80 FR 32441 - Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 110 (June 9, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 110 (June 9, 2015)
| Page Range | 32441-32445 | |
| FR Document | 2015-13325 |
[Federal Register Volume 80, Number 110 (Tuesday, June 9, 2015)] [Rules and Regulations] [Pages 32441-32445] From the Federal Register Online [www.thefederalregister.org] [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 [email protected]; 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: [email protected]. 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: [email protected]. (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 [email protected]; 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
![Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations 32441
The woven composite fan blades are failure, a centrifugal load equal to two meet the requirements of § 33.75
a novel and unusual design feature that times the maximum load the retention following a lightning strike on the
requires additional airworthiness system could experience within composite fan blade structure, but that
standards for type certification of the approved engine operating limitations. the lightning strike will not cause
LEAP–1A and –1C engine models. The fan blade retention system includes damage to the fan blades that would
the portion of the fan blade from the prevent continued safe operation of the
Discussion of Comments inner annulus flow path line inward to affected engine.
A notice of proposed special the blade dovetail, the blade retention (g) Account for the effects of in-
conditions, No. 33–14–02–SC, for the components, and the fan disk and fan service deterioration, manufacturing
CFM LEAP–1A and—1C engine models blade attachment features. variations, minimum material
was published in the Federal Register (c) Using a procedure approved by the properties, and environmental effects
on Friday, November 14, 2014 (79 FR FAA, establish an operating limitation during the tests and analyses required
68137). No comments were received and that specifies the maximum allowable by paragraphs (a), (b), (c), (d), (e), and
the special conditions are adopted as number of start-stop stress cycles for the (f) of these special conditions.
proposed. fan blade retention system. The life (h) Propose fleet leader monitoring
evaluation must include the combined and field sampling programs that will
Applicability effects of high-cycle and low-cycle monitor the effects of engine fan blade
As discussed above, these special fatigue. If the operating limitation is less usage and fan blade retention system
conditions are applicable to the LEAP than 100,000 cycles, that limitation integrity.
–1A and –1C engine models. Should must be specified in Chapter 5 of the (i) Mark each fan blade legibly and
CFM apply at a later date for a change Engine Manual Airworthiness permanently with a part number and a
to the type certificate to include another Limitations Section. The procedure serial number.
model on the same type certificate used to establish the maximum
incorporating the same novel or unusual allowable number of start-stop stress Issued in Burlington, Massachusetts, on
June 1, 2015.
design feature, the special conditions cycles for the fan blade retention system
would apply to that model as well. will incorporate the integrity Ann C. Mollica,
requirements in paragraphs (c)(1), (c)(2), Acting Manager, Engine and Propeller
Conclusion Directorate, Aircraft Certification Service.
and (c)(3) of these special conditions for
This action affects only certain novel the fan blade retention system. [FR Doc. 2015–14084 Filed 6–8–15; 8:45 am]
or unusual design features on LEAP–1A (1) An engineering plan, which BILLING CODE 4910–13–P
and –1C engine models. It is not a rule establishes and maintains that the
of general applicability and applies only combinations of loads, material
to CFM, who requested FAA approval of properties, environmental influences, DEPARTMENT OF TRANSPORTATION
this engine feature. and operating conditions, including the
Federal Aviation Administration
List of Subjects in 14 CFR Part 33 effects of parts influencing these
parameters, are well known or
Aircraft, Engines, Aviation Safety, 14 CFR Part 39
predictable through validated analysis,
Reporting and recordkeeping test, or service experience. [Docket No. FAA–2014–0227; Directorate
requirements. (2) A manufacturing plan that Identifier 2013–NM–211–AD; Amendment
The authority citation for these identifies the specific manufacturing 39–18165; AD 2015–11–02]
special conditions is as follows: constraints necessary to consistently RIN 2120–AA64
Authority: 49 U.S.C. 106(g), 40113, 44701, produce the fan blade retention system
44702, 44704. with the attributes required by the Airworthiness Directives; Lockheed
engineering plan. Martin Corporation/Lockheed Martin
The Special Conditions (3) A service management plan that Aeronautics Company Airplanes
Accordingly, pursuant to the defines in-service processes for
authority delegated to me by the maintenance and repair of the fan blade AGENCY: Federal Aviation
Administrator, the following special retention system, which will maintain Administration (FAA), DOT.
