comply with a collection of information 
subject to the requirements of the Paperwork Reduction Act unless 
that collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 5 minutes per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

Alternative Methods of Compliance (AMOCs)

    (q)(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

    (r) For more information about this AD, 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.
    (s) For service information identified in this 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; phone: 770-494-5444; fax: 770-494-
5445; e-mail: ams.portal@lmco.com; Internet https://www.lockheedmartin.com/ams/tools/TechPubs.htm. 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.

    Issued in Renton, Washington, on July 29, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-19968 Filed 8-5-11; 8:45 am]
BILLING CODE 4910-13-P