81 FR 3045 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 12 (January 20, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 12 (January 20, 2016)
| Page Range | 3045-3051 | |
| FR Document | 2016-00634 |
[Federal Register Volume 81, Number 12 (Wednesday, January 20, 2016)] [Proposed Rules] [Pages 3045-3051] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-00634] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-8470; Directorate Identifier 2013-NM-199-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) 95-21-09, for all Airbus Model A300 series airplanes, and Airbus Model A300 B4- 600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 95-21-09 currently requires repetitive inspections for cracking of the No. 2 flap beams, and replacement of the flap beams, if necessary; and provides optional modifications for extending certain inspection thresholds, and an optional terminating modification for certain inspections. Since we issued AD 95-21-09, we have determined that the compliance times must be reduced. This proposed AD would reduce the compliance times for inspections and also reduce the number of airplanes affected. We are proposing this AD to detect and correct cracking of the No. 2 flap beams, which could result in rupture of the flap beams and reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by March 7, 2016. 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. [[Page 3046]] 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 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. 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-2015- 8470; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket 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-2015-8470; Directorate Identifier 2013-NM-199-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 October 3, 1995, we issued AD 95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995). AD 95-21-09 requires actions intended to address an unsafe condition on Airbus Model A300 and A300-600 series airplanes. Since we issued AD 95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), we have received a report that analyses showed a need for reduced compliance times. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2013-0234R2, dated October 7, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A300 and A300-600 series airplanes. The MCAI states: Fatigue and ``fail safe'' tests developed on a test specimen confirmed that cracks may appear and propagate from the bolt holes of the base member and the side members of flap beam No. 2. The development of such cracks, if not detected, could result in a rupture of flap beams No. 2, which could adversely affect the structural integrity of the airframe. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A300-57-0116 and SB A300-57-6005 and DGAC France issued AD 1986-187-076(B) [available at http://ad.easa.europa.eu/blob/1986-187-076%28B%29R4en.pdf/AD_F-1986-187-076R4_1], later revised, to require a repetitive inspection programme [and corrective action] for A300 and A300-600 aeroplanes. [French AD 86-187-076(B)R3, dated March 2, 1994, corresponds to FAA AD 95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), which superseded FAA AD 85-07-04, Amendment 39-5027 (49 FR 45755, April 2, 1985).] For A300 aeroplanes, and in the frame of the Extended Service Goal (ESG) exercise, it was shown that design changes (Airbus Mod. 4740/Airbus SB A300-57-0128 or Airbus Mod. 5815/Airbus SB A300-57- 0141) were not sufficient to enable full ESG life without inspections. For A300-600 aeroplanes, since DGAC France AD 1986-187-076(B) was issued, a fleet survey and updated Fatigue and Damage Tolerance analyses have been performed in order to substantiate the second A300-600 ESG2 exercise. Airbus SB A300-57-6005 has been revised accordingly to decrease the inspection thresholds and intervals. For the reasons described above, this [EASA] AD retains the requirements of DGAC France AD 1986-187-076(B)R4, which is superseded, and requires those inspections to be accomplished at reduced thresholds and intervals. This [EASA] AD has been revised to correct typographical errors in some compliance times defined in Appendix 1, Tables 1 and 2. The MCAI also reduces the number of airplanes identified in the applicability by exempting certain Model A300-600 airplanes on which certain Airbus modifications have been embodied. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-8470. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletins A300-57-0116, Revision 07, dated September 19, 2011; and A300-57-6005, Revision 06, dated November 14, 2013. This service information describes procedures for ultrasonic inspections of the number 2 flap beam base and side members. 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. 