conditions are issued as part of the type attributes consistent with those required ACTION: Final rule.
certification basis for CFM LEAP–1A by the engineering plan.
and –1C engine models. (d) Substantiate by test and analysis, SUMMARY: We are superseding
or other methods acceptable to the FAA, Airworthiness Directive (AD) 95–26–11
1. Part 33, Requirements that the blade design below the inner for all Lockheed Martin Corporation/
In addition to the airworthiness annulus flow path line provides Lockheed Martin Aeronautics Company
standards in 14 CFR part 33, effective multiple load paths and crack arresting Model L–1011 series airplanes. AD 95–
February 1, 1965, with Amendments features that prevent delamination or 26–11 required repetitive inspections to
33–1 through 33–32 applicable to the crack propagation to blade failure detect cracking of the fittings that attach
LEAP–1A and –1C engine models, CFM during the life of the blade. the aft pressure bulkhead to the fuselage
will: (e) Substantiate that during the stringers, repetitive inspections to detect
(a) Conduct an engine fan blade service life of the engine, the total cracking of the fittings and of the splice
containment test with the fan blade probability of an individual blade tab of the aft pressure bulkhead, and
failing at the inner annulus flow path retention system failure resulting from corrective actions if necessary. This new
line instead of at the outermost all possible causes, as defined in AD requires repetitive inspections to
tkelley on DSK3SPTVN1PROD with RULES
retention groove. § 33.75, will be extremely improbable detect cracking of the fittings that attach
(b) Substantiate by test and analysis, with a cumulative calculated probability the aft pressure bulkhead to the fuselage
or other methods acceptable to the FAA, of failure of less than 10¥9 per engine stringers, repetitive inspections to detect
that a fan disk and fan blade retention flight hour. cracking of the fittings and of the splice
system with minimum material (f) Substantiate by test or analysis that tab of the aft pressure bulkhead,
properties can withstand, without not only will the engine continue to repetitive inspections for cracking of
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![32442 Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations
certain aft fuselage skin panels, a contains this AD, the regulatory through fatigue cracking at the aft
structural modification, a post- evaluation, any comments received, and pressure bulkhead, which could lead to
modification inspection program, and other information. The address for the rapid decompression of the airplane.
corrective actions if necessary. This AD Docket Office (phone: 800–647–5527) is
Comments
was prompted by a determination that Docket Management Facility, U.S.
the fittings at stringer attachments to the Department of Transportation, Docket We gave the public the opportunity to
upper region of the aft pressure Operations, M–30, West Building participate in developing this AD. We
bulkhead are subject to widespread Ground Floor, Room W12–140, 1200 received no comments on the SNPRM
fatigue damage (WFD). We are issuing New Jersey Avenue SE., Washington, (79 FR 68377, November 17, 2014) or on
this AD to prevent simultaneous failure DC 20590. the determination of the cost to the
of multiple stringer end fittings through FOR FURTHER INFORMATION CONTACT: Carl public.
fatigue cracking at the aft pressure Gray, Aerospace Engineer, Airframe Conclusion
bulkhead, which could lead to rapid Branch, ACE–117A, FAA, Atlanta
decompression of the airplane. Aircraft Certification Office (ACO), 1701 We reviewed the relevant data and
DATES: This AD is effective July 14, Columbia Avenue, College Park, GA determined that air safety and the
2015. 30337; phone: 404–474–5554; fax: 404– public interest require adopting this AD
The Director of the Federal Register 474–5605; email: carl.w.gray@faa.gov. as proposed except for minor editorial
approved the incorporation by reference SUPPLEMENTARY INFORMATION: changes. We have determined that these
of a certain publication listed in this AD minor changes:
as of July 14, 2015. Discussion • Are consistent with the intent that
The Director of the Federal Register We issued a supplemental notice of was proposed in the SNPRM (79 FR
approved the incorporation by reference proposed rulemaking (SNPRM) to 68377, November 17, 2014) for
of a certain other publication listed in amend 14 CFR part 39 to supersede AD correcting the unsafe condition; and
this AD as of January 11, 1996 (60 FR 95–26–11, Amendment 39–9469 (60 FR • Do not add any additional burden
668702, December 27, 1995). 66870, December 27, 1995). AD 95–26– upon the public than was already
ADDRESSES: For service information 11 applied to all Lockheed Martin proposed in the SNPRM (79 FR 68377,
identified in this AD, contact Lockheed Corporation/Lockheed Martin November 17, 2014).
