Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes, 32441-32445 [2015-13325]

Download as PDF Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations The woven composite fan blades are a novel and unusual design feature that requires additional airworthiness standards for type certification of the LEAP–1A and –1C engine models. Discussion of Comments A notice of proposed special conditions, No. 33–14–02–SC, for the CFM LEAP–1A and—1C engine models was published in the Federal Register on Friday, November 14, 2014 (79 FR 68137). No comments were received and the special conditions are adopted as proposed. Applicability As discussed above, these special conditions are applicable to the LEAP –1A and –1C engine models. Should CFM apply at a later date for a change to the type certificate to include another model on the same type certificate incorporating the same novel or unusual design feature, the special conditions would apply to that model as well. Conclusion This action affects only certain novel or unusual design features on LEAP–1A and –1C engine models. It is not a rule of general applicability and applies only to CFM, who requested FAA approval of this engine feature. List of Subjects in 14 CFR Part 33 Aircraft, Engines, Aviation Safety, Reporting and recordkeeping requirements. The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. tkelley on DSK3SPTVN1PROD with RULES The Special Conditions Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for CFM LEAP–1A and –1C engine models. 1. Part 33, Requirements In addition to the airworthiness standards in 14 CFR part 33, effective February 1, 1965, with Amendments 33–1 through 33–32 applicable to the LEAP–1A and –1C engine models, CFM will: (a) Conduct an engine fan blade containment test with the fan blade failing at the inner annulus flow path line instead of at the outermost retention groove. (b) Substantiate by test and analysis, or other methods acceptable to the FAA, that a fan disk and fan blade retention system with minimum material properties can withstand, without VerDate Sep<11>2014 15:56 Jun 08, 2015 Jkt 235001 failure, a centrifugal load equal to two times the maximum load the retention system could experience within approved engine operating limitations. The fan blade retention system includes the portion of the fan blade from the inner annulus flow path line inward to the blade dovetail, the blade retention components, and the fan disk and fan blade attachment features. (c) Using a procedure approved by the FAA, establish an operating limitation that specifies the maximum allowable number of start-stop stress cycles for the fan blade retention system. The life evaluation must include the combined effects of high-cycle and low-cycle fatigue. If the operating limitation is less than 100,000 cycles, that limitation must be specified in Chapter 5 of the Engine Manual Airworthiness Limitations Section. The procedure used to establish the maximum allowable number of start-stop stress cycles for the fan blade retention system will incorporate the integrity requirements in paragraphs (c)(1), (c)(2), and (c)(3) of these special conditions for the fan blade retention system. (1) An engineering plan, which establishes and maintains that the combinations of loads, material properties, environmental influences, and operating conditions, including the effects of parts influencing these parameters, are well known or predictable through validated analysis, test, or service experience. (2) A manufacturing plan that identifies the specific manufacturing constraints necessary to consistently produce the fan blade retention system with the attributes required by the engineering plan. (3) A service management plan that defines in-service processes for maintenance and repair of the fan blade retention system, which will maintain attributes consistent with those required by the engineering plan. (d) Substantiate by test and analysis, or other methods acceptable to the FAA, that the blade design below the inner annulus flow path line provides multiple load paths and crack arresting features that prevent delamination or crack propagation to blade failure during the life of the blade. (e) Substantiate that during the service life of the engine, the total probability of an individual blade retention system failure resulting from all possible causes, as defined in § 33.75, will be extremely improbable with a cumulative calculated probability of failure of less than 10¥9 per engine flight hour. (f) Substantiate by test or analysis that not only will the engine continue to PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 32441 meet the requirements of § 33.75 following a lightning strike on the composite fan blade structure, but that the lightning strike will not cause damage to the fan blades that would prevent continued safe operation of the affected engine. (g) Account for the effects of inservice deterioration, manufacturing variations, minimum material properties, and environmental effects during the tests and analyses required by paragraphs (a), (b), (c), (d), (e), and (f) of these special conditions. (h) Propose fleet leader monitoring and field sampling programs that will monitor the effects of engine fan blade usage and fan blade retention system integrity. (i) Mark each fan blade legibly and permanently with a part number and a serial number. Issued in Burlington, Massachusetts, on June 1, 2015. Ann C. Mollica, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2015–14084 Filed 6–8–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0227; Directorate Identifier 2013–NM–211–AD; Amendment 39–18165; AD 2015–11–02] 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 Airworthiness Directive (AD) 95–26–11 for all Lockheed Martin Corporation/ Lockheed Martin Aeronautics Company Model L–1011 series airplanes. AD 95– 26–11 required repetitive inspections to detect cracking of the fittings that attach the aft pressure bulkhead to the fuselage stringers, repetitive inspections to detect cracking of the fittings and of the splice tab of the aft pressure bulkhead, and corrective actions if necessary. This new AD requires repetitive inspections to detect cracking of the fittings that attach the aft pressure bulkhead to the fuselage stringers, repetitive inspections to detect cracking of the fittings and of the splice tab of the aft pressure bulkhead, repetitive inspections for cracking of SUMMARY: E:\FR\FM\09JNR1.SGM 09JNR1 32442 Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations certain aft fuselage skin panels, a structural modification, a postmodification inspection program, and corrective actions if necessary. This AD was prompted by a determination that the fittings at stringer attachments to the upper region of the aft pressure bulkhead are subject to widespread fatigue damage (WFD). We are issuing this AD to prevent simultaneous failure of multiple stringer end fittings through fatigue cracking at the aft pressure bulkhead, which could lead to rapid decompression of the airplane. DATES: This AD is effective July 14, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 14, 2015. