80 FR 27607 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 93 (May 14, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 93 (May 14, 2015)
| Page Range | 27607-27611 | |
| FR Document | 2015-11554 |
[Federal Register Volume 80, Number 93 (Thursday, May 14, 2015)] [Proposed Rules] [Pages 27607-27611] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-11554] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-1417; Directorate Identifier 2013-NM-159-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2004-20- 14, for all Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; and all Model A300 B4-600, B4-600R, and F4-600R series airplanes. AD 2004- 20-14 requires repetitive inspections to detect cracking of the splice fitting at fuselage frame (FR) 47 between stringers 24 and 26 (left- and right-hand sides), and corrective actions if necessary. Since we issued AD 2004-20-14, we have determined that the inspection compliance time and repetitive inspection interval must be reduced to allow timely detection of cracks in the splice fitting at fuselage FR 47. This proposed AD would reduce the inspection compliance time and repetitive inspection intervals, and add Model A300 C4-605R Variant F airplanes to the applicability. We are proposing this AD to detect and correct cracking of the splice fitting at fuselage FR 47, which could result in reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by June 29, 2015. ADDRESSES: You may send comments by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: (202) 493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this 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. Examining the AD Docket 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-1417; Directorate Identifier 2013-NM-159-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On September 30, 2004, we issued AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004), which superseded AD 2001-03-14, Amendment 39-12118 (66 FR 10957, February 21, 2001). AD 2004-20-14 requires actions intended to address an unsafe condition on all Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; and all Model A300 B4- 600, B4-600R, and F4-600R series airplanes. Since we issued AD 2004-20- 14, Amendment 39-13819 (69 FR 60809, October 13, 2004), we have determined that the inspection compliance time and repetitive inspection interval must be reduced to allow timely detection of cracks in the splice fitting at fuselage FR 47, and that Model A300 C4-605R Variant F airplanes must be added to the applicability. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2013-0184R1, dated August 22, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for the specified products. The MCAI states: In order to prevent crack development in the fastener holes at Frame (FR) 47 splicing joint on A300 aeroplanes, Airbus developed modification (Mod) 5890 for aeroplanes in production and issued corresponding Service Bulletin (SB) A300-53-0199 for aeroplanes in service. Subsequently, cracks were found on FR47 splice fitting between stringers (STRG) 24 and 26 on A300 aeroplanes previously modified by SB A300-53-0199. This condition, if not detected and corrected, could reduce the structural integrity of the aeroplane. To address this potential unsafe condition, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 2002- 184 http://ad.easa.europa.eu/blob/2002184tb_superseded.pdf/AD_F-2002-184_2 [which corresponds to FAA AD 2004-20-14, Amendment 39- 13819 (69 FR 60809, October 13, 2004)], superseding [DGAC France] AD 85-152-069 and [DGAC France] AD 1999-515-298 [which corresponds to FAA AD 2001-03-14, Amendment 39-12118 (66 FR 10957, February 21, 2001)], to require repetitive High Frequency Eddy Current (HFEC) rotating probe inspections of the splice fitting between STRG 24 and 26 and, [[Page 27608]] depending on findings, corrective action(s). DGAC France AD 2002- 184(B) expanded the applicability to A300-600 aeroplanes, which have the same design. Since that [DGAC France] AD was issued, a fleet survey and updated Fatigue and Damage Tolerance analyses have been performed in order to substantiate the second A300-600 Extended Service Goal (ESG2) exercise. The results of these analyses have determined that the inspection threshold and intervals for A300-600 aeroplanes must be reduced to allow timely detection of these cracks and the accomplishment of an applicable corrective action. For the reasons described above, [EASA] AD 2013-0184 retains the requirements of DGAC France AD 2002-184, which is superseded, but requires accomplishment of the actions for A300-600 aeroplanes within the new thresholds and intervals introduced with Revision 05 of Airbus SB [service bulletin] A300-53-6123 [dated August 1, 2011] . This [EASA] AD was revised to correct the splices Part Numbers (P/N) in Table 4 of Appendix 1 of this [EASA] AD. Also, reference is now made to Airbus SB A300-53-6123 Revision 06 [dated September 28, 2011], which corrected this mistake compared to Revision 05. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA-2015-1417. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service bulletins: Airbus Service Bulletin A300-53-6123, Revision 06, including Inspection Report, dated September 28, 2011. This service bulletin describes procedures for inspection for cracking of the splice fitting at fuselage FR 47 between stringers 24 and 26, and corrective actions. Airbus Service Bulletin A300-53-0350, Revision 03, including Appendix 03, dated July 26, 2007. This service bulletin describes procedures for inspection to detect cracking of the splice fitting at fuselage FR 47 between stringers 24 and 26, and corrective actions. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. 