Martin Corporation/Lockheed Martin Aeronautics Company Model L–1011 We also determined that these
Aeronautics Company, L1011 Technical series airplanes. The SNPRM published changes will not increase the economic
Support Center, Dept. 6A4M, Zone in the Federal Register on November 17, burden on any operator or increase the
0579, 86 South Cobb Drive, Marietta, 2014 (79 FR 68377). We preceded the scope of this AD.
GA 30063–0579; telephone 770–494– SNPRM with a notice of proposed
Related Service Information Under 1
5444; fax 770–494–5445; email rulemaking (NPRM) that published in
CFR Part 51
L1011.support@lmco.com; Internet the Federal Register on April 14, 2014
http://www.lockheedmartin.com/ams/ (79 FR 20819). The NPRM proposed to We reviewed Lockheed Service
tools/TechPubs.html. You may view this require repetitive inspections to detect Bulletin 093–53–105, Revision 3, dated
referenced service information at the cracking of the fittings that attach the aft May 31, 2013. The service information
FAA, Transport Airplane Directorate, pressure bulkhead to the fuselage describes procedures for inspections for
1601 Lind Avenue SW., Renton, WA. stringers, repetitive inspections to detect cracking of the stringer end fittings at
For information on the availability of cracking of the fittings and of the splice the aft pressure bulkhead, corrective
this material at the FAA, call 425–227– tab of the aft pressure bulkhead, actions, and a modification that
1221. It is also available on the Internet repetitive inspections for cracking of includes replacement of the stringer end
at http://www.regulations.gov by certain aft fuselage skin panels, a fittings of certain stringers with new
searching for and locating Docket No. structural modification, a post- fittings. This service information is
FAA–2014–0227. modification inspection program, and reasonably available because the
corrective actions if necessary. The interested parties have access to it
Examining the AD Docket NPRM was prompted by a through their normal course of business
You may examine the AD docket on determination that the fittings at stringer or by the means identified in the
the Internet at http:// attachments to the upper region of the ADDRESSES section of this AD.
www.regulations.gov by searching for aft pressure bulkhead are subject to
Costs of Compliance
and locating Docket No. FAA–2014– WFD. The SNPRM proposed to reduce
0227; or in person at the Docket the post-structural modification We estimate that this AD affects 26
Management Facility between 9 a.m. repetitive inspection interval. We are airplanes of U.S. registry.
and 5 p.m., Monday through Friday, issuing this AD to prevent simultaneous We estimate the following costs to
except Federal holidays. The AD docket failure of multiple stringer end fittings 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 × $85 per $0 $1,955 per inspection cycle $50,830 per inspection
from AD 95–26–11, hour = $1,955 per inspec- cycle.
tkelley on DSK3SPTVN1PROD with RULES
Amendment 39–9469 (60 tion cycle.
FR 66870, December 27,
1995)].
Inspections and modification 185 work-hours × $85 per 6,750 $22,475 ................................ $584,350.
[new action]. hour = $15,725.
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![Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations 32443
We estimate the following costs to do be required based on the results of the determining the number of aircraft that
any necessary replacements that would inspections. We have no way of 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 Adoption of the Amendment with no changes. Perform a detailed visual
that would enable us to provide cost inspection to detect cracking of the fittings
Accordingly, under the authority that attach the aft pressure bulkhead to the
estimates for the other on-condition delegated to me by the Administrator, fuselage stringers (hereinafter referred to as
actions specified in this AD. the FAA amends 14 CFR part 39 as ‘‘fittings’’) at stringers 1 through 10 (right
Authority for This Rulemaking follows: side) and at stringers 56 through 64 (left
side), at the later of the times specified in
Title 49 of the United States Code PART 39—AIRWORTHINESS either paragraph (g)(1) or (g)(2) of this AD.