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of January 11, 1996 (60 FR 668702, December 27, 1995). ADDRESSES: 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, GA 30063–0579; telephone 770–494– 5444; fax 770–494–5445; email L1011.support@lmco.com; Internet http://www.lockheedmartin.com/ams/ tools/TechPubs.html. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227– 1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2014–0227. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0227; 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 Docket 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, GA 30337; phone: 404–474–5554; fax: 404– 474–5605; email: carl.w.gray@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 to supersede AD 95–26–11, Amendment 39–9469 (60 FR 66870, December 27, 1995). AD 95–26– 11 applied to all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model L–1011 series airplanes. The SNPRM published in the Federal Register on November 17, 2014 (79 FR 68377). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on April 14, 2014 (79 FR 20819). The NPRM proposed to require repetitive inspections to detect cracking of the fittings that attach the aft pressure bulkhead to the fuselage stringers, repetitive inspections to detect cracking of the fittings and of the splice tab of the aft pressure bulkhead, repetitive inspections for cracking of certain aft fuselage skin panels, a structural modification, a postmodification inspection program, and corrective actions if necessary. The NPRM was prompted by a determination that the fittings at stringer attachments to the upper region of the aft pressure bulkhead are subject to WFD. The SNPRM proposed to reduce the post-structural modification repetitive inspection interval. We are issuing this AD to prevent simultaneous failure of multiple stringer end fittings through fatigue cracking at the aft pressure bulkhead, which could lead to rapid decompression of the airplane. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the SNPRM (79 FR 68377, November 17, 2014) or on the determination of the cost to the public. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the SNPRM (79 FR 68377, November 17, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the SNPRM (79 FR 68377, November 17, 2014). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed Lockheed Service Bulletin 093–53–105, Revision 3, dated May 31, 2013. The service information describes procedures for inspections for cracking of the stringer end fittings at the aft pressure bulkhead, corrective actions, and a modification that includes replacement of the stringer end fittings of certain stringers with new fittings. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this 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 tkelley on DSK3SPTVN1PROD with RULES Action Labor cost Inspections [actions retained from AD 95–26–11, Amendment 39–9469 (60 FR 66870, December 27, 1995)]. Inspections and modification [new action]. 23 work-hours × $85 per hour = $1,955 per inspection cycle. VerDate Sep<11>2014 15:56 Jun 08, 2015 Parts cost $0 185 work-hours × $85 per hour = $15,725. Jkt 235001 PO 00000 Frm 00004 Cost per product 6,750 Fmt 4700 Sfmt 4700 Cost on U.S. operators $1,955 per inspection cycle $50,830 per inspection cycle. $22,475 ................................ $584,350. E:\FR\FM\09JNR1.SGM 09JNR1 Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations We estimate the following costs to do any necessary replacements that would be required based on the results of the inspections. We have no way of 32443 determining the number of aircraft that might need these replacements: ON-CONDITION COSTS Action Labor cost Parts cost Cost per product Replacement of one fitting ...................................... 16 work-hour × $85 per hour = $1,360 .................. $250 $1,610 We have received no definitive data that would enable us to provide cost estimates for the other on-condition actions specified in this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: 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. tkelley on DSK3SPTVN1PROD with RULES Regulatory Findings 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) 95–26–11, Amendment 39–9469 (60 FR 66870, December 27, 1995), and adding the following new AD: ■ 2015–11–02 Lockheed Martin Corporation/ Lockheed Martin Aeronautics Company: Amendment 39–18165 ; Docket No. FAA–2014–0227; Directorate Identifier 2013–NM–211–AD. (a) Effective Date This AD is effective July 14, 2015. (b) Affected ADs This AD replaces AD 95–26–11, Amendment 39–9469 (60 FR 66870, December 27, 1995). 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. (c) Applicability This AD applies to 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. List of Subjects in 14 CFR Part 39 (g) Retained Detailed Visual Inspection This paragraph restates the requirements of paragraph (a) of AD 95–26–11, Amendment 39–9469 (60 FR 66870, December 27, 1995), Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. VerDate Sep<11>2014 15:56 Jun 08, 2015 Jkt 235001 (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by a determination that the fittings at stringer attachments to the upper region of the aft pressure bulkhead are subject to widespread fatigue damage (WFD). We are issuing this AD to prevent simultaneous failure of multiple stringer end fittings through fatigue cracking at the aft pressure bulkhead, which could lead to rapid decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 with no changes. Perform a detailed visual inspection to detect cracking of the fittings that attach the aft pressure bulkhead to the fuselage stringers (hereinafter referred to as ‘‘fittings’’) at stringers 1 through 10 (right side) and at stringers 56 through 64 (left side), at the later of the times specified in either paragraph (g)(1) or (g)(2) of this AD. (1) Prior to the accumulation of 20,000 total flight cycles; or (2) Within the next 25 flight cycles or 10 days after September 28, 1995 (the effective date of AD 95–18–52, Amendment 39–9366 (60 FR 47465, September 13, 1995)), whichever occurs earlier. (h) Retained Corrective Action for Cracked Fitting This paragraph restates the requirements of paragraph (c) of AD 95–26–11, Amendment 39–9469 (60 FR 66870, December 27, 1995), with no changes. If any cracked fitting is detected during the inspection required by paragraph (g) of this AD: Before further flight, accomplish the requirements of paragraphs (h)(1) and (h)(2) of this AD. (1) Replace the cracked fitting with a new fitting, or with a serviceable fitting on which a detailed visual inspection has been performed previously to detect cracking and that has been found to be free of cracks. (2) Perform a detailed visual inspection to detect cracking in the radius at the lower end of the vertical leg of the bulkhead T-shaped frame between the stringer locations on either side of the stringer having the cracked fitting. If any cracked T-shaped frame is detected: Before further flight, repair in accordance with a method approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA. (i) Retained Repetitive Fitting Inspections This paragraph restates the requirements of paragraph (d) of AD 95–26–11, Amendment 39–9469 (60 FR 66870, December 27, 1995), with no changes. Repeat the inspections and other necessary actions required by paragraphs (g) and (h) of this AD at intervals not to exceed 1,800 flight cycles or 3,000 flight