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 NPRM. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Costs of Compliance We estimate that this proposed AD affects 72 airplanes of U.S. registry. We also estimate that it would take up to 14 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $85,680, or $1,190 per product. In addition, we estimate that any necessary follow-on actions would take up to 204 work-hours and require parts costing up to $37,000, for a cost of up to $54,340 per product. We have no way of determining the number of aircraft that might need these actions. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 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) 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004), and adding the following new AD: Airbus: Docket No. FAA-2015-1417; Directorate Identifier 2013-NM- 159-AD. (a) Comments Due Date We must receive comments by June 29, 2015. (b) Affected ADs This AD replaces AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004). (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(5) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes. (2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes. (3) Airbus Model A300 B4-605R and B4-622R airplanes. (4) Airbus Model A300 F4-605R and F4-622R airplanes. (5) Airbus Model A300 C4-605R Variant F airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. [[Page 27609]] (e) Reason This AD was prompted by a determination that the inspection compliance time and repetitive inspection interval must be reduced to allow timely detection of cracks in the splice fitting at fuselage frame (FR) 47. We are issuing this AD to detect and correct cracking of the splice fitting at fuselage FR 47, which could result in reduced structural integrity of the airplane. (f) Compliance You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. (g) Retained Repetitive Inspections for Airplanes Defined in Airbus Service Bulletin A300-53-0350, Revision 02, Dated November 12, 2002, With New Service Information This paragraph restates the requirements of paragraph (a) of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004), with new service information. For airplanes defined in Airbus Service Bulletin A300-53-0350, Revision 02, dated November 12, 2002: Do a high frequency eddy current (HFEC) inspection to detect cracking of the splice fitting at fuselage FR 47 between stringers 24 and 26 (left- and right-hand sides), at the applicable times specified in paragraph (g)(1) or (g)(2) of this AD. Repeat the inspection thereafter at the earlier of the flight-cycle/flight-hour intervals specified in the applicable column in Table 2 of Figure 1 and Sheet 1 of the Accomplishment Instructions of Airbus Service Bulletin A300-53-0350, Revision 02, excluding Appendix 01, dated November 12, 2002. Do the inspections in accordance with Airbus Service Bulletin A300-53-0350, Revision 02, excluding Appendix 01, dated November 12, 2002; or Revision 03, excluding Appendix 01, dated July 26, 2007. As of the effective date of this AD, use only Airbus Service Bulletin A300-53-0350, Revision 03, excluding Appendix 01, dated July 26, 2007. (1) For airplanes that have accumulated 20,000 or more total flight cycles as of November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)): Do the initial inspection at the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. (i) At the earlier of the flight-cycle/flight-hour intervals after November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)), as specified in the applicable column in Table 1 of Figure 1 and Sheet 1 of the Accomplishment Instructions of Airbus Service Bulletin A300-53-0350, Revision 02, excluding Appendix 01, dated November 12, 2002. (ii) Within 750 flight cycles or 1,500 flight hours after November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)), whichever is first. (2) For airplanes that have accumulated fewer than 20,000 total flight cycles as of November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)): Do the initial inspection at the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. (i) At the earlier of the flight-cycle/flight-hour intervals after November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)), as specified in the applicable column in Table 1 of Figure 1 and Sheet 1 of the Accomplishment Instructions of Airbus Service Bulletin A300-53-0350, Revision 02, excluding Appendix 01, dated November 12, 2002. (ii) Within 1,800 flight cycles or 3,000 flight hours after November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)), whichever is first. (h) Retained Repetitive Inspections for Airplanes Defined in Airbus Service Bulletin A300-53-6123, Revision 02, Dated November 12, 2002, With New Service Information This paragraph restates the requirements of paragraph (b) of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004), with new service information. For airplanes defined in Airbus Service Bulletin A300-53-6123, Revision 02, dated November 12, 2002: Do the HFEC inspection required by paragraph (g) of this AD at the applicable times specified in paragraph (h)(1) or (h)(2) of this AD. Repeat the inspection thereafter at the earlier of the flight-cycle/ flight-hour intervals specified in the applicable column in Table 2 of Figure 1 and Sheet 1 of the Accomplishment Instructions of Airbus Service Bulletin A300-53-6123, Revision 02, excluding Appendix 01, dated November 12, 2002. Do the inspections in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6123, Revision 02, excluding Appendix 01, dated November 12, 2002, excluding Appendix 01; or Revision 06, dated September 28, 2011. Accomplishment of the actions required by paragraph (j) of this AD terminates the requirements of this