Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes, 20522-20526 [2012-8040]

Download as PDF 20522 Federal Register / Vol. 77, No. 66 / Thursday, April 5, 2012 / Rules and Regulations Bombardier Temporary Revision 5–2–59, dated November 25, 2010, to Section 5–10– 40, of Part 2, of the Bombardier Challenger 300 BD–100 Time Limits/Maintenance Checks Manual. For this task, the initial compliance time starts at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD. (1) For airplanes with 400 or fewer total flight hours as of the effective date of this AD: Prior to the accumulation of 800 total flight hours. (2) For airplanes with more than 400 total flight hours as of the effective date of this AD: Within 400 flight hours or 12 months after the effective date of this AD, whichever occurs first. (i) No Alternative Actions or Intervals After accomplishing the revision required by paragraphs (g) and (h) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (j)(1) of this AD. rmajette on DSK2TPTVN1PROD with RULES (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone 516–228–7300; fax 516– 794–5531. 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. The AMOC approval letter must specifically reference this AD. (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. (k) Related Information Refer to MCAI Canadian Airworthiness Directive CF–2011–05, dated March 24, 2011; and Bombardier Temporary Revision 5–2–59, dated November 25, 2010, to Section 5–10– 40, of Part 2, of the Bombardier Challenger 300 BD–100 Time Limits/Maintenance Checks Manual; for related information. (l) Material Incorporated by Reference (1) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference (IBR) of the VerDate Mar<15>2010 15:36 Apr 04, 2012 Jkt 226001 following service information under 5 U.S.C. 552(a) and 1 CFR part 51: (i) Bombardier Temporary Revision 5–2– 59, dated November 25, 2010, to Section 5– 10–40, of Part 2, of the Bombardier Challenger 300 BD–100 Time Limits/ Maintenance Checks Manual. (2) For service information identified in ˆ this AD, contact Bombardier, Inc., 400 Cote´ Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– 855–7401; email thd.crj@aero.bombardier. com; Internet https://www.bombardier.com. (3) You may review copies of the 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. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at an NARA facility, call 202–741– 6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on March 9, 2012. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–8041 Filed 4–4–12; 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; Amendment 39–16978; AD 2012–05–06] RIN 2120–AA64 Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding an existing airworthiness directive (AD) for all Lockheed Martin Corporation/ Lockheed Martin Aeronautics Company Model L–1011–385–1, L–1011–385–1– 14, and L–1011–385–1–15 airplanes. That 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. This new AD adds Model L– 1011–385–3 airplanes to the SUMMARY: PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 applicability, changes certain inspection thresholds, adds three new structurally significant details (SSDs), and removes an SSD that has been addressed by a different AD. This AD was prompted by an evaluation by the manufacturer of usage and flight data that provided additional information about certain 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. This AD is effective May 10, 2012. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of May 10, 2012. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of November 2, 1995 (60 FR 51713, October 3, 1995). ADDRESSES: 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; email 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. DATES: Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. 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; email: Carl.W.Gray@faa.gov. SUPPLEMENTARY INFORMATION: E:\FR\FM\05APR1.SGM 05APR1 20523 Federal Register / Vol. 77, No. 66 / Thursday, April 5, 2012 / Rules and Regulations Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 95–20–04 R1, Amendment 39–9454 (60 FR 63414, December 11, 1995). That AD applies to the specified products. The NPRM published in the Federal Register on August 8, 2011 (76 FR 48049). That NPRM proposed to continue to require implementation of a SID program of structural inspections to detect fatigue cracking, and repair if necessary. That NPRM also proposed to 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, include three additional SSDs for Model L–1011–385– 3 airplanes, and remove an SSD that has been addressed by a different AD action. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal NPRM (76 FR 48049, August 8, 2011) and the FAA’s response to each comment. Request To Withdraw NPRM (76 FR 48049, August 8, 2011) An anonymous commenter requested that we stop ‘‘regulating job(s) out of this country’’ and leave companies alone to run their business as they see fit. We infer the commenter is requesting that we withdraw the NPRM (76 FR 48049, August 8, 2011). We disagree. This AD addresses an identified unsafe condition. If the structural inspections required by this AD are not done, an airplane could develop fatigue cracking that could compromise the structural integrity of the airplane. We have not revised this AD in this regard. Request To Clarify Reference Lockheed Martin requested that we clarify the section of the document referenced in paragraph (g)(5) of the NPRM (76 FR 48049, August 8, 2011) by replacing ‘‘Appendix VI’’ with ‘‘Section VI., Appendix.’’ The commenter noted that there is no Appendix VI in the document and that there is a section VI titled Appendix. We agree, for the reason provided by the commenter. We have revised paragraph (g)(5) of this AD accordingly. Clarification of Repair Service Information We have added Note 1 following paragraph (n)(1) of this AD to clarify that guidance on doing repairs in accordance with a ‘‘L–1011–385 Series Supplemental Inspection Document’’ specified in paragraph (n)(1) of this AD can be found in the applicable service bulletins identified in certain SSDs of the ‘‘L–1011–385 Series Supplemental Inspection Document.’’ Explanation of Changes Made to This AD We have revised certain headers throughout this AD. We have also revised the wording in paragraph (g) of this AD. These changes have not changed the intent of this AD. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting the AD with the change described previously— and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (76 FR 48049, August 8, 2011) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (76 FR 48049, August 8, 2011). We also determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. Costs of Compliance We estimate that this AD affects 26 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost rmajette on DSK2TPTVN1PROD with RULES Incorporate SID into maintenance program [retained actions from AD 95– 20–04 R1, Amendment 39–9454 (60 FR 63414, December 11, 1995)]. Initial inspections [retained actions from AD 95–20–04 R1, Amendment 39– 9454 (60 FR 63414, December 11, 1995)]. Repetitive inspections [retained actions from AD 95–20–04 R1, Amendment 39–9454 (60 FR 63414, December 11, 1995)]. Incorporate SID into maintenance program [new action for Model L–1011– 385–3 airplanes]. Initial inspections [new action for Model L–1011–385–3 airplanes]. Repetitive inspections [new action for Model L–1011–385–3 airplanes]. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue VerDate Mar<15>2010 15:36 Apr 04, 2012 Jkt 226001 Parts cost Cost per product Number of airplanes affected Cost for U.S. operators 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. $0 $4,080 ..................... 2 $8,160. $0 $3,740 per inspection cycle. 2 $7,480 per inspection cycle. 48 work-hours × $85 per hour = $4,080. 44 work-hours × $85 per hour = $3,740 per inspection cycle. rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, E:\FR\FM\05APR1.SGM 05APR1 20524 Federal Register / Vol. 77, No. 66 / Thursday, April 5, 2012 / Rules and Regulations 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 AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 95–20–04 R1, Amendment 39–9454 (60 FR 63414, December 11, 1995), and adding the following new AD: rmajette on DSK2TPTVN1PROD with RULES ■ 2012–05–06 Lockheed Martin Corporation/ Lockheed Martin Aeronautics Company: Amendment 39–16978; Docket No. FAA–2011–0723; Directorate Identifier 2010–NM–080–AD. VerDate Mar<15>2010 15:36 Apr 04, 2012 Jkt 226001 (a) Effective Date This airworthiness directive (AD) is effective May 10, 2012. (b) Affected ADs This AD supersedes AD 95–20–04 R1, Amendment 39–9454 (60 FR 63414, December 11, 1995). (c) Applicability 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. (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition 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. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Maintenance Program Revision This maintenance program revision is retained from AD 95–20–04 R1, Amendment 39–9454 (60 FR 63414, December 11, 1995): 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, Amendment 39– 9454 (60 FR 63414, December 11, 1995)), incorporate a revision into the maintenance inspection program which provides for inspection(s) of the structurally significant details (SSD) defined in Lockheed Document 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 PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 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 Section VI., ‘‘Appendix,’’ 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. (h) New Requirements of This AD: Maintenance Program Revision 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. (i) New