hours, whichever occurs earlier, until paragraph (j) of this AD is accomplished. (j) Retained Eddy Current Surface Scan (ECSS) Inspections, and Related Investigative and Corrective Actions This paragraph restates the requirements of paragraph (e) of AD 95–26–11, Amendment 39–9469 (60 FR 66870, December 27, 1995), with revised compliance times specified in paragraph (k) of this AD, exclusion of an ECSS inspection for certain airplanes, and new service information. Except as provided by paragraph (l) of this AD: At the applicable time specified in paragraph (k)(1) of this AD, accomplish the requirements of paragraphs E:\FR\FM\09JNR1.SGM 09JNR1 tkelley on DSK3SPTVN1PROD with RULES 32444 Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations (j)(1) and (j)(2) of this AD. Repeat the ECSS inspections thereafter at the compliance time specified in paragraph (k)(2) of this AD. Accomplishment of the ECSS inspection constitutes terminating action for the repetitive inspection requirements of paragraph (i) of this AD. (1) Perform an ECSS inspection to detect cracking of the fittings at stringers 1 through 14 (right side) and at stringers 52 through 64 (left side), in accordance with the Accomplishment Instructions of Lockheed L– 1011 Service Bulletin 093–53–105, Revision 1, dated November 17, 1995; or Lockheed Service Bulletin 093–53–105, Revision 3, dated May 31, 2013; except for airplanes with a large (47-inch-wide) aft passenger door, an ECSS inspection of stringers 12, 13, 53, and 54 is not required by this paragraph. Except as provided by paragraph (m) of this AD, if any cracking is detected, prior to further flight, replace the fitting with a new fitting without pilot holes, rework the fitting, and perform various follow-on actions (i.e., bolt hole eddy current (BHEC), ECSS, and borescope inspections; and repair) of the inner and outer tee caps, in accordance with the Accomplishment Instructions of Lockheed L–1011 Service Bulletin 093–53– 105, Revision 1, dated November 17, 1995; or Lockheed Service Bulletin 093–53–105, Revision 3, dated May 31, 2013, except as required by paragraph (p) of this AD. As of the effective date of this AD, use only Lockheed Service Bulletin 093–53–105, Revision 3, dated May 31, 2013, for accomplishing the actions required by this paragraph. (2) Perform an ECSS inspection to detect cracking of the lower (or inner) surface of the upper bonded splice tab of the bulkhead assembly at stringers 1 through 14 (right side) and at stringers 52 through 64 (left side), in accordance with the Accomplishment Instructions of Lockheed L–1011 Service Bulletin 093–53–105, Revision 1, dated November 17, 1995; or Lockheed Service Bulletin 093–53–105, Revision 3, dated May 31, 2013. As of the effective date of this AD, use only Lockheed Service Bulletin 093–53– 105, Revision 3, dated May 31, 2013, for accomplishing the actions required by this paragraph. (i) Except as provided by paragraph (m) of this AD, if any cracking is detected at the upper bonded splice tab, repair in accordance with a method approved by the Manager, Atlanta ACO, FAA. (ii) Except as provided by paragraph (m) of this AD, if any cracking is detected at a fastener, prior to further flight, perform a BHEC inspection to detect cracking of the forward flange of the inner tee cap, in accordance with the Accomplishment Instructions of Lockheed L–1011 Service Bulletin 093–53–105, Revision 1, dated November 17, 1995; or Lockheed Service Bulletin 093–53–105, Revision 3, dated May 31, 2013. If any cracking is detected, prior to further flight, repair in accordance with the Accomplishment Instructions of Lockheed L– 1011 Service Bulletin 093–53–105, Revision 1, dated November 17, 1995; or Lockheed Service Bulletin 093–53–105, Revision 3, dated May 31, 2013, except as required by paragraph (p) of this AD. As of the effective VerDate Sep<11>2014 15:56 Jun 08, 2015 Jkt 235001 date of this AD, use only Lockheed Service Bulletin 093–53–105, Revision 3, dated May 31, 2013, for accomplishing the actions required by this paragraph. (k) New Revised Compliance Times for Paragraph (j) of This AD (1) Do the initial inspections required by paragraph (j) of this AD at the earlier of the times specified in paragraphs (k)(1)(i) and (k)(1)(ii) of this AD. (i) Prior to the accumulation of 20,000 total flight cycles, or within 30 days after January 11, 1996 (the effective date of date of AD 95– 26–11, Amendment 39–9469 (60 FR 66870, December 27, 1995)), whichever occurs later. (ii) At the later of the times specified in paragraphs (k)(1)(ii)(A) and (k)(1)(ii)(B) of this AD. (A) Before the accumulation of 13,875 total flight cycles. (B) Within 365 days or 1,000 flight cycles after the effective date of this AD, whichever occurs first. (2) Repeat the inspections specified in paragraph (j) of this AD within 2,500 flight cycles after accomplishing the most recent inspection required by paragraph (j) of this AD, and repeat the inspection thereafter at intervals not to exceed 1,750 flight cycles. (l) Retained Inspection Deferral for Paragraph (j) of This AD This paragraph restates the requirements of paragraph (f) of AD 95–26–11, Amendment 39–9469 (60 FR 66870, December 27, 1995). Accomplishment of the initial ECSS inspections required by paragraph (j) of this AD may be deferred to a date within 120 days after January 11, 1996 (the effective date of date of AD 95–26–11), provided that, in the interim, a visual inspection as specified in paragraph (g) of this AD is accomplished within 30 days after January 11, 1996 (the effective date of date of AD 95–26–11), and repeated thereafter at intervals not to exceed 50 flight cycles. Once the ECSS inspections begin, the visual inspections may be terminated. (m) Retained Inspection Deferral With Revised Compliance Time and New Deferral This paragraph restates the requirements of paragraph (g) of AD 95–26–11, Amendment 39–9469 (60 FR 66870, December 27, 1995), with a revised compliance time, service information, and a new deferred action. As of the effective date of this AD, the deferral specified in paragraphs (m)(1) and (m)(2) of this AD cannot be done. If cracking was found before the effective date of this AD, the deferral specified in paragraphs (m)(1) and (m)(2) of this AD may be done. (1) If two or more adjacent fittings on both sides of the cracked fittings or bonded splice tabs/ fasteners are determined to be free of cracks by the ECSS inspection required by paragraphs (j)(1) and (j)(2) of this AD, repeat the ECSS inspection of the adjacent fittings thereafter at intervals not to exceed 600 flight cycles until the cracked fittings or splice tabs/fasteners are replaced or repaired, in accordance with the Accomplishment Instructions of Lockheed L–1011 Service Bulletin 093–53–105, Revision 1, dated November 17, 1995; or Lockheed Service Bulletin 093–53–105, Revision 3, dated May PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 31, 2013. At the applicable time specified in paragraphs (m)(1)(i) and (m)(1)(ii) of this AD: Replace the cracked fitting and/or splice tab/ fasteners, in accordance with the Accomplishment Instructions of Lockheed L–1011 Service Bulletin 093–53–105, Revision 1, dated November 17, 1995; or Lockheed Service Bulletin 093–53–105, Revision 3, dated May 31, 2013. As of the effective date of