paragraph. (1) For airplanes that have accumulated 10,000 or more total flight cycles as of November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)): Do the initial inspection within 750 flight cycles or 1,900 flight hours after November 17, 2004, whichever is first. (2) For airplanes that have accumulated fewer than 10,000 total flight cycles as of November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)): Do the initial inspection at the later of the times specified in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD. (i) At the earlier of the flight-cycle/flight-hour intervals after November 17, 2004 (the effective date of AD 2004-2-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)), as specified in the applicable column in Table 1 of Figure 1 and Sheet 1 of the Accomplishment Instructions of Airbus Service Bulletin A300-53-6123, Revision 02, excluding Appendix 01, dated November 12, 2002. (ii) Within 1,500 flight cycles or 3,800 flight hours after November 17, 2004 (the effective date of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004)), whichever is first. (i) Retained Repair, With Revised Repair Instructions This paragraph restates the requirements of paragraph (c) of AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004), with revised repair instructions. Repair any cracking found during any inspection required by paragraphs (g) and (h) this AD before further flight, in accordance with Airbus Service Bulletin A300-53-0350, Revision 02, excluding Appendix 01, dated November 12, 2002; or Airbus Service Bulletin A300-53-6123, Revision 02, excluding Appendix 01, dated November 12, 2002; as applicable. Where Airbus Service Bulletin A300-53-0350, Revision 02, excluding Appendix 01, dated November 12, 2002; or Airbus Service Bulletin A300-53-6123, Revision 02, excluding Appendix 01, dated November 12, 2002; specify to contact Airbus in case of certain crack findings, this AD requires that a repair be accomplished before further flight using a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated agent); or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). (j) New Requirement of This AD: Repetitive Inspections For airplanes identified in paragraphs (c)(2) through (c)(5) of this AD: At the applicable time specified in paragraph (j)(1) or (j)(2) of this AD: Remove the fasteners and accomplish an HFEC rotating probe inspection for cracking of the splice fitting between stringer 24 and 26, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6123, Revision 06, excluding Inspection Report, dated September 28, 2011. Repeat the inspection thereafter at the applicable intervals specified in paragraphs (k)(1) through (k)(4) of this AD. If no cracking is found: Before further flight after each inspection, install new fasteners, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6123, Revision 06, excluding Inspection Report, dated September 28, 2011. Accomplishment of the initial inspection required by this paragraph terminates the requirements of paragraph (h) of this AD for that airplane. (1) For airplanes on which Airbus Modification 5890, or the actions specified in Airbus Service Bulletin A300-53-6131, have not been done: At the applicable time specified in paragraphs (j)(1)(i) and (j)(1)(ii) of this AD. (i) For airplanes that have an average flight time (AFT) that is more than 1.5 hours: At the later of the times specified in paragraphs (j)(1)(i)(A) and (j)(1)(i)(B) of this AD. (A) Before the accumulation of 2,500 total flight cycles or 5,500 total flight hours, whichever occurs first. [[Page 27610]] (B) Within 800 flight cycles or 1,750 flight hours, whichever occurs first after the effective date of this AD. (ii) For airplanes that have an AFT that is equal to or less than 1.5 hours: At the later of the times specified in paragraphs (j)(1)(ii)(A) and (j)(1)(ii)(B) of this AD. (A) Before the accumulation of 2,700 total flight cycles or 4,100 total flight hours, whichever occurs first. (B) Within 800 flight cycles or 1,750 flight hours, whichever occurs first after the effective date of this AD. (2) For airplanes that have accomplished Airbus Modification 5890, or have accomplished the actions specified in Airbus Service Bulletin A300-53-6131: At the applicable time specified in paragraph (j)(2)(i) or (j)(2)(ii) of this AD. (i) For airplanes that have an AFT that is more than 1.5 hours: At the later of the times specified in paragraphs (j)(2)(i)(A) and (j)(2)(i)(B) of this AD. (A) Before the accumulation of 6,800 total flight cycles or 14,700 total flight hours, whichever occurs first. (B) Within 800 flight cycles or 1,750 flight hours, whichever occurs first after the effective date of this AD. (ii) For airplanes that have an AFT that is equal to or less than 1.5 hours: At the later of the times specified in paragraphs (j)(2)(ii)(A) and (j)(2)(ii)(B) of this AD. (A) Before the accumulation of 7,300 total flight cycles or 11,000 total flight hours, whichever occurs first. (B) Within 800 flight cycles or 1,750 flight hours, whichever occurs first after the effective date of this AD. (k) New Requirement of This AD: Repetitive Inspection Intervals for Actions Specified in Paragraph (j) of This AD For airplanes identified in paragraphs (c)(2) through (c)(5) of this AD: Repeat the inspection required by paragraph (j) of this AD at the applicable time specified in paragraphs (k)(1) through (k)(4) of this AD. (1) For airplanes that have an AFT of more than 1.5 hours and meet the applicable conditions specified in paragraphs (k)(1)(i) through (k)(1)(iv) of this AD: Inspect at intervals not to exceed 800 flight cycles or 1,750 flight hours, whichever occurs first. (i) Airplanes on which Airbus Modification 5890 has not been