Requirement of This AD: Threshold and Intervals 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 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 E:\FR\FM\05APR1.SGM 05APR1 Federal Register / Vol. 77, No. 66 / Thursday, April 5, 2012 / Rules and Regulations 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. (j) Exception to Intervals—10 Percent Deviation Allowed 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) Exception to Intervals Specifying ‘‘C’’ Check 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. rmajette on DSK2TPTVN1PROD with RULES (l) Exceptions to Threshold and Intervals 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). (m) Exception to Inspection Procedure 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. VerDate Mar<15>2010 15:36 Apr 04, 2012 Jkt 226001 (n) New Requirements of This AD: Repair 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 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 Lockheed Document Number LG92ER0060, ‘‘L–1011–385 Series Supplemental Inspection Document,’’ revised April 2009. Note 1 to paragraph (n)(1) of this AD: Guidance on doing repairs in accordance with a ‘‘L–1011–385 Series Supplemental Inspection Document’’ specified in paragraph (n)(1) of this AD can be found in the applicable service bulletins identified in certain SSDs of the ‘‘L–1011–385 Series Supplemental Inspection Document’’ specified in paragraph (n)(1) of this AD. (2) In accordance with 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. (o) New Requirements of This AD: Reporting 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. (p) Paperwork Reduction Act Burden Statement 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 PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 20525 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. (q) Alternative Methods of Compliance (AMOCs) (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. (r) Related Information 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; email: Carl.W.Gray@faa.gov. (s) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the following service information under 5 U.S.C. 552(a) and 1 CFR part 51 on the date specified. (2) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on May 10, 2012. (i) Lockheed Document Number LG92ER0060, ‘‘L–1011–385 Series Supplemental Inspection Document,’’ revised April 2009. (ii) Lockheed L–1011 Structural Repair Manual, Revision 80, dated December 15, 2009, which contains the following errors: (A) Page 13/14 of Section 51–10–06, pages 1 through 10 of the Table of Contents for Chapter 54, and page 809/810 of Section 55– 35–00 show a page date of ‘‘Date 15XX;’’ these pages should be dated December 15, 2009. (B) The List of Effective Pages for Chapter 51 identifies incorrect dates for pages 3 and 4 of the Table of Contents for Chapter 51; the correct date of those pages is March 15, 1999. (C) Page 7 of the List of Effective Pages for Chapter 53 does not list a configuration number for page 20 of Section 53–21–00; that page should be identified as configuration 2. (D) The List of Effective Pages for Chapter 53 identifies incorrect dates for pages 3 and 5 of Section 53–14–00 (Configuration 2); the correct dates are September 15, 1995, for page 3, and March 15, 1994, for page 5. (E) The List of Effective Pages for Chapter 53 identifies an incorrect date for page 4 of Section 53–15–00; the correct date for that page is September 15, 1981. E:\FR\FM\05APR1.SGM 05APR1 rmajette on DSK2TPTVN1PROD with RULES 20526 Federal Register / Vol. 77, No. 66 / Thursday, April 5, 2012 / Rules and Regulations (F) The List of Effective Pages for Chapter 54 identifies an incorrect date for page 1 of Section 54–23–00; the correct date for that page is May 15, 1986. (G) The List of Effective Pages for Chapter 54 identifies an incorrect date for page 4 of Section 54–32–00; the correct date for that page is March 15, 1992. (H) The List of Effective Pages for Chapter 57 identifies an incorrect date for page 13 of Section 57–00–00; the correct date for that page is April 15, 2005. (I) The List of Effective Pages for Chapter 57 identifies an incorrect date for pages 16 and 18 of Section 57–12–00; the correct date for those pages is March 15, 1983. (J) The List of Effective Pages for Chapter 57 identifies an incorrect date for pages 801, 802, and 805/806 of Section 57–13–00; the correct date for those pages is December 15, 2009. (K) The List of Effective Pages for Chapter 57 identifies an incorrect date for pages 810 through 819 of Section 57–51–00; the correct date for those pages is December 15, 2009. (L) The List of Effective Pages for Chapter 57 identifies an incorrect date for page 4 of Section 57–52–00; the correct date for that page is December 15, 2009. (M) Page 25, dated March 15, 1983, and page 26, dated May 15, 1986, of Section 57– 12–00 were inadvertently omitted from the