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. Differences Between This Proposed AD and the MCAI or Service Information Although the MCAI or service information allows further flight after cracks are found during compliance with the required action, paragraph (m) of this proposed AD requires that you replace the flap beam before further flight. Explanation of ``RC'' Procedures and Tests in Service Information The FAA worked in conjunction with industry, under the Airworthiness [[Page 3047]] Directive Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for annotating which procedures and tests in the service information are required for compliance with an AD. Differentiating these procedures and tests from other tasks in the service information is expected to improve an owner's/operator's understanding of crucial AD requirements and help provide consistent judgment in AD compliance. The procedures and tests identified as Required for Compliance (RC) in any service information have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. As specified in a NOTE under the Accomplishment Instructions of the specified service information, procedures and tests that are identified as RC in any service information must be done to comply with the proposed AD. However, procedures and tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an alternative method of compliance (AMOC), provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC will require approval of an AMOC. Costs of Compliance We estimate that this proposed AD affects 49 airplanes of U.S. registry. The actions that are required by AD 95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), and retained in this proposed AD take about 6 work-hours per product, at an average labor rate of $85 per work-hour. Required parts cost about $0 per product. Based on these figures, the estimated cost of the actions that were required by AD 95- 21-09 is $510 per product, per inspection cycle. We also estimate that it would take about 6 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 $24,990 per inspection cycle, or $510 per product, per inspection cycle. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed 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 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. 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) 95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), and adding the following new AD: Airbus: Docket No. FAA-2015-8470; Directorate Identifier 2013-NM- 199-AD. (a) Comments Due Date We must receive comments by March 7, 2016. (b) Affected ADs This AD replaces AD 95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995). (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(5) of this AD, certificated in any category. (1) Model Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes, all manufacturer serial numbers (MSNs). (2) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, and B4-622R airplanes, all MSNs. (3) Airbus Model A300 F4-605R, all MSNs, except those airplanes on which both Airbus Modifications 11133 and 12699 have been embodied. (4) Airbus Model A300 F4-622R airplanes, all MSNs, except those airplanes on which all Airbus Modifications 11133, 12047, 12048, and 12050 have been embodied, and except those airplanes on which both Airbus Modifications 11133 and 12699 have been embodied. (5) Airbus Model A300 C4-605R Variant F airplanes, all MSNs. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a determination that the compliance times must be reduced. We are issuing this AD to detect and correct cracking of the No. 2 flap beams, which could result in rupture of the flap beams and reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection and Corrective Actions for Model A300 Series Airplanes, With Note 3 of AD 95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), Incorporated and Additional Terminating Provisions This paragraph restates the requirements of paragraph (a) of AD 95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), with Note 3 of AD 95-21-09 incorporated and additional terminating provisions. For Model A300 series airplanes: Prior to the accumulation of 15,000 total landings, or within the next 120 days after May 9, 1985 (the effective date of AD 85-07-04, Amendment 39- 5027 (49 FR 45755, April 2, [[Page 3048]] 1985)), whichever occurs later, inspect for cracking of the base steel member and light alloy side members of the No. 2 flap beams, left hand and right hand, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-116, Revision 6, dated July 16, 1993. Accomplishing the requirements of paragraph (h) or (l) of this AD terminates the requirements of this paragraph. Measurement of crack length is performed by measurement of the probe displacement (perpendicular to symmetry plane of beam) between defect indication appearance and its complete disappearance. The bolt hole indication should not be interpreted as an indication of a defect. These two indications appear very close together because the defects originate from the bolt holes. (1) If no cracking is detected: Except as provided by paragraph (i) of this AD, repeat the inspection at intervals not to exceed 1,700 landings until the requirements of paragraph (h) or (l) of this AD are accomplished. (2) If