accomplished. (ii) Airplanes on which the actions specified in Airbus Service Bulletin A300-53-6131 have not been accomplished. (iii) Airplanes on which Airbus Modification 5890 has been accomplished and have splice part number (P/N) A53834139-202/-203 installed. (iv) Airplanes on which the actions specified in Airbus Service Bulletin A300-53-6131 have been accomplished and have splice P/N A53834139-202/-203 installed. (2) For airplanes that have an AFT that is equal to or less than 1.5 hours and meet the applicable conditions specified in paragraphs (k)(2)(i) through (k)(2)(iv) of this AD: Inspect at intervals not to exceed 800 flight cycles or 1,750 flight hours. (i) Airplanes on which Airbus Modification 5890 has not been accomplished. (ii) Airplanes on which the actions specified in Airbus Service Bulletin A300-53-6131 have not been accomplished. (iii) Airplanes on which Airbus Modification 5890 has been accomplished and have splice P/N A53834139-202/-203 installed. (iv) Airplanes on which the actions described in Airbus Service Bulletin A300-53-6131 have been accomplished and have splice P/N A53834139-202/-203 installed. (3) For airplanes that have an AFT of more than 1.5 hours and meet the applicable conditions specified in paragraphs (k)(3)(i) and (k)(3)(ii) of this AD: Inspect at intervals not to exceed 800 flight cycles or 1,750 flight hours. (i) Airplanes on which Airbus Modification 5890 has been accomplished and have splice P/N A53812635-200/-201/-202/-203 installed. (ii) Airplanes on which the actions specified in Airbus Service Bulletin A300-53-6131 have been accomplished and have splice P/N A53812635-200/-201/-202/-203 installed. (4) For the airplanes that have an AFT that is equal to or less than 1.5 hours and meet the applicable conditions specified in paragraphs (k)(4)(i) and (k)(4)(ii) of this AD: Inspect at intervals not to exceed 800 flight cycles or 1,750 flight hours. (i) Airplanes on which Airbus Modification 5890 has been accomplished and have splice P/N A53812635-200/-201/-202/-203 installed. (ii) Airplanes on which the actions specified in Airbus Service Bulletin A300-53-6131 have been accomplished and have splice P/N A53812635-200/-201/-202/-203 installed. (l) New Requirement of This AD: Corrective Actions If, during any inspection required by paragraph (j) or (k) of this AD, any cracks are found: Before further flight, do the applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6123, Revision 06, excluding Inspection Report, dated September 28, 2011; except as provided by paragraph (m) of this AD. (m) New Requirement of This AD: Exception to Service Information If any crack is found during any inspection required by paragraph (j) or (k) of this AD and Airbus Service Bulletin A300-53- 6123, Revision 06, excluding Inspection Report, dated September 28, 2011; or Airbus Service Bulletin A300-53-0350, Revision 03, dated July 26, 2007; specifies to contact Airbus: Before further flight, repair the crack using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. (n) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (j) and (l) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraphs (n)(1) through (n)(7) of this AD. (1) Airbus Service Bulletin A300-53-0350, Revision 01, dated December 18, 2001, which is not incorporated by reference in this AD. (2) Airbus Service Bulletin A300-53-0350, Revision 02, excluding Appendix 01, dated November 12, 2002, which is incorporated by reference in AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004). (3) Airbus Service Bulletin A300-53-6123, Revision 01, dated December 18, 2001, which is not incorporated by reference in this AD. (4) Airbus Service Bulletin A300-53-6123, Revision 02, excluding Appendix 01, dated November 12, 2002, which is incorporated by reference in AD 2004-20-14, Amendment 39-13819 (69 FR 60809, October 13, 2004). (5) Airbus Service Bulletin A300-53-6123, Revision 03, dated August 20, 2004, which is not incorporated by reference in this AD. (6) Airbus Service Bulletin A300-53-6123, Revision 04, dated April 25, 2008, which is not incorporated by reference in this AD. (7) Airbus Service Bulletin A300-53-6123, Revision 05, dated August 1, 2011, which is not incorporated by reference in this AD. (o) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, 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 International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM- 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Airworthiness Directive 2013-0184R1, dated August 22, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-1417. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; [[Page 27611]] telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this 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. Issued in Renton, Washington, on April 30, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-11554 Filed 5-13-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 93 / Thursday, May 14, 2015 / Proposed Rules 27607
(h) Additional Information • Federal eRulemaking Portal: Go to closing date and may amend this
The subject of this AD is addressed in the http://www.regulations.gov. Follow the proposed AD based on those comments.
Direction General De L’Aviation Civile instructions for submitting comments. We will post all comments we
(DGAC) AD No. 67A005, Revision 1, dated • Fax: (202) 493–2251. receive, without change, to http://
February 6, 2002. You may view the DGAC • Mail: U.S. Department of www.regulations.gov, including any
AD on the Internet at http:// Transportation, Docket Operations, M– personal information you provide. We
www.regulations.gov in Docket No. FAA– 30, West Building Ground Floor, Room will also post a report summarizing each
2015–1480.