List of Effective Pages for Chapter 57. (4) The following service information was approved for IBR November 2, 1995 (60 FR 51713, October 3, 1995). (i) Lockheed Document Number LG92ER0060, ‘‘L–1011–385 Series Supplemental Inspection Document,’’ revised January 1994. (5) For service information identified in this AD, contact Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, L1011 Technical Support Center, Dept. 6A4M, Zone 0579, 86 South Cobb Drive, Marietta, Georgia 30063–0579; telephone 770–494–5444; fax 770–494–5445; email L1011.support@lmco.com; Internet https://www.lockheedmartin.com/ams/tools/ TechPubs.html. (6) You may review copies of the 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. (7) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at an NARA facility, call 202–741– 6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, WA, on March 1, 2012. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–8040 Filed 4–4–12; 8:45 am] BILLING CODE 4910–13–P VerDate Mar<15>2010 15:36 Apr 04, 2012 Jkt 226001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Washington 98057–3356; telephone (425) 227–1137; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: 14 CFR Part 39 Discussion [Docket No. FAA–2011–1318; Directorate Identifier 2010–NM–274–AD; Amendment 39–17009; AD 2012–07–03] We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on December 12, 2011 (76 FR 77159), and proposed to supersede AD 2009–21–06, Amendment 39–16043 (74 FR 53151, October 16, 2009). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: RIN 2120–AA64 Airworthiness Directives; 328 Support Services GmbH Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding an existing airworthiness directive (AD) for all 328 Support Services GmbH (Type Certificate previously held by AvCraft Aerospace GmbH; Fairchild Dornier GmbH; Dornier Luftfahrt GmbH) Model 328–100 and –300 airplanes. That AD currently requires performing a detailed visual inspection of the cockpit door locking device and the surrounding area for proper installation, and corrective action if necessary. This new AD requires removing or replacing the locking device of the cockpit door; performing operational tests, and repair if necessary; and, for certain airplanes, installing gap filler parts. This AD was prompted by a report that a right-hand power lever jammed in flight-idle position during the landing roll-out, and the airplane was stopped by excessive braking. We are issuing this AD to detect and correct interference with the engine and flight control cables, which could result in reduced controllability of the airplane. DATES: This AD becomes effective May 10, 2012. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of May 10, 2012. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of November 20, 2009 (74 FR 53151, October 16, 2009). ADDRESSES: You may examine the AD docket on the Internet at https://www. regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, SUMMARY: PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 An incident has been reported with a Dornier 328–100 aeroplane, where the righthand (RH) power lever jammed in flight-idle position during the landing roll-out. The aeroplane was stopped by excessive braking. The reason for the jamming was that the cockpit door locking device Part Number (P/ N) 001A252A3914012 had fallen off the RH cockpit wall, blocking the RH power/ condition lever pulley/cable cluster below the door. Although the affected aeroplane had been modified, the technical investigation showed that a loose Cockpit Door Locking device could also occur on 328–100 and 328–300 aeroplanes with a standard installation. This condition, if not corrected, could cause interference with the engine and/or flight control cables, possibly resulting in reduced control of the aeroplane. To address that unsafe condition, EASA issued AD 2009–0082 [which corresponds to FAA AD 2009–21–06, Amendment 39–16043 (74 FR 53151, October 16, 2009)] as an interim solution, to require a one-time inspection of the cockpit door locking device and the surrounding area and the reporting of all findings to the TC [type certificate] holder. Since that AD was issued, the TC holder has developed an improved cockpit door locking device, P/N 001A252A3914016. Consequently, this [EASA] AD retains the requirements of [EASA] AD 2009–0082, which is superseded, and requires the replacement of the current P/N 001A252A3914012 with new designed P/N 001A252A3914016 cockpit door locking device, or the removal of the cockpit door locking device P/N 001A252A3914012 and the installation of a gap filler, as applicable to aeroplane configuration. The required actions include performing operational tests, and repair if necessary. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (76 FR 77159, December 12, 2011) or on the determination of the cost to the public. E:\FR\FM\05APR1.SGM 05APR1