any crack is detected that is less than or equal to 4 mm: Repeat the inspection at intervals not to exceed 250 landings, until the requirements of paragraph (h) or (l) of this AD are accomplished. (3) If any crack is detected that exceeds 4 mm: Prior to further flight, replace the flap beam in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-116, Revision 6, dated July 16, 1993, and prior to the accumulation of 15,000 flight cycles on the replaced flap beam, perform the ultrasonic inspection as required by paragraph (h) or (l) of this AD. (h) Retained Ultrasonic Inspection and Corrective Action for Model A300 Series Airplanes, With Additional Terminating Provisions This paragraph restates the requirements of paragraph (b) of AD 95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), with additional terminating provisions. For Model A300 series airplanes: Prior to the accumulation of 15,000 total landings, or within the next 1,000 landings after November 17, 1995 (the effective date of AD 95-21-09), whichever occurs later, perform an ultrasonic inspection to detect cracking of the No. 2 flap beams, in accordance with Airbus Service Bulletin A300-57-116, Revision 6, dated July 16, 1993. Accomplishment of this inspection terminates the inspections required by paragraph (g) of this AD. Accomplishment of the requirements of paragraph (l) of this AD terminates the requirements of this paragraph. (1) If no cracking is detected: Except as provided by paragraph (i) of this AD, repeat the ultrasonic inspections thereafter at intervals not to exceed 1,700 landings. (2) If any crack is detected beyond the bolt hole, and that crack is less than or equal to 4 mm in length: Repeat the ultrasonic inspections thereafter at intervals not to exceed 250 landings. (3) If any crack is detected beyond the bolt hole and that crack is greater than 4 mm in length: Prior to further flight, replace the flap beam in accordance with Airbus Service Bulletin A300-57-116, Revision 6, dated July 16, 1993, and prior to the accumulation of 15,000 flight cycles on the replaced flap beam, perform the ultrasonic inspection as required by this paragraph. (i) Retained Modification of the No. 2 Track Beam for Model A300 Series Airplanes, With Changes to Compliance Extension This paragraph restates the provisions of paragraph (c) of AD 95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), with changes to compliance extension. For Model A300 series airplanes: After accomplishing the initial inspection required by paragraph (h) of this AD, accomplishment of either paragraph (i)(1) or (i)(2) of this AD before the effective date of this AD extends the fatigue life of the No. 2 flap track beam as specified in those paragraphs, provided that no cracking is detected during any inspection required by paragraph (g) or (h) of this AD. (1) Removal of any damage and the installation of larger diameter bolts on the No. 2 flap track beam (Modification No. 4740), in accordance with Airbus Service Bulletin A300-57-128, Revision 3, dated January 26, 1990, extends the interval for the first repetitive inspection required by paragraph (h) of this AD from 1,700 landings to 12,000 landings, provided that Modification No. 4740 is accomplished prior to the accumulation of 16,700 total landings on the flap beams. Following accomplishment of the first repetitive inspection, subsequent repetitive inspections shall be performed at intervals not to exceed 1,700 landings. Or (2) Cold working of the bolt holes and the installation of larger diameter bolts on the No. 2 flap track beam (Modification No. 5815), in accordance with Airbus Service Bulletin A300-57-141, Revision 7, dated July 16, 1993, extends the interval for the first repetitive inspection required by paragraph (h) of this AD from 1,700 landings to the interval specified in paragraph (i)(2)(i) or (i)(2)(ii) of this AD. (i) If interference fit bolts that are 15/32-inch in diameter are fitted, the interval for the first repetitive inspection required by paragraph (h) of this AD is extended to 22,000 landings, provided that Modification 5815 is accomplished prior to the accumulation of 16,700 total landings on the flap beam. Following accomplishment of the first repetitive inspection required by paragraph (h) of this AD, subsequent repetitive inspections shall be performed at intervals not to exceed 1,700 landings. Or (ii) If interference fit bolts that are 7/16- or 3/8-inch in diameter are fitted, the interval for the first repetitive inspection required by paragraph (h) of this AD is extended to 33,000 landings, provided that Modification 5815 is accomplished prior to the accumulation of 16,700 total landings on the flap beam. Following accomplishment of the first repetitive inspection required by paragraph (h) of this AD, subsequent repetitive inspections shall be performed at intervals not to exceed 1,700 landings. (j) Retained Ultrasonic Inspection and Corrective Actions for Model A300-600 Series Airplanes, With Terminating Provisions This paragraph restates the