this AD, use only Lockheed Service Bulletin 093–53–105, Revision 3, dated May 31, 2013, for accomplishing the actions required by this paragraph. (i) For any crack found before the effective date of this AD: Within 2,500 flight cycles after finding the crack. (ii) For any crack found on or after the effective date of this AD: Before further flight after finding the crack. (2) If two or more adjacent fittings on both sides of the cracked fittings or bonded splice tabs/fasteners are determined to be free of cracks by the ECSS inspection required by paragraphs (j)(1) and (j)(2) of this AD, the follow-on inspection (i.e., BHEC, ECSS, and borescope inspections) of the inner and outer tee caps required by paragraph (j)(1) of this AD may also be deferred until the cracked fittings are replaced as required by paragraph (m)(1) of this AD, but no later than before the accumulation of 20,800 total flight cycles. (n) New Repetitive Borescope Inspections of Certain End Fittings and Corrective Actions For airplanes with a large (47-inch-wide) aft passenger door: At the later of the times specified in paragraphs (n)(1) and (n)(2) of this AD, do a borescope inspection for cracking of the stringer end fittings at stringer locations 12, 13, 53, and 54; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Lockheed Service Bulletin 093–53–105, Revision 3, dated May 31, 2013, except as specified in paragraph (p) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection of the stringer end fittings thereafter at intervals not to exceed 1,750 flight cycles until the actions required by paragraph (q) of this AD have been done. (1) Before the accumulation of 13,875 total flight cycles. (2) Within 365 days or 1,000 flight cycles after the effective date of this AD, whichever occurs earlier. (o) New Repetitive Borescope Inspections of Fuselage Skin Panels For airplanes with a large (47-inch-wide) aft passenger door: At the later of the times specified in paragraphs (o)(1) and (o)(2) of this AD, do an ECSS inspection for cracking of the left and right aft fuselage skin panels; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Lockheed Service Bulletin 093–53–105, Revision 3, dated May 31, 2013, except as specified in paragraph (p) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection of the aft fuselage skin panels thereafter at intervals not to exceed 1,750 flight cycles until the modification required by paragraph (q) of this AD is done. E:\FR\FM\09JNR1.SGM 09JNR1 Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations (1) Before the accumulation of 13,875 total flight cycles. (2) Within 365 days or 1,000 flight cycles after the effective date of this AD, whichever occurs first. (p) New Service Information Exception If any cracking is found during any inspection required by this AD, and Lockheed Service Bulletin 093–53–105, Revision 3, dated May 31, 2013, specifies contacting Lockheed for appropriate action: Before further flight, repair the cracking in accordance with a method approved by the Manager, Atlanta ACO, FAA. As of the effective date of this AD, for a repair method to be approved by the Manager, Atlanta ACO, as required by this paragraph, the Manager’s approval letter must specifically refer to this AD. (q) New Pre-Structural Modification Inspections and Structural Modification Before the accumulation of 20,800 total flight cycles: Do the applicable actions specified in paragraphs (q)(1) and (q)(2) of this AD. (1) Perform pre-structural modification inspections by doing the actions required by paragraphs (j), (n), and (o) of this AD. (2) Perform a structural modification of the aft pressure bulkhead by removing and replacing all stringer end fittings with new or refurbished fittings at stringers 1 through 14, and 52 through 64, in accordance with the Accomplishment Instructions of Lockheed Service Bulletin 093–53–105, Revision 3, dated May 31, 2013. (r) New Post-Structural Modification Repetitive Inspections Within 13,875 flight cycles after performing the actions required by paragraph (q)(2) of this AD: Do the actions specified in paragraphs (j), (n), and (o) of this AD, and repeat thereafter at intervals not to exceed 1,750 flight cycles. tkelley on DSK3SPTVN1PROD with RULES (s) No Reporting Requirement Although Lockheed Service Bulletin 093– 53–105, Revision 3, dated May 31, 2013, referenced in this AD specifies to submit certain information to the manufacturer, this AD does not include that requirement. (t) 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 paragraph (u) 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. Aircraft Certification Office (ACO), 1701 Columbia Avenue, College Park, GA 30337; phone: 404–474–5554; fax: 404–474–5605; email: carl.w.gray@faa.gov. DEPARTMENT OF TRANSPORTATION (v) Material Incorporated by Reference 14 CFR Part 39 (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on July 14, 2015. (i) Lockheed Service Bulletin 093–53–105, Revision 3, dated May 31, 2013 (The date of May 15, 2013, on page 1 of Lockheed Service Bulletin 093–53–105, Revision 3, dated May 31, 2013, is incorrect and should be May 31, 2013). (ii) Reserved. (4) The following service information was approved for IBR on January 11, 1996 (60 FR 66870, December 27, 1995). (i) Lockheed L–1011 Service Bulletin 093– 53–105, Revision 1, dated November 17, 1995. (ii) Reserved. (5) For Lockheed 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, GA 30063–0579; telephone 770–494–5444; fax 770–494–5445; email L1011.support@lmco.com; Internet http://www.lockheedmartin.com/ams/tools/ TechPubs.html. (6) You may view this service information at FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. [Docket No. FAA–2015–1937; Directorate Identifier 2014–SW–067–AD; Amendment 39–18171; AD 2015–11–08] Issued in Renton, Washington, on May 18, 2015. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. 15:56 Jun 08, 2015 Jkt 235001 Federal Aviation Administration RIN 2120–AA64 Airworthiness Directives; Agusta S.p.A. (Agusta) Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are superseding airworthiness directive (AD) 2014–02– 08 for Agusta Model A109C, A109S, A109K2, A109E, and AW109SP helicopters. AD 2014–02–08 required inspecting the lock wires securing the tail rotor (T/R) duplex bearing locking nut (locking nut) to determine whether any lock wires are missing or damaged. This AD retains some of the requirements of AD 2014–02–08 but removes the terminating action, expands the applicability, and adds a daily pilot check. This AD was prompted by reports of loosening T/R locking nuts. These actions are intended to prevent failure of the T/R and subsequent loss of control of the helicopter. DATES: This AD becomes effective June 24, 2015. We must receive comments on this AD by August 10, 2015. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. SUMMARY: [FR Doc. 2015–13325 Filed 6–8–15; 8:45 am] Examining the AD Docket BILLING CODE 4910–13–P You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the European Aviation Safety Agency (EASA) AD, the economic evaluation, any comments (u) Related Information For more information about this AD, contact Carl Gray, Aerospace Engineer, Airframe Branch, ACE–117A, FAA, Atlanta VerDate Sep<11>2014 32445 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\09JNR1.SGM 09JNR1