Agencies

[Federal Register Volume 77, Number 66 (Thursday, April 5, 2012)]
[Rules and Regulations]
[Pages 20522-20526]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-8040]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0723; Directorate Identifier 2010-NM-080-AD; 
Amendment 39-16978; AD 2012-05-06]
RIN 2120-AA64


Airworthiness Directives; Lockheed Martin Corporation/Lockheed 
Martin Aeronautics Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding an existing airworthiness directive (AD) 
for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company 
Model L-1011-385-1, L-1011-385-1-14, and L-1011-385-1-15 airplanes. 
That 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. This new AD adds Model L-1011-385-3 airplanes to the 
applicability, changes certain inspection thresholds, adds three new 
structurally significant details (SSDs), and removes an SSD that has 
been addressed by a different AD. This AD was prompted by an evaluation 
by the manufacturer of usage and flight data that provided additional 
information about certain 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.

DATES: This AD is effective May 10, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of May 10, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
November 2, 1995 (60 FR 51713, October 3, 1995).

ADDRESSES: 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; 
email 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 AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (phone: 800-647-5527) is Document Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC 20590.

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; email: Carl.W.Gray@faa.gov.

SUPPLEMENTARY INFORMATION: 

[[Page 20523]]

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 95-20-04 R1, Amendment 39-9454 (60 FR 63414, 
December 11, 1995). That AD applies to the specified products. The NPRM 
published in the Federal Register on August 8, 2011 (76 FR 48049). That 
NPRM proposed to continue to require implementation of a SID program of 
structural inspections to detect fatigue cracking, and repair if 
necessary. That NPRM also proposed to 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, include three additional SSDs for Model L-1011-385-3 
airplanes, and remove an SSD that has been addressed by a different AD 
action.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
NPRM (76 FR 48049, August 8, 2011) and the FAA's response to each 
comment.

Request To Withdraw NPRM (76 FR 48049, August 8, 2011)

    An anonymous commenter requested that we stop ``regulating job(s) 
out of this country'' and leave companies alone to run their business 
as they see fit.
    We infer the commenter is requesting that we withdraw the NPRM (76 
FR 48049, August 8, 2011). We disagree. This AD addresses an identified 
unsafe condition. If the structural inspections required by this AD are 
not done, an airplane could develop fatigue cracking that could 
compromise the structural integrity of the airplane. We have not 
revised this AD in this regard.

Request To Clarify Reference

    Lockheed Martin requested that we clarify the section of the 
document referenced in paragraph (g)(5) of the NPRM (76 FR 48049, 
August 8, 2011) by replacing ``Appendix VI'' with ``Section VI., 
Appendix.'' The commenter noted that there is no Appendix VI in the 
document and that there is a section VI titled Appendix.
    We agree, for the reason provided by the commenter. We have revised 
paragraph (g)(5) of this AD accordingly.

Clarification of Repair Service Information

    We have added Note 1 following paragraph (n)(1) of this AD to 
clarify that guidance on doing repairs in accordance with a ``L-1011-
385 Series Supplemental Inspection Document'' specified in paragraph 
(n)(1) of this AD can be found in the applicable service bulletins 
identified in certain SSDs of the ``L-1011-385 Series Supplemental 
Inspection Document.''