specifies the FAA’s authority to issue DIRECTIVES (1) Prior to the accumulation of 20,000
rules on aviation safety. Subtitle I, total flight cycles; or
section 106, describes the authority of ■ 1. The authority citation for part 39 (2) Within the next 25 flight cycles or 10
the FAA Administrator. Subtitle VII: continues to read as follows: days after September 28, 1995 (the effective
Aviation Programs, describes in more date of AD 95–18–52, Amendment 39–9366
Authority: 49 U.S.C. 106(g), 40113, 44701. (60 FR 47465, September 13, 1995)),
detail the scope of the Agency’s whichever occurs earlier.
authority. § 39.13 [Amended]
We are issuing this rulemaking under ■ 2. The FAA amends § 39.13 by (h) Retained Corrective Action for Cracked
the authority described in Subtitle VII, removing Airworthiness Directive (AD) Fitting
Part A, Subpart III, Section 44701: 95–26–11, Amendment 39–9469 (60 FR This paragraph restates the requirements of
‘‘General requirements.’’ Under that 66870, December 27, 1995), and adding paragraph (c) of AD 95–26–11, Amendment
section, Congress charges the FAA with the following new AD: 39–9469 (60 FR 66870, December 27, 1995),
promoting safe flight of civil aircraft in with no changes. If any cracked fitting is
2015–11–02 Lockheed Martin Corporation/ detected during the inspection required by
air commerce by prescribing regulations Lockheed Martin Aeronautics Company: paragraph (g) of this AD: Before further flight,
for practices, methods, and procedures Amendment 39–18165 ; Docket No. accomplish the requirements of paragraphs
the Administrator finds necessary for FAA–2014–0227; Directorate Identifier (h)(1) and (h)(2) of this AD.
safety in air commerce. This regulation 2013–NM–211–AD. (1) Replace the cracked fitting with a new
is within the scope of that authority (a) Effective Date fitting, or with a serviceable fitting on which
because it addresses an unsafe condition a detailed visual inspection has been
This AD is effective July 14, 2015.
that is likely to exist or develop on performed previously to detect cracking and
products identified in this rulemaking (b) Affected ADs that has been found to be free of cracks.
This AD replaces AD 95–26–11, (2) Perform a detailed visual inspection to
action. detect cracking in the radius at the lower end
Amendment 39–9469 (60 FR 66870,
Regulatory Findings December 27, 1995). of the vertical leg of the bulkhead T-shaped
frame between the stringer locations on
This AD will not have federalism (c) Applicability either side of the stringer having the cracked
implications under Executive Order This AD applies to all Lockheed Martin fitting. If any cracked T-shaped frame is
13132. This AD will not have a Corporation/Lockheed Martin Aeronautics detected: Before further flight, repair in
substantial direct effect on the States, on Company Model L–1011–385–1, L–1011– accordance with a method approved by the
the relationship between the national 385–1–14, L–1011–385–1–15, and L–1011– Manager, Atlanta Aircraft Certification Office
government and the States, or on the 385–3 airplanes, certificated in any category. (ACO), FAA.
distribution of power and (d) Subject (i) Retained Repetitive Fitting Inspections
responsibilities among the various This paragraph restates the requirements of
Air Transport Association (ATA) of
levels of government. America Code 53, Fuselage. paragraph (d) of AD 95–26–11, Amendment
For the reasons discussed above, I 39–9469 (60 FR 66870, December 27, 1995),
certify that this AD: (e) Unsafe Condition with no changes. Repeat the inspections and
(1) Is not a ‘‘significant regulatory This AD was prompted by a determination other necessary actions required by
action’’ under Executive Order 12866, that the fittings at stringer attachments to the paragraphs (g) and (h) of this AD at intervals
(2) Is not a ‘‘significant rule’’ under upper region of the aft pressure bulkhead are not to exceed 1,800 flight cycles or 3,000
subject to widespread fatigue damage (WFD). flight hours, whichever occurs earlier, until
DOT Regulatory Policies and Procedures paragraph (j) of this AD is accomplished.