W12–140, 1200 New Jersey Avenue SE., substantive verbal contact we receive
(i) Subject Washington, DC 20590. about this proposed AD.
Joint Aircraft Service Component (JASC) • Hand Delivery: U.S. Department of Discussion
Code: 2500, Cabin Equipment/Furnishings. Transportation, Docket Operations, M–
30, West Building Ground Floor, Room On September 30, 2004, we issued AD
Issued in Fort Worth, Texas, on May 1,
2015. W12–140, 1200 New Jersey Avenue SE., 2004–20–14, Amendment 39–13819 (69
Washington, DC, between 9 a.m. and 5 FR 60809, October 13, 2004), which
Lance T. Gant,
p.m., Monday through Friday, except superseded AD 2001–03–14,
Acting Directorate Manager, Rotorcraft Amendment 39–12118 (66 FR 10957,
Directorate, Aircraft Certification Service. Federal holidays.
For service information identified in February 21, 2001). AD 2004–20–14
[FR Doc. 2015–11522 Filed 5–13–15; 8:45 am]
this proposed AD, contact Airbus SAS, requires actions intended to address an
BILLING CODE 4910–13–P unsafe condition on all Airbus Model
Airworthiness Office—EAW, 1 Rond
Point Maurice Bellonte, 31707 Blagnac A300 B4–2C, B4–103, and B4–203
Cedex, France; telephone +33 5 61 93 36 airplanes; and all Model A300 B4–600,
DEPARTMENT OF TRANSPORTATION B4–600R, and F4–600R series airplanes.
96; fax +33 5 61 93 44 51; email
Federal Aviation Administration account.airworth-eas@airbus.com; Since we issued AD 2004–20–14,
Internet http://www.airbus.com. You Amendment 39–13819 (69 FR 60809,
14 CFR Part 39 may view this service information at the October 13, 2004), we have determined
FAA, Transport Airplane Directorate, that the inspection compliance time and
[Docket No. FAA–2015–1417; Directorate 1601 Lind Avenue SW., Renton, WA. repetitive inspection interval must be
Identifier 2013–NM–159–AD] For information on the availability of reduced to allow timely detection of
this material at the FAA, call 425–227– cracks in the splice fitting at fuselage FR
RIN 2120–AA64 47, and that Model A300 C4–605R
1221.
Variant F airplanes must be added to the
Airworthiness Directives; Airbus Examining the AD Docket applicability.
Airplanes The European Aviation Safety Agency
You may examine the AD docket on
AGENCY: Federal Aviation the Internet at http:// (EASA), which is the Technical Agent
Administration (FAA), DOT. www.regulations.gov; or in person at the for the Member States of the European
ACTION: Notice of proposed rulemaking Docket Operations office between 9 a.m. Union, has issued EASA Airworthiness
(NPRM). and 5 p.m., Monday through Friday, Directive 2013–0184R1, dated August
except Federal holidays. The AD docket 22, 2013 (referred to after this as the
SUMMARY: We propose to supersede contains this proposed AD, the Mandatory Continuing Airworthiness
Airworthiness Directive (AD) 2004–20– regulatory evaluation, any comments Information, or ‘‘the MCAI’’), to correct
14, for all Airbus Model A300 B4–2C, received, and other information. The an unsafe condition for the specified
B4–103, and B4–203 airplanes; and all street address for the Docket Operations products. The MCAI states:
Model A300 B4–600, B4–600R, and F4– office (telephone 800–647–5527) is in In order to prevent crack development in
600R series airplanes. AD 2004–20–14 the ADDRESSES section. Comments will the fastener holes at Frame (FR) 47 splicing
requires repetitive inspections to detect be available in the AD docket shortly joint on A300 aeroplanes, Airbus developed
cracking of the splice fitting at fuselage after receipt. modification (Mod) 5890 for aeroplanes in
frame (FR) 47 between stringers 24 and production and issued corresponding Service
FOR FURTHER INFORMATION CONTACT: Dan
26 (left- and right-hand sides), and Bulletin (SB) A300–53–0199 for aeroplanes
Rodina, Aerospace Engineer, in service.
corrective actions if necessary. Since we International Branch, ANM–116, Subsequently, cracks were found on FR47
issued AD 2004–20–14, we have Transport Airplane Directorate, FAA, splice fitting between stringers (STRG) 24
determined that the inspection 1601 Lind Avenue SW., Renton, WA and 26 on A300 aeroplanes previously
compliance time and repetitive 98057–3356; telephone 425–227–2125; modified by SB A300–53–0199.
inspection interval must be reduced to fax 425–227–1149. This condition, if not detected and
allow timely detection of cracks in the corrected, could reduce the structural
SUPPLEMENTARY INFORMATION:
splice fitting at fuselage FR 47. This integrity of the aeroplane.