Explanation of Changes Made to This AD

    We have revised certain headers throughout this AD. We have also 
revised the wording in paragraph (g) of this AD. These changes have not 
changed the intent of this AD.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the change described previously--and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (76 FR 48049, August 8, 2011) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (76 FR 48049, August 8, 2011).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

Costs of Compliance

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

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Number of
            Action                Labor cost      Parts cost        Cost per        airplanes     Cost for U.S.
                                                                    product         affected        operators
----------------------------------------------------------------------------------------------------------------
Incorporate SID into           550 work-hours               $0  $46,750........              26  $1,215,500.
 maintenance program            x $85 per hour
 [retained actions from AD 95-  = $46,750.
 20-04 R1, Amendment 39-9454
 (60 FR 63414, December 11,
 1995)].
Initial inspections [retained  245 work-hours               $0  $20,825........              26  $541,450.
 actions from AD 95-20-04 R1,   x $85 per hour
 Amendment 39-9454 (60 FR       = $20,825.
 63414, December 11, 1995)].
Repetitive inspections         52 work-hours x              $0  $4,420 per                   26  $114,920 per
 [retained actions from AD 95-  $85 per hour =                   inspection                       inspection
 20-04 R1, Amendment 39-9454    $4,420 per                       cycle.                           cycle.
 (60 FR 63414, December 11,     inspection
 1995)].                        cycle.
Incorporate SID into           1 work-hour x                $0  $85............               2  $170.
 maintenance program [new       85 = $85.
 action for Model L-1011-385-
 3 airplanes].
Initial inspections [new       48 work-hours x              $0  $4,080.........               2  $8,160.
 action for Model L-1011-385-   $85 per hour =
 3 airplanes].                  $4,080.
Repetitive inspections [new    44 work-hours x              $0  $3,740 per                    2  $7,480 per
 action for Model L-1011-385-   $85 per hour =                   inspection                       inspection
 3 airplanes].                  $3,740 per                       cycle.                           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,

[[Page 20524]]

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 AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (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.

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
95-20-04 R1, Amendment 39-9454 (60 FR 63414, December 11, 1995), and 
adding the following new AD:

2012-05-06 Lockheed Martin Corporation/Lockheed Martin Aeronautics 
Company: Amendment 39-16978; Docket No. FAA-2011-0723; Directorate 
Identifier 2010-NM-080-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective May 10, 2012.

(b) Affected ADs

    This AD supersedes AD 95-20-04 R1, Amendment 39-9454 (60 FR 
63414, December 11, 1995).

(c) Applicability

    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.

(d) Subject

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

(e) Unsafe Condition

    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.

(f) Compliance

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

(g) Retained Maintenance Program Revision

    This maintenance program revision is retained from AD 95-20-04 
R1, Amendment 39-9454 (60 FR 63414, December 11, 1995): 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, Amendment 39-9454 (60 FR 63414, December 11, 1995)), incorporate 
a revision into the maintenance inspection program which provides 
for inspection(s) of the structurally significant details (SSD) 
defined in Lockheed Document 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 
Section VI., ``Appendix,'' 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.

(h) New Requirements of This AD: Maintenance Program Revision

    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.

(i) New Requirement of This AD: Threshold and Intervals

    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

[[Page 20525]]

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.

(j) Exception to Intervals--10 Percent Deviation Allowed

    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) Exception to Intervals Specifying ``C'' Check

    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) Exceptions to Threshold and Intervals

    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).

(m) Exception to Inspection Procedure

    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.

(n) New Requirements of This AD: Repair

    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 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 
Lockheed Document Number LG92ER0060, ``L-1011-385 Series 
Supplemental Inspection Document,'' revised April 2009.

    Note 1 to paragraph (n)(1) of this AD: Guidance on doing repairs 
in accordance with a ``L-1011-385 Series Supplemental Inspection 
Document'' specified in paragraph (n)(1) of this AD can be found in 
the applicable service bulletins identified in certain SSDs of the 
``L-1011-385 Series Supplemental Inspection Document'' specified in 
paragraph (n)(1) of this AD.

    (2) In accordance with 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.

(o) New Requirements of This AD: Reporting

    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.