We are issuing this AD to prevent
(44 FR 11034, February 26, 1979), simultaneous failure of multiple stringer end
(3) Will not affect intrastate aviation (j) Retained Eddy Current Surface Scan
fittings through fatigue cracking at the aft (ECSS) Inspections, and Related
in Alaska, and pressure bulkhead, which could lead to rapid
(4) Will not have a significant Investigative and Corrective Actions
decompression of the airplane.
economic impact, positive or negative, This paragraph restates the requirements of
(f) Compliance paragraph (e) of AD 95–26–11, Amendment
on a substantial number of small entities
under the criteria of the Regulatory Comply with this AD within the 39–9469 (60 FR 66870, December 27, 1995),
tkelley on DSK3SPTVN1PROD with RULES
compliance times specified, unless already with revised compliance times specified in
Flexibility Act. paragraph (k) of this AD, exclusion of an
done.
List of Subjects in 14 CFR Part 39 ECSS inspection for certain airplanes, and
(g) Retained Detailed Visual Inspection new service information. Except as provided
Air transportation, Aircraft, Aviation This paragraph restates the requirements of by paragraph (l) of this AD: At the applicable
safety, Incorporation by reference, paragraph (a) of AD 95–26–11, Amendment time specified in paragraph (k)(1) of this AD,
Safety. 39–9469 (60 FR 66870, December 27, 1995), accomplish the requirements of paragraphs
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(1) Before the accumulation of 13,875 total Aircraft Certification Office (ACO), 1701 DEPARTMENT OF TRANSPORTATION
flight cycles. Columbia Avenue, College Park, GA 30337;
(2) Within 365 days or 1,000 flight cycles phone: 404–474–5554; fax: 404–474–5605; Federal Aviation Administration
after the effective date of this AD, whichever email: carl.w.gray@faa.gov.
occurs first.
(v) Material Incorporated by Reference
14 CFR Part 39
(p) New Service Information Exception
(1) The Director of the Federal Register [Docket No. FAA–2015–1937; Directorate
If any cracking is found during any Identifier 2014–SW–067–AD; Amendment
inspection required by this AD, and approved the incorporation by reference
39–18171; AD 2015–11–08]
Lockheed Service Bulletin 093–53–105, (IBR) of the service information listed in this
Revision 3, dated May 31, 2013, specifies paragraph under 5 U.S.C. 552(a) and 1 CFR RIN 2120–AA64
contacting Lockheed for appropriate action: part 51.
Before further flight, repair the cracking in (2) You must use this service information Airworthiness Directives; Agusta
accordance with a method approved by the as applicable to do the actions required by S.p.A. (Agusta) Helicopters
Manager, Atlanta ACO, FAA. As of the this AD, unless the AD specifies otherwise.
effective date of this AD, for a repair method AGENCY: Federal Aviation
(3) The following service information was
to be approved by the Manager, Atlanta ACO, approved for IBR on July 14, 2015.
Administration (FAA), DOT.
as required by this paragraph, the Manager’s ACTION: Final rule; request for
(i) Lockheed Service Bulletin 093–53–105,
approval letter must specifically refer to this comments.
AD. Revision 3, dated May 31, 2013 (The date of
May 15, 2013, on page 1 of Lockheed Service
(q) New Pre-Structural Modification Bulletin 093–53–105, Revision 3, dated May
SUMMARY: We are superseding
Inspections and Structural Modification 31, 2013, is incorrect and should be May 31,
airworthiness directive (AD) 2014–02–
Before the accumulation of 20,800 total 2013). 08 for Agusta Model A109C, A109S,
flight cycles: Do the applicable actions (ii) Reserved. A109K2, A109E, and AW109SP
specified in paragraphs (q)(1) and (q)(2) of (4) The following service information was helicopters. AD 2014–02–08 required
this AD. approved for IBR on January 11, 1996 (60 FR inspecting the lock wires securing the
(1) Perform pre-structural modification tail rotor (T/R) duplex bearing locking
66870, December 27, 1995).
inspections by doing the actions required by nut (locking nut) to determine whether
paragraphs (j), (n), and (o) of this AD. (i) Lockheed L–1011 Service Bulletin 093–
53–105, Revision 1, dated November 17, any lock wires are missing or damaged.