Agencies

[Federal Register Volume 80, Number 110 (Tuesday, June 9, 2015)]
[Rules and Regulations]
[Pages 32441-32445]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-13325]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0227; Directorate Identifier 2013-NM-211-AD; 
Amendment 39-18165; AD 2015-11-02]
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 Airworthiness Directive (AD) 95-26-11 for 
all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company 
Model L-1011 series airplanes. AD 95-26-11 required repetitive 
inspections to detect cracking of the fittings that attach the aft 
pressure bulkhead to the fuselage stringers, repetitive inspections to 
detect cracking of the fittings and of the splice tab of the aft 
pressure bulkhead, and corrective actions if necessary. This new AD 
requires repetitive inspections to detect cracking of the fittings that 
attach the aft pressure bulkhead to the fuselage stringers, repetitive 
inspections to detect cracking of the fittings and of the splice tab of 
the aft pressure bulkhead, repetitive inspections for cracking of

[[Page 32442]]

certain aft fuselage skin panels, a structural modification, a post-
modification inspection program, and corrective actions if necessary. 
This AD was prompted by a determination that the fittings at stringer 
attachments to the upper region of the aft pressure bulkhead are 
subject to widespread fatigue damage (WFD). We are issuing this AD to 
prevent simultaneous failure of multiple stringer end fittings through 
fatigue cracking at the aft pressure bulkhead, which could lead to 
rapid decompression of the airplane.

DATES: This AD is effective July 14, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of July 14, 
2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
January 11, 1996 (60 FR 668702, December 27, 1995).

ADDRESSES: 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, GA 30063-0579; telephone 770-494-5444; fax 770-494-5445; 
email L1011.support@lmco.com; Internet http://www.lockheedmartin.com/ams/tools/TechPubs.html. You may view this referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221. It is also available on the 
Internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2014-0227.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0227; 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 Docket 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, GA 30337; phone: 404-474-
5554; fax: 404-474-5605; email: carl.w.gray@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 to supersede AD 95-26-11, Amendment 39-9469 (60 FR 
66870, December 27, 1995). AD 95-26-11 applied to all Lockheed Martin 
Corporation/Lockheed Martin Aeronautics Company Model L-1011 series 
airplanes. The SNPRM published in the Federal Register on November 17, 
2014 (79 FR 68377). We preceded the SNPRM with a notice of proposed 
rulemaking (NPRM) that published in the Federal Register on April 14, 
2014 (79 FR 20819). The NPRM proposed to require repetitive inspections 
to detect cracking of the fittings that attach the aft pressure 
bulkhead to the fuselage stringers, repetitive inspections to detect 
cracking of the fittings and of the splice tab of the aft pressure 
bulkhead, repetitive inspections for cracking of certain aft fuselage 
skin panels, a structural modification, a post-modification inspection 
program, and corrective actions if necessary. The NPRM was prompted by 
a determination that the fittings at stringer attachments to the upper 
region of the aft pressure bulkhead are subject to WFD. The SNPRM 
proposed to reduce the post-structural modification repetitive 
inspection interval. We are issuing this AD to prevent simultaneous 
failure of multiple stringer end fittings through fatigue cracking at 
the aft pressure bulkhead, which could lead to rapid decompression of 
the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the SNPRM (79 FR 68377, November 
17, 2014) or on the determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
SNPRM (79 FR 68377, November 17, 2014) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM (79 FR 68377, November 17, 2014).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed Lockheed Service Bulletin 093-53-105, Revision 3, dated 
May 31, 2013. The service information describes procedures for 
inspections for cracking of the stringer end fittings at the aft 
pressure bulkhead, corrective actions, and a modification that includes 
replacement of the stringer end fittings of certain stringers with new 
fittings. This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section of this 
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
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                    Labor cost          Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspections [actions retained     23 work-hours x $85                 $0  $1,955 per          $50,830 per
 from AD 95-26-11, Amendment 39-   per hour = $1,955                       inspection cycle.   inspection cycle.
 9469 (60 FR 66870, December 27,   per inspection
 1995)].                           cycle.
Inspections and modification      185 work[dash]hours              6,750  $22,475...........  $584,350.
 [new action].                     x $85 per hour =
                                   $15,725.
----------------------------------------------------------------------------------------------------------------