(p) Paperwork Reduction Act Burden Statement

    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.

(q) Alternative Methods of Compliance (AMOCs)

    (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.

(r) Related Information

    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; email: Carl.W.Gray@faa.gov.

(s) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the following service 
information under 5 U.S.C. 552(a) and 1 CFR part 51 on the date 
specified.
    (2) You must use the following service information to do the 
actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
May 10, 2012.
    (i) Lockheed Document Number LG92ER0060, ``L-1011-385 Series 
Supplemental Inspection Document,'' revised April 2009.
    (ii) Lockheed L-1011 Structural Repair Manual, Revision 80, 
dated December 15, 2009, which contains the following errors:
    (A) Page 13/14 of Section 51-10-06, pages 1 through 10 of the 
Table of Contents for Chapter 54, and page 809/810 of Section 55-35-
00 show a page date of ``Date 15XX;'' these pages should be dated 
December 15, 2009.
    (B) The List of Effective Pages for Chapter 51 identifies 
incorrect dates for pages 3 and 4 of the Table of Contents for 
Chapter 51; the correct date of those pages is March 15, 1999.
    (C) Page 7 of the List of Effective Pages for Chapter 53 does 
not list a configuration number for page 20 of Section 53-21-00; 
that page should be identified as configuration 2.
    (D) The List of Effective Pages for Chapter 53 identifies 
incorrect dates for pages 3 and 5 of Section 53-14-00 (Configuration 
2); the correct dates are September 15, 1995, for page 3, and March 
15, 1994, for page 5.
    (E) The List of Effective Pages for Chapter 53 identifies an 
incorrect date for page 4 of Section 53-15-00; the correct date for 
that page is September 15, 1981.

[[Page 20526]]

    (F) The List of Effective Pages for Chapter 54 identifies an 
incorrect date for page 1 of Section 54-23-00; the correct date for 
that page is May 15, 1986.
    (G) The List of Effective Pages for Chapter 54 identifies an 
incorrect date for page 4 of Section 54-32-00; the correct date for 
that page is March 15, 1992.
    (H) The List of Effective Pages for Chapter 57 identifies an 
incorrect date for page 13 of Section 57-00-00; the correct date for 
that page is April 15, 2005.
    (I) The List of Effective Pages for Chapter 57 identifies an 
incorrect date for pages 16 and 18 of Section 57-12-00; the correct 
date for those pages is March 15, 1983.
    (J) The List of Effective Pages for Chapter 57 identifies an 
incorrect date for pages 801, 802, and 805/806 of Section 57-13-00; 
the correct date for those pages is December 15, 2009.
    (K) The List of Effective Pages for Chapter 57 identifies an 
incorrect date for pages 810 through 819 of Section 57-51-00; the 
correct date for those pages is December 15, 2009.
    (L) The List of Effective Pages for Chapter 57 identifies an 
incorrect date for page 4 of Section 57-52-00; the correct date for 
that page is December 15, 2009.
    (M) Page 25, dated March 15, 1983, and page 26, dated May 15, 
1986, of Section 57-12-00 were inadvertently omitted from the List 
of Effective Pages for Chapter 57.
    (4) The following service information was approved for IBR 
November 2, 1995 (60 FR 51713, October 3, 1995).
    (i) Lockheed Document Number LG92ER0060, ``L-1011-385 Series 
Supplemental Inspection Document,'' revised January 1994.
    (5) For service information identified in this AD, contact 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, 
L1011 Technical Support Center, Dept. 6A4M, Zone 0579, 86 South Cobb 
Drive, Marietta, Georgia 30063-0579; telephone 770-494-5444; fax 
770-494-5445; email L1011.support@lmco.com; Internet https://www.lockheedmartin.com/ams/tools/TechPubs.html.
    (6) You may review copies of the 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.
    (7) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at an NARA facility, call 202-741-6030, or go to https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, WA, on March 1, 2012.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-8040 Filed 4-4-12; 8:45 am]
BILLING CODE 4910-13-P
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