requirements of paragraph (d) of AD 95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), with terminating provisions. For Model A300-600 series airplanes: Prior to the accumulation of 15,000 total landings, or within the next 1,000 landings after November 17, 1995 (the effective date of AD 95- 21-09), whichever occurs later, perform an ultrasonic inspection to detect cracking of the No. 2 flap track beams, in accordance with Airbus Service Bulletin A300-57-6005, Revision 2, dated December 16, 1993. Accomplishing the actions required by paragraph (l) of this AD terminates the requirements of this paragraph. (1) If no cracking is detected, repeat the ultrasonic inspections thereafter at intervals not to exceed 1,700 landings. (2) If any crack is detected beyond the bolt hole and that crack is less than or equal to 4 mm in length: Repeat the ultrasonic inspections thereafter at intervals not to exceed 250 landings. (3) If any crack is detected beyond the bolt hole and that crack is greater than 4 mm in length: Prior to further flight, replace the flap beam in accordance with Airbus Service Bulletin A300-57-6005, Revision 2, dated December 16, 1993, and prior to the accumulation of 15,000 landings on the replaced flap beam, perform the ultrasonic inspection required by paragraph (j) of this AD. (k) Retained Optional Action With Note 5 of AD 95-21-09 Amendment 39- 9395 (60 FR 53847, October 18, 1995), Incorporated and Changes to Terminating Action This paragraph restates the provisions of paragraph (e) of AD 95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), with Note 5 of AD 95-21-09 incorporated and changes to terminating action. For Model A300-600 series airplanes: Installation of oversized transition fit bolts in cold-worked holes, in accordance with Airbus Service Bulletin A300-57-6006 (Modification 5815), Revision 4, dated July 25, 1994, constitutes terminating action for the repetitive inspection requirements of paragraph (j) of this AD, provided that no cracking is detected during any inspection required by paragraph (j) of this AD, and provided that the installation is accomplished prior to the accumulation of 15,000 total landings and before the effective date of this AD. If any bolt requires oversizing above 7/16-inch diameter during accomplishment of this installation, prior to further flight, repair using a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, or by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA. As of the effective date of this AD, any new repair approval must be done using a method approved by the Manager, International Branch, ANM- 116, Transport Airplane Directorate, FAA. If Airbus Service Bulletin A300-57-6005, Revision 2, dated December 16, 1993, is accomplished concurrently with [[Page 3049]] Airbus Service Bulletin A300-57-6006, Revision 3, dated December 16, 1993 (Modification 5815), the ultrasonic inspection for cracking required by paragraph (j) of this AD need not be performed since the eddy current inspection detailed for Modification 5815 is more comprehensive. (l) New Requirement of This AD: Initial and Repetitive Ultrasonic Inspections At the applicable time specified in paragraph (l)(1) or (l)(2) of this AD and, thereafter at intervals not to exceed those defined in table 3 to paragraph (l) of this AD, as applicable, accomplish an ultrasonic inspection for cracking of the steel base member and the aluminum side members' flap beam on the left-hand (LH) and right- hand (RH) sides in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0116, Revision 07, dated September 19, 2011, including Appendixes A and B, undated; or Airbus Service Bulletin A300-57-6005, Revision 06, dated November 14, 2013; as applicable. For the purposes of this AD, average flight time (AFT) is considered to be the number of flight hours per flight cycle. Doing the actions required by this paragraph terminates the requirements of paragraphs (g) through (k) of this AD. (1) For Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes (referred to as Model A300 series airplanes): Within the applicable compliance time defined in table 1 to paragraph (l) of this AD. (2) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4- 622R, F4-605R, F4-622R, F4-622R airplanes, and Model A300 C4-605R Variant F airplanes (referred to as Model A300-600 series airplanes): At the later of the times specified in paragraphs (l)(2)(i) and (l)(2)(ii) of this AD. (i) Within the compliance time defined in table 2 to paragraph (l) of this AD. (ii) Within 300 flight cycles or 640 flight hours after the effective date of this AD, whichever occurs first. Table 1 to Paragraph (l) of This AD--Inspection Compliance Times for Model A300 Series Airplanes ------------------------------------------------------------------------ Compliance times Compliance times for airplanes with Airplane configuration for airplanes with an AFT of more an AFT of less than or equal to than 1.5 1.5 ------------------------------------------------------------------------ Model A300 B2-1A, B2-1C, B2K-3C, Within 15,000 Within 15,000 B2-203 airplanes on which flight cycles or flight cycles or Airbus Modifications 4740 and 16,900 flight 16,900 flight 5815 have not been embodied. hours since first hours since first flight of the flight of the airplane, airplane, whichever occurs whichever occurs first. first. Model A300 B4-103 airplanes on Within 15,000 Within 15,000 which Airbus Modifications 4740 flight cycles or flight cycles or and 5815 have not been embodied. 