(2) Perform a structural modification of the
aft pressure bulkhead by removing and 1995. This AD retains some of the
replacing all stringer end fittings with new or (ii) Reserved. requirements of AD 2014–02–08 but
refurbished fittings at stringers 1 through 14, (5) For Lockheed service information removes the terminating action, expands
and 52 through 64, in accordance with the identified in this AD, contact Lockheed the applicability, and adds a daily pilot
Accomplishment Instructions of Lockheed Martin Corporation/Lockheed Martin check. This AD was prompted by
Service Bulletin 093–53–105, Revision 3, Aeronautics Company, L1011 Technical reports of loosening T/R locking nuts.
dated May 31, 2013. Support Center, Dept. 6A4M, Zone 0579, 86 These actions are intended to prevent
(r) New Post-Structural Modification South Cobb Drive, Marietta, GA 30063–0579; failure of the T/R and subsequent loss
Repetitive Inspections telephone 770–494–5444; fax 770–494–5445; of control of the helicopter.
Within 13,875 flight cycles after email L1011.support@lmco.com; Internet DATES: This AD becomes effective June
performing the actions required by paragraph http://www.lockheedmartin.com/ams/tools/ 24, 2015.
(q)(2) of this AD: Do the actions specified in TechPubs.html. We must receive comments on this
paragraphs (j), (n), and (o) of this AD, and (6) You may view this service information AD by August 10, 2015.
repeat thereafter at intervals not to exceed at FAA, Transport Airplane Directorate, 1601
1,750 flight cycles. ADDRESSES: You may send comments by
Lind Avenue SW., Renton, WA. For
any of the following methods:
(s) No Reporting Requirement information on the availability of this
• Federal eRulemaking Docket: Go to
Although Lockheed Service Bulletin 093– material at the FAA, call 425–227–1221.
http://www.regulations.gov. Follow the
53–105, Revision 3, dated May 31, 2013, (7) You may view this service information
online instructions for sending your
referenced in this AD specifies to submit that is incorporated by reference at the
comments electronically.
certain information to the manufacturer, this National Archives and Records
AD does not include that requirement. Administration (NARA). For information on
• Fax: 202–493–2251.
the availability of this material at NARA, call
• Mail: Send comments to the U.S.
(t) Alternative Methods of Compliance Department of Transportation, Docket
(AMOCs) 202–741–6030, or go to: http://
www.archives.gov/federal-register/cfr/ibr- Operations, M–30, West Building
(1) The Manager, Atlanta ACO, FAA, has Ground Floor, Room W12–140, 1200
locations.html.
the authority to approve AMOCs for this AD, New Jersey Avenue SE., Washington,
if requested using the procedures found in 14 Issued in Renton, Washington, on May 18, DC 20590–0001.
CFR 39.19. In accordance with 14 CFR 39.19, 2015. • Hand Delivery: Deliver to the
send your request to your principal inspector
John P. Piccola, Jr., ‘‘Mail’’ address between 9 a.m. and 5
or local Flight Standards District Office, as
appropriate. If sending information directly Acting Manager, Transport Airplane p.m., Monday through Friday, except
to the manager of the ACO, send it to the Directorate, Aircraft Certification Service. Federal holidays.
attention of the person identified in [FR Doc. 2015–13325 Filed 6–8–15; 8:45 am]
Examining the AD Docket
paragraph (u) of this AD. BILLING CODE 4910–13–P
(2) Before using any approved AMOC, You may examine the AD docket on
notify your appropriate principal inspector, the Internet at http://
or lacking a principal inspector, the manager www.regulations.gov or in person at the
tkelley on DSK3SPTVN1PROD with RULES
of the local flight standards district office/ Docket Operations Office between 9
certificate holding district office.
a.m. and 5 p.m., Monday through
(u) Related Information Friday, except Federal holidays. The AD
For more information about this AD, docket contains this AD, the European
contact Carl Gray, Aerospace Engineer, Aviation Safety Agency (EASA) AD, the
Airframe Branch, ACE–117A, FAA, Atlanta economic evaluation, any comments
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Document Created: 2015-12-15 15:25:12
Document Modified: 2015-12-15 15:25:12
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective July 14, 2015. | |
| 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: [email protected] | |
| FR Citation | 80 FR 32441 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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