[[Page 32443]]

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the inspections. We have 
no way of determining the number of aircraft that might need these 
replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                  Action                             Labor cost               Parts cost       Cost per product
----------------------------------------------------------------------------------------------------------------
Replacement of one fitting................  16 work-hour x $85 per hour                $250              $1,610
                                             = $1,360.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the other on-condition actions specified in this AD.

Authority for This Rulemaking

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

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (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) 
95-26-11, Amendment 39-9469 (60 FR 66870, December 27, 1995), and 
adding the following new AD:

2015-11-02 Lockheed Martin Corporation/Lockheed Martin Aeronautics 
Company: Amendment 39-18165 ; Docket No. FAA-2014-0227; Directorate 
Identifier 2013-NM-211-AD.

(a) Effective Date

    This AD is effective July 14, 2015.

(b) Affected ADs

    This AD replaces AD 95-26-11, Amendment 39-9469 (60 FR 66870, 
December 27, 1995).

(c) Applicability

    This AD applies to 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

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by a determination that the fittings at 
stringer attachments to the upper region of the aft pressure 
bulkhead are subject to widespread fatigue damage (WFD). We are 
issuing this AD to prevent simultaneous failure of multiple stringer 
end fittings through fatigue cracking at the aft pressure bulkhead, 
which could lead to rapid decompression of the airplane.

(f) Compliance

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

(g) Retained Detailed Visual Inspection

    This paragraph restates the requirements of paragraph (a) of AD 
95-26-11, Amendment 39-9469 (60 FR 66870, December 27, 1995), with 
no changes. Perform a detailed visual inspection to detect cracking 
of the fittings that attach the aft pressure bulkhead to the 
fuselage stringers (hereinafter referred to as ``fittings'') at 
stringers 1 through 10 (right side) and at stringers 56 through 64 
(left side), at the later of the times specified in either paragraph 
(g)(1) or (g)(2) of this AD.
    (1) Prior to the accumulation of 20,000 total flight cycles; or
    (2) Within the next 25 flight cycles or 10 days after September 
28, 1995 (the effective date of AD 95-18-52, Amendment 39-9366 (60 
FR 47465, September 13, 1995)), whichever occurs earlier.

(h) Retained Corrective Action for Cracked Fitting

    This paragraph restates the requirements of paragraph (c) of AD 
95-26-11, Amendment 39-9469 (60 FR 66870, December 27, 1995), with 
no changes. If any cracked fitting is detected during the inspection 
required by paragraph (g) of this AD: Before further flight, 
accomplish the requirements of paragraphs (h)(1) and (h)(2) of this 
AD.
    (1) Replace the cracked fitting with a new fitting, or with a 
serviceable fitting on which a detailed visual inspection has been 
performed previously to detect cracking and that has been found to 
be free of cracks.
    (2) Perform a detailed visual inspection to detect cracking in 
the radius at the lower end of the vertical leg of the bulkhead T-
shaped frame between the stringer locations on either side of the 
stringer having the cracked fitting. If any cracked T-shaped frame 
is detected: Before further flight, repair in accordance with a 
method approved by the Manager, Atlanta Aircraft Certification 
Office (ACO), FAA.

(i) Retained Repetitive Fitting Inspections

    This paragraph restates the requirements of paragraph (d) of AD 
95-26-11, Amendment 39-9469 (60 FR 66870, December 27, 1995), with 
no changes. Repeat the inspections and other necessary actions 
required by paragraphs (g) and (h) of this AD at intervals not to 
exceed 1,800 flight cycles or 3,000 flight hours, whichever occurs 
earlier, until paragraph (j) of this AD is accomplished.

(j) Retained Eddy Current Surface Scan (ECSS) Inspections, and Related 
Investigative and Corrective Actions

    This paragraph restates the requirements of paragraph (e) of AD 
95-26-11, Amendment 39-9469 (60 FR 66870, December 27, 1995), with 
revised compliance times specified in paragraph (k) of this AD, 
exclusion of an ECSS inspection for certain airplanes, and new 
service information. Except as provided by paragraph (l) of this AD: 
At the applicable time specified in paragraph (k)(1) of this AD, 
accomplish the requirements of paragraphs

[[Page 32444]]