20,500 flight 20,500 flight hours since first hours since first flight of the flight of the airplane, airplane, whichever occurs whichever occurs first. first. Model A300 B4-2C, and B4-203 Within 16,200 Within 15,000 airplanes on which Airbus flight cycles or flight cycles or Modifications 4740 and 5815 22,200 flight 34,000 flight have not been embodied. hours since first hours since first flight of the flight of the airplane, airplane, whichever occurs whichever occurs first. first. Model A300 B2-1A, B2-1C, B2K-3C, Within 12,000 Within 12,000 B2-203 airplanes on which flight cycles or flight cycles or Airbus Modification 4740 has 13,500 flight 13,500 flight been embodied. hours since hours since embodiment of embodiment of Airbus Airbus Modification Modification 4740, whichever 4740, whichever occurs first. occurs first. Model A300 B4-103 airplanes on Within 12,000 Within 12,000 which Airbus Modification 4740 flight cycles or flight cycles or has been embodied. 16,400 flight 16,400 flight hours since hours since embodiment of embodiment of Airbus Airbus Modification Modification 4740, whichever 4740, whichever occurs first. occurs first. Model A300 B4-2C, and B4-203 Within 12,900 Within 12,000 airplanes on which Airbus flight cycles or flight cycles or Modification 4740 has been 17,700 flight 27,200 flight embodied. hours since hours since embodiment of embodiment of Airbus Airbus Modification Modification 4740, whichever 4740, whichever occurs first. occurs first. Model A300 B2-1A, B2-1C, B2K-3C, Within 33,000 Within 33,000 B2-203 airplanes on which flight cycles or flight cycles or Airbus Modification 5815 has 37,200 flight 37,200 flight been embodied and no bolt hours since hours since larger than 7/16-inch diameter embodiment of embodiment of is fitted. Airbus Airbus Modification Modification 5815, whichever 5815, whichever occurs first. occurs first. Model A300 B4-103 airplanes on Within 33,000 Within 33,000 which Airbus Modification 5815 flight cycles or flight cycles or has been embodied and no bolt 45,200 flight 45,200 flight larger than 7/16-inch diameter hours since hours since is fitted. embodiment of embodiment of Airbus Airbus Modification Modification 5815, whichever 5815, whichever occurs first. occurs first. Model A300 B4-2C, and B4-203 Within 35,600 Within 33,000 airplanes on which Airbus flight cycles or flight cycles or Modification 5815 has been 48,800 flight 74,900 flight embodied and no bolt larger hours since hours since than 7/16-inch diameter is embodiment of embodiment of fitted. Airbus Airbus Modification Modification 5815, whichever 5815, whichever occurs first. occurs first. Model A300 B2-1A, B2-1C, B2K-3C, Within 22,000 Within 22,000 B2-203 airplanes on which flight cycles or flight cycles or Airbus Modification 5815 has 24,800 flight 24,800 flight been embodied and at least one hours since hours since bolt with a 15/32[dash]inch embodiment of embodiment of diameter is fitted. Airbus Airbus Modification Modification 5815, whichever 5815, whichever occurs first. occurs first. Model A300 B4-103 airplanes on Within 22,000 Within 22,000 which Airbus Modification 5815 flight cycles or flight cycles or has been embodied and at least 30,100 flight 30,100 flight one bolt with a 15/32[dash]inch hours since hours since diameter is fitted. embodiment of embodiment of Airbus Airbus Modification Modification 5815, whichever 5815, whichever occurs first. occurs first. Model A300 B4-2C, and B4-203, Within 23,700 Within 22,000 airplanes on which Airbus flight cycles or flight cycles or Modification 5815 has been 32,500 flight 49,900 flight embodied and at least one bolt hours since hours since with a 15/32-inch diameter is embodiment of embodiment of fitted. Airbus Airbus Modification Modification 5815, whichever 5815, whichever occurs first. occurs first. ------------------------------------------------------------------------ Table 2 to Paragraph (l) of This AD--Compliance Times for Model A300-600 Series Airplanes ------------------------------------------------------------------------ Compliance times Compliance times for airplanes with Airplane configuration for airplanes with an AFT of more an AFT of less than or equal to than 1.5 1.5 ------------------------------------------------------------------------ Model A300-600 series airplanes Within 16,200 Within 15,000 on which Airbus Modification flight cycles or flight cycles or 5815 and Airbus Modification 24,300 flight 32,400 flight 11133 have not been embodied. hours since first hours since first flight of the flight of the airplane, airplane, whichever