proposed AD would reduce the Comments Invited To address this potential unsafe condition,
inspection compliance time and DGAC [Direction Générale de l’Aviation
We invite you to send any written Civile] France issued AD 2002–184 http://
repetitive inspection intervals, and add relevant data, views, or arguments about ad.easa.europa.eu/blob/2002184tb_
Model A300 C4–605R Variant F this proposed AD. Send your comments superseded.pdf/AD_F-2002-184_2 [which
airplanes to the applicability. We are to an address listed under the corresponds to FAA AD 2004–20–14,
proposing this AD to detect and correct Amendment 39–13819 (69 FR 60809, October
tkelley on DSK3SPTVN1PROD with PROPOSALS
ADDRESSES section. Include ‘‘Docket No.
cracking of the splice fitting at fuselage FAA–2015–1417; Directorate Identifier 13, 2004)], superseding [DGAC France] AD
FR 47, which could result in reduced 2013–NM–159–AD’’ at the beginning of 85–152–069 and [DGAC France] AD 1999–
structural integrity of the airplane. 515–298 [which corresponds to FAA AD
your comments. We specifically invite 2001–03–14, Amendment 39–12118 (66 FR
DATES: We must receive comments on comments on the overall regulatory, 10957, February 21, 2001)], to require
this proposed AD by June 29, 2015. economic, environmental, and energy repetitive High Frequency Eddy Current
ADDRESSES: You may send comments by aspects of this proposed AD. We will (HFEC) rotating probe inspections of the
any of the following methods: consider all comments received by the splice fitting between STRG 24 and 26 and,
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![27608 Federal Register / Vol. 80, No. 93 / Thursday, May 14, 2015 / Proposed Rules
depending on findings, corrective action(s). in the United States. Pursuant to our 1. Is not a ‘‘significant regulatory
DGAC France AD 2002–184(B) expanded the bilateral agreement with the State of action’’ under Executive Order 12866;
applicability to A300–600 aeroplanes, which Design Authority, we have been notified 2. Is not a ‘‘significant rule’’ under the
have the same design.
of the unsafe condition described in the DOT Regulatory Policies and Procedures
Since that [DGAC France] AD was issued,
a fleet survey and updated Fatigue and MCAI and service information (44 FR 11034, February 26, 1979);
Damage Tolerance analyses have been referenced above. We are proposing this 3. Will not affect intrastate aviation in
performed in order to substantiate the second AD because we evaluated all pertinent Alaska; and
A300–600 Extended Service Goal (ESG2) information and determined an unsafe 4. Will not have a significant
exercise. The results of these analyses have condition exists and is likely to exist or economic impact, positive or negative,
determined that the inspection threshold and develop on other products of the same on a substantial number of small entities
intervals for A300–600 aeroplanes must be under the criteria of the Regulatory
type design.
reduced to allow timely detection of these
Flexibility Act.
cracks and the accomplishment of an Costs of Compliance
applicable corrective action. We prepared a regulatory evaluation
For the reasons described above, [EASA] We estimate that this proposed AD of the estimated costs to comply with
AD 2013–0184 retains the requirements of affects 72 airplanes of U.S. registry. this proposed AD and placed it in the
DGAC France AD 2002–184, which is We also estimate that it would take up AD docket.
superseded, but requires accomplishment of to 14 work-hours per product to comply
the actions for A300–600 aeroplanes within with the basic requirements of this List of Subjects in 14 CFR Part 39
the new thresholds and intervals introduced proposed AD. The average labor rate is Air transportation, Aircraft, Aviation
with Revision 05 of Airbus SB [service $85 per work hour. Based on these safety, Incorporation by reference,
bulletin] A300–53–6123 [dated August 1, figures, we estimate the cost of this Safety.
2011] .
This [EASA] AD was revised to correct the
proposed AD on U.S. operators to be
The Proposed Amendment
splices Part Numbers (P/N) in Table 4 of $85,680, or $1,190 per product.
Appendix 1 of this [EASA] AD. Also, In addition, we estimate that any Accordingly, under the authority
reference is now made to Airbus SB A300– necessary follow-on actions would take delegated to me by the Administrator,
53–6123 Revision 06 [dated September 28, up to 204 work-hours and require parts the FAA proposes to amend 14 CFR part
2011], which corrected this mistake costing up to $37,000, for a cost of up 39 as follows:
compared to Revision 05. to $54,340 per product. We have no way
You may examine the MCAI in the of determining the number of aircraft PART 39—AIRWORTHINESS
AD docket on the Internet at http:// that might need these actions. DIRECTIVES
www.regulations.gov by searching for Authority for This Rulemaking ■ 1. The authority citation for part 39
and locating it in Docket No. FAA– continues to read as follows:
2015–1417. Title 49 of the United States Code
specifies the FAA’s authority to issue Authority: 49 U.S.C. 106(g), 40113, 44701.