(j)(1) and (j)(2) of this AD. Repeat the ECSS inspections thereafter 
at the compliance time specified in paragraph (k)(2) of this AD. 
Accomplishment of the ECSS inspection constitutes terminating action 
for the repetitive inspection requirements of paragraph (i) of this 
AD.
    (1) Perform an ECSS inspection to detect cracking of the 
fittings at stringers 1 through 14 (right side) and at stringers 52 
through 64 (left side), in accordance with the Accomplishment 
Instructions of Lockheed L-1011 Service Bulletin 093-53-105, 
Revision 1, dated November 17, 1995; or Lockheed Service Bulletin 
093-53-105, Revision 3, dated May 31, 2013; except for airplanes 
with a large (47-inch-wide) aft passenger door, an ECSS inspection 
of stringers 12, 13, 53, and 54 is not required by this paragraph. 
Except as provided by paragraph (m) of this AD, if any cracking is 
detected, prior to further flight, replace the fitting with a new 
fitting without pilot holes, rework the fitting, and perform various 
follow-on actions (i.e., bolt hole eddy current (BHEC), ECSS, and 
borescope inspections; and repair) of the inner and outer tee caps, 
in accordance with the Accomplishment Instructions of Lockheed L-
1011 Service Bulletin 093-53-105, Revision 1, dated November 17, 
1995; or Lockheed Service Bulletin 093-53-105, Revision 3, dated May 
31, 2013, except as required by paragraph (p) of this AD. As of the 
effective date of this AD, use only Lockheed Service Bulletin 093-
53-105, Revision 3, dated May 31, 2013, for accomplishing the 
actions required by this paragraph.
    (2) Perform an ECSS inspection to detect cracking of the lower 
(or inner) surface of the upper bonded splice tab of the bulkhead 
assembly at stringers 1 through 14 (right side) and at stringers 52 
through 64 (left side), in accordance with the Accomplishment 
Instructions of Lockheed L-1011 Service Bulletin 093-53-105, 
Revision 1, dated November 17, 1995; or Lockheed Service Bulletin 
093-53-105, Revision 3, dated May 31, 2013. As of the effective date 
of this AD, use only Lockheed Service Bulletin 093-53-105, Revision 
3, dated May 31, 2013, for accomplishing the actions required by 
this paragraph.
    (i) Except as provided by paragraph (m) of this AD, if any 
cracking is detected at the upper bonded splice tab, repair in 
accordance with a method approved by the Manager, Atlanta ACO, FAA.
    (ii) Except as provided by paragraph (m) of this AD, if any 
cracking is detected at a fastener, prior to further flight, perform 
a BHEC inspection to detect cracking of the forward flange of the 
inner tee cap, in accordance with the Accomplishment Instructions of 
Lockheed L-1011 Service Bulletin 093-53-105, Revision 1, dated 
November 17, 1995; or Lockheed Service Bulletin 093-53-105, Revision 
3, dated May 31, 2013. If any cracking is detected, prior to further 
flight, repair in accordance with the Accomplishment Instructions of 
Lockheed L-1011 Service Bulletin 093-53-105, Revision 1, dated 
November 17, 1995; or Lockheed Service Bulletin 093-53-105, Revision 
3, dated May 31, 2013, except as required by paragraph (p) of this 
AD. As of the effective date of this AD, use only Lockheed Service 
Bulletin 093-53-105, Revision 3, dated May 31, 2013, for 
accomplishing the actions required by this paragraph.

(k) New Revised Compliance Times for Paragraph (j) of This AD

    (1) Do the initial inspections required by paragraph (j) of this 
AD at the earlier of the times specified in paragraphs (k)(1)(i) and 
(k)(1)(ii) of this AD.
    (i) Prior to the accumulation of 20,000 total flight cycles, or 
within 30 days after January 11, 1996 (the effective date of date of 
AD 95-26-11, Amendment 39-9469 (60 FR 66870, December 27, 1995)), 
whichever occurs later.
    (ii) At the later of the times specified in paragraphs 
(k)(1)(ii)(A) and (k)(1)(ii)(B) of this AD.
    (A) Before the accumulation of 13,875 total flight cycles.
    (B) Within 365 days or 1,000 flight cycles after the effective 
date of this AD, whichever occurs first.
    (2) Repeat the inspections specified in paragraph (j) of this AD 
within 2,500 flight cycles after accomplishing the most recent 
inspection required by paragraph (j) of this AD, and repeat the 
inspection thereafter at intervals not to exceed 1,750 flight 
cycles.

(l) Retained Inspection Deferral for Paragraph (j) of This AD

    This paragraph restates the requirements of paragraph (f) of AD 
95-26-11, Amendment 39-9469 (60 FR 66870, December 27, 1995). 
Accomplishment of the initial ECSS inspections required by paragraph 
(j) of this AD may be deferred to a date within 120 days after 
January 11, 1996 (the effective date of date of AD 95-26-11), 
provided that, in the interim, a visual inspection as specified in 
paragraph (g) of this AD is accomplished within 30 days after 
January 11, 1996 (the effective date of date of AD 95-26-11), and 
repeated thereafter at intervals not to exceed 50 flight cycles. 
Once the ECSS inspections begin, the visual inspections may be 
terminated.

(m) Retained Inspection Deferral With Revised Compliance Time and New 
Deferral

    This paragraph restates the requirements of paragraph (g) of AD 
95-26-11, Amendment 39-9469 (60 FR 66870, December 27, 1995), with a 
revised compliance time, service information, and a new deferred 
action. As of the effective date of this AD, the deferral specified 
in paragraphs (m)(1) and (m)(2) of this AD cannot be done. If 
cracking was found before the effective date of this AD, the 
deferral specified in paragraphs (m)(1) and (m)(2) of this AD may be 
done. (1) If two or more adjacent fittings on both sides of the 
cracked fittings or bonded splice tabs/fasteners are determined to 
be free of cracks by the ECSS inspection required by paragraphs 
(j)(1) and (j)(2) of this AD, repeat the ECSS inspection of the 
adjacent fittings thereafter at intervals not to exceed 600 flight 
cycles until the cracked fittings or splice tabs/fasteners are 
replaced or repaired, in accordance with the Accomplishment 
Instructions of Lockheed L-1011 Service Bulletin 093-53-105, 
Revision 1, dated November 17, 1995; or Lockheed Service Bulletin 
093-53-105, Revision 3, dated May 31, 2013. At the applicable time 
specified in paragraphs (m)(1)(i) and (m)(1)(ii) of this AD: Replace 
the cracked fitting and/or splice tab/fasteners, in accordance with 
the Accomplishment Instructions of Lockheed L-1011 Service Bulletin 
093-53-105, Revision 1, dated November 17, 1995; or Lockheed Service 
Bulletin 093-53-105, Revision 3, dated May 31, 2013. As of the 
effective date of this AD, use only Lockheed Service Bulletin 093-
53-105, Revision 3, dated May 31, 2013, for accomplishing the 
actions required by this paragraph.
    (i) For any crack found before the effective date of this AD: 
Within 2,500 flight cycles after finding the crack.
    (ii) For any crack found on or after the effective date of this 
AD: Before further flight after finding the crack.
    (2) If two or more adjacent fittings on both sides of the 
cracked fittings or bonded splice tabs/fasteners are determined to 
be free of cracks by the ECSS inspection required by paragraphs 
(j)(1) and (j)(2) of this AD, the follow-on inspection (i.e., BHEC, 
ECSS, and borescope inspections) of the inner and outer tee caps 
required by paragraph (j)(1) of this AD may also be deferred until 
the cracked fittings are replaced as required by paragraph (m)(1) of 
this AD, but no later than before the accumulation of 20,800 total 
flight cycles.