occurs whichever occurs first. first. [[Page 3050]] Model A300-600 series airplanes Within 35,600 Within 33,000 on which Airbus Modification flight cycles or flight cycles or 5815 has been embodied and no 53,400 flight 71,200 flight bolt larger than 7/16-inch hours since hours since diameter is fitted. embodiment of embodiment of Airbus Airbus Modification Modification 5815, whichever 5815, whichever occurs first. occurs first. Model A300-600 series airplanes Within 23,700 Within 22,000 on which Airbus Modification flight cycles or flight cycles or 5815 has been embodied and at 35,600 flight 47,500 flight least one bolt 15/32-inch hours since hours since diameter is fitted. embodiment of embodiment of Airbus Airbus Modification Modification 5815, whichever 5815, whichever occurs first. occurs first. Model A300-600 series airplanes Within 35,600 Within 33,000 on which Airbus Modification flight cycles or flight cycles or 11133 has been embodied. 53,400 flight 71,200 flight hours since first hours since first flight, whichever flight, whichever occurs first. occurs first. ------------------------------------------------------------------------ Table 3 to Paragraph (l) of This AD--Repetitive Inspection Intervals ------------------------------------------------------------------------ Repetitive Repetitive interval (not to interval (not to exceed) for exceed) for Airplane models airplanes with an airplanes with an AFT of less than AFT equal to or 1.5 more than 1.5 ------------------------------------------------------------------------ A300 B2-1A, B2-1C, B2K-3C, B2- 1,500 flight 1,500 flight 203. cycles or 1,600 cycles or 1,600 flight hours, flight hours, whichever occurs whichever occurs first. first. A300B4-103 airplanes............ 1,500 flight 1,500 flight cycles or 2,000 cycles or 2,000 flight hours, flight hours, whichever occurs whichever occurs first. first. A300 B4-2C, and B4-203.......... 1,600 flight 1,500 flight cycles or 2,200 cycles or 3,400 flight hours, flight hours, whichever occurs whichever occurs first. first. A300-600 series airplanes....... 1,600 flight 1,500 flight cycles or 2,400 cycles or 3,200 flight hours, flight hours, whichever occurs whichever occurs first. first. ------------------------------------------------------------------------ (m) New Requirement of This AD: Corrective Action If any crack is found during any inspection required by paragraph (l) of this AD: Before further flight, replace the flap beam using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). Replacement of the flap beam does not constitute terminating action for the inspections required by paragraph (l) of this AD. (n) Credit for Previous Actions (1) This paragraph provides credit for inspections required by paragraph (g) of this AD, if those inspections were performed before November 17, 1995 (the effective date of AD 95-21-09, Amendment 39- 9395 (60 FR 53847, October 18, 1995)) using Airbus Service Bulletin A300-57-116, Revision 1, dated August 27, 1983; Revision 2, dated April 24, 1984; Revision 3, dated July 20, 1984; Revision 4, dated August 13, 1986; or Revision 5, dated July 10, 1989; as applicable. (2) This paragraph provides credit for actions required by paragraph (l) of this AD, if those actions were performed before the effective date of this AD using the applicable service information identified in paragraphs (n)(2)(i) through (n)(2)(x) of this AD. (i) Airbus Service Bulletin A300-57-6005, Revision 03, dated November 25, 1997, which was not previously incorporated by reference. (ii) Airbus Service Bulletin A300-57-6005, Revision 04, dated October 25, 1999, which was not previously incorporated by reference. (iii) Airbus Service Bulletin A300-57-6005, Revision 05, dated April 25, 2013, which was not previously incorporated by reference. (iv) Airbus Service Bulletin A300-57-6005, Revision 2, dated December 16, 1993, which was previously incorporated by reference on November 17 1995 (60 FR 53847, October 18, 1995). (v) Airbus Service Bulletin A300-57-116, Revision 1, dated August 27, 1983, which was not previously incorporated by reference. (vi) Airbus Service Bulletin A300-57-116, Revision 2, dated April 24, 1984, which was not previously incorporated by reference. (vii) Airbus Service Bulletin A300-57-116, Revision 3, dated July 20, 1984, which was not previously incorporated by reference. (viii) Airbus Service Bulletin A300-57-116, Revision 4, dated August 13, 1986, which was not previously incorporated by reference. (ix) Airbus Service Bulletin A300-57-116, Revision 5, dated July 10, 1989, which was not previously incorporated by reference. (x) Airbus Service Bulletin A300-57-116, Revision 6, dated July 16, 1993, which was previously incorporated by reference on November 17, 1995 (60 FR 53847, October 18, 1995). (o) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, 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]. (i) 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. (ii) AMOCs approved previously for AD 95-21-09, Amendment