Related Service Information Under 1 rules on aviation safety. Subtitle I,
CFR Part 51 section 106, describes the authority of § 39.13 [Amended]
Airbus has issued the following the FAA Administrator. ‘‘Subtitle VII: ■ 2. The FAA amends § 39.13 by
service bulletins: Aviation Programs,’’ describes in more removing airworthiness directive (AD)
• Airbus Service Bulletin A300–53– detail the scope of the Agency’s 2004–20–14, Amendment 39–13819 (69
6123, Revision 06, including Inspection authority. FR 60809, October 13, 2004), and
Report, dated September 28, 2011. This We are issuing this rulemaking under adding the following new AD:
service bulletin describes procedures for the authority described in ‘‘Subtitle VII, Airbus: Docket No. FAA–2015–1417;
inspection for cracking of the splice Part A, Subpart III, Section 44701: Directorate Identifier 2013–NM–159–AD.
fitting at fuselage FR 47 between General requirements.’’ Under that
(a) Comments Due Date
stringers 24 and 26, and corrective section, Congress charges the FAA with
promoting safe flight of civil aircraft in We must receive comments by June 29,
actions.
2015.
• Airbus Service Bulletin A300–53– air commerce by prescribing regulations
0350, Revision 03, including Appendix for practices, methods, and procedures (b) Affected ADs
03, dated July 26, 2007. This service the Administrator finds necessary for This AD replaces AD 2004–20–14,
bulletin describes procedures for safety in air commerce. This regulation Amendment 39–13819 (69 FR 60809, October
inspection to detect cracking of the is within the scope of that authority 13, 2004).
splice fitting at fuselage FR 47 between because it addresses an unsafe condition (c) Applicability
stringers 24 and 26, and corrective that is likely to exist or develop on
This AD applies to the Airbus airplanes
actions. products identified in this rulemaking
identified in paragraphs (c)(1) through (c)(5)
The actions described in this service action. of this AD, certificated in any category, all
information are intended to correct the manufacturer serial numbers.
Regulatory Findings
unsafe condition identified in the (1) Airbus Model A300 B4–2C, B4–103,
MCAI. This service information is We determined that this proposed AD and B4–203 airplanes.
reasonably available because the would not have federalism implications (2) Airbus Model A300 B4–601, B4–603,
interested parties have access to it under Executive Order 13132. This B4–620, and B4–622 airplanes.
through their normal course of business proposed AD would not have a (3) Airbus Model A300 B4–605R and B4–
tkelley on DSK3SPTVN1PROD with PROPOSALS
or by the means identified in the substantial direct effect on the States, on 622R airplanes.
ADDRESSES section of this NPRM. the relationship between the national (4) Airbus Model A300 F4–605R and F4–
Government and the States, or on the 622R airplanes.
FAA’s Determination and Requirements (5) Airbus Model A300 C4–605R Variant F
distribution of power and airplanes.
of This Proposed AD responsibilities among the various
This product has been approved by levels of government. (d) Subject
the aviation authority of another For the reasons discussed above, I Air Transport Association (ATA) of
country, and is approved for operation certify this proposed regulation: America Code 53, Fuselage.
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![Federal Register / Vol. 80, No. 93 / Thursday, May 14, 2015 / Proposed Rules 27611
telephone +33 5 61 93 36 96; fax +33 5 61 Management System will not accept Administration; Mailing Address: 8701
93 44 51; email account.airworth-eas@ comments after 11:59 p.m. Eastern Time Morrissette Drive, Springfield, Virginia
airbus.com; Internet http://www.airbus.com. on the last day of the comment period. 22152; Telephone: (202) 598–6812.
You may view this service information at the Interested persons, defined at 21 CFR
FAA, Transport Airplane Directorate, 1601 SUPPLEMENTARY INFORMATION:
Lind Avenue SW., Renton, WA. For 1300.01 as those ‘‘adversely affected or
information on the availability of this aggrieved by any rule or proposed rule Posting of Public Comments
material at the FAA, call 425–227–1221. issuable pursuant to section 201 of the
Act (21 U.S.C. 811),’’ may file a request Please note that all comments
Issued in Renton, Washington, on April 30,
2015. for hearing, notice of appearance, or received are considered part of the
waiver of hearing pursuant to 21 CFR public record. They will, unless
Michael Kaszycki,
1308.44 and in accordance with 21 CFR reasonable cause is given, be made
Acting Manager, Transport Airplane 1316.45, 1316.47, 1316.48, or 1316.49,
Directorate, Aircraft Certification Service.