(n) New Repetitive Borescope Inspections of Certain End Fittings and 
Corrective Actions

    For airplanes with a large (47-inch-wide) aft passenger door: At 
the later of the times specified in paragraphs (n)(1) and (n)(2) of 
this AD, do a borescope inspection for cracking of the stringer end 
fittings at stringer locations 12, 13, 53, and 54; and do all 
applicable related investigative and corrective actions; in 
accordance with the Accomplishment Instructions of Lockheed Service 
Bulletin 093-53-105, Revision 3, dated May 31, 2013, except as 
specified in paragraph (p) of this AD. Do all applicable related 
investigative and corrective actions before further flight. Repeat 
the inspection of the stringer end fittings thereafter at intervals 
not to exceed 1,750 flight cycles until the actions required by 
paragraph (q) of this AD have been done.
    (1) Before the accumulation of 13,875 total flight cycles.
    (2) Within 365 days or 1,000 flight cycles after the effective 
date of this AD, whichever occurs earlier.

(o) New Repetitive Borescope Inspections of Fuselage Skin Panels

    For airplanes with a large (47-inch-wide) aft passenger door: At 
the later of the times specified in paragraphs (o)(1) and (o)(2) of 
this AD, do an ECSS inspection for cracking of the left and right 
aft fuselage skin panels; and do all applicable related 
investigative and corrective actions; in accordance with the 
Accomplishment Instructions of Lockheed Service Bulletin 093-53-105, 
Revision 3, dated May 31, 2013, except as specified in paragraph (p) 
of this AD. Do all applicable related investigative and corrective 
actions before further flight. Repeat the inspection of the aft 
fuselage skin panels thereafter at intervals not to exceed 1,750 
flight cycles until the modification required by paragraph (q) of 
this AD is done.

[[Page 32445]]

    (1) Before the accumulation of 13,875 total flight cycles.
    (2) Within 365 days or 1,000 flight cycles after the effective 
date of this AD, whichever occurs first.

(p) New Service Information Exception

    If any cracking is found during any inspection required by this 
AD, and Lockheed Service Bulletin 093-53-105, Revision 3, dated May 
31, 2013, specifies contacting Lockheed for appropriate action: 
Before further flight, repair the cracking in accordance with a 
method approved by the Manager, Atlanta ACO, FAA. As of the 
effective date of this AD, for a repair method to be approved by the 
Manager, Atlanta ACO, as required by this paragraph, the Manager's 
approval letter must specifically refer to this AD.

(q) New Pre-Structural Modification Inspections and Structural 
Modification

    Before the accumulation of 20,800 total flight cycles: Do the 
applicable actions specified in paragraphs (q)(1) and (q)(2) of this 
AD.
    (1) Perform pre-structural modification inspections by doing the 
actions required by paragraphs (j), (n), and (o) of this AD.
    (2) Perform a structural modification of the aft pressure 
bulkhead by removing and replacing all stringer end fittings with 
new or refurbished fittings at stringers 1 through 14, and 52 
through 64, in accordance with the Accomplishment Instructions of 
Lockheed Service Bulletin 093-53-105, Revision 3, dated May 31, 
2013.

(r) New Post-Structural Modification Repetitive Inspections

    Within 13,875 flight cycles after performing the actions 
required by paragraph (q)(2) of this AD: Do the actions specified in 
paragraphs (j), (n), and (o) of this AD, and repeat thereafter at 
intervals not to exceed 1,750 flight cycles.

(s) No Reporting Requirement

    Although Lockheed Service Bulletin 093-53-105, Revision 3, dated 
May 31, 2013, referenced in this AD specifies to submit certain 
information to the manufacturer, this AD does not include that 
requirement.

(t) 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 paragraph 
(u) 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.

 (u) Related Information

    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, GA 
30337; phone: 404-474-5554; fax: 404-474-5605; email: 
carl.w.gray@faa.gov.

(v) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
July 14, 2015.
    (i) Lockheed Service Bulletin 093-53-105, Revision 3, dated May 
31, 2013 (The date of May 15, 2013, on page 1 of Lockheed Service 
Bulletin 093-53-105, Revision 3, dated May 31, 2013, is incorrect 
and should be May 31, 2013).
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
January 11, 1996 (60 FR 66870, December 27, 1995).
    (i) Lockheed L-1011 Service Bulletin 093-53-105, Revision 1, 
dated November 17, 1995.
    (ii) Reserved.
    (5) For Lockheed 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, GA 30063-0579; telephone 770-494-5444; 
fax 770-494-5445; email L1011.support@lmco.com; Internet http://www.lockheedmartin.com/ams/tools/TechPubs.html.
    (6) You may view this service information at FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on May 18, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-13325 Filed 6-8-15; 8:45 am]
 BILLING CODE 4910-13-P