available by the Drug Enforcement
as applicable. Requests for hearing, Administration (DEA) for public
[FR Doc. 2015–11554 Filed 5–13–15; 8:45 am]
notices of appearance, and waivers of an inspection online at http://
BILLING CODE 4910–13–P opportunity for a hearing or to www.regulations.gov. Such information
participate in a hearing must be includes personal identifying
received on or before June 15, 2015. information (such as your name,
DEPARTMENT OF JUSTICE ADDRESSES: To ensure proper handling address, etc.) voluntarily submitted by
Drug Enforcement Administration of comments, please reference ‘‘Docket the commenter. The Freedom of
No. DEA–417N’’ on all correspondence, Information Act (FOIA) applies to all
21 CFR Part 1308 including any attachments. comments received. If you want to
• Electronic comments: The Drug submit personal identifying information
[Docket No. DEA–417N] Enforcement Administration encourages (such as your name, address, etc.) as
that all comments be submitted
Schedules of Controlled Substances: part of your comment, but do not want
electronically through the Federal
Placement of UR–144, XLR11, and it to be made publicly available, you
eRulemaking Portal, which provides the
AKB48 Into Schedule I must include the phrase ‘‘PERSONAL
ability to type short comments directly
into the comment field on the Web page IDENTIFYING INFORMATION’’ in the
AGENCY: Drug Enforcement first paragraph of your comment. You
Administration, Department of Justice. or to attach a file for lengthier
comments. Please go to http:// must also place all of the personal
ACTION: Notice of proposed rulemaking. identifying information you do not want
www.regulations.gov and follow the
SUMMARY: The Drug Enforcement online instructions at that site for made publicly available in the first
Administration (DEA) proposes placing submitting comments. Upon completion paragraph of your comment and identify
(1-pentyl-1H-indol-3-yl)(2,2,3,3- of your submission you will receive a what information you want redacted.
tetramethylcyclopropyl)methanone Comment Tracking Number for your If you want to submit confidential
(UR–144), [1-(5-fluoro-pentyl)-1H-indol- comment. Please be aware that business information as part of your
3-yl](2,2,3,3- submitted comments are not comment, but do not want it to be made
tetramethylcyclopropyl)methanone (5- instantaneously available for public publicly available, you must include the
fluoro-UR–144, XLR11), and N-(1- view on Regulations.gov. If you have phrase ‘‘CONFIDENTIAL BUSINESS
adamantyl)-1-pentyl-1H-indazole-3- received a Comment Tracking Number, INFORMATION’’ in the first paragraph
carboxamide (APINACA, AKB48) your comment has been successfully of your comment. You must also
including their salts, isomers, and salts submitted and there is no need to prominently identify confidential
of isomers whenever the existence of resubmit the same comment.
business information to be redacted
such salts, isomers, and salts of isomers • Paper comments: Paper comments
within the comment.
is possible, into schedule I of the that duplicate the electronic submission
Controlled Substances Act. This are not necessary and are discouraged. Comments containing personal
proposed scheduling action is pursuant Should you wish to mail a paper identifying information and confidential
to the Controlled Substance Act which comment in lieu of an electronic business information identified as
requires that such actions be made on comment, it should be sent via regular directed above will generally be made
the record after opportunity for a or express mail to: Drug Enforcement publicly available in redacted form. If a
hearing through formal rulemaking. If Administration, Attn: DEA Federal comment has so much confidential
finalized, this action would impose the Register Representative/ODXL, 8701 business information or personal
regulatory controls and administrative, Morrissette Drive, Springfield, Virginia identifying information that it cannot be
civil, and criminal sanctions applicable 22152. effectively redacted, all or part of that
to schedule I controlled substances on • Hearing requests: All requests for comment may not be made publicly
persons who handle (manufacture, hearing and waivers of participation available. Comments posted to http://
distribute, import, export, engage in must be sent to: Drug Enforcement www.regulations.gov may include any
research, conduct instructional Administration, Attn: Federal Register personal identifying information (such
activities, or possess), or propose to Representative/ODL, 8701 Morrissette as name, address, and phone number)
handle UR–144, XLR11, or AKB48. Drive, Springfield, Virginia 22152. All included in the text of your electronic
requests for hearing and waivers of
tkelley on DSK3SPTVN1PROD with PROPOSALS
DATES: Interested persons may file submission that is not identified as
written comments on this proposal in participation should also be sent to:
directed above as confidential.
accordance with 21 CFR 1308.43(g). Drug Enforcement Administration, Attn:
Electronic comments must be Hearing Clerk/LJ, 8701 Morrissette An electronic copy of this document
submitted, and written comments must Drive, Springfield, Virginia 22152. and supplemental information to this
be postmarked, on or before June 15, FOR FURTHER INFORMATION CONTACT: John proposed rule are available at http://
2015. Commenters should be aware that R. Scherbenske, Office of Diversion www.regulations.gov for easy reference.
the electronic Federal Docket Control, Drug Enforcement
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Document Created: 2015-12-15 15:32:39
Document Modified: 2015-12-15 15:32:39
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by June 29, 2015. | |
| Contact | Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. | |
| FR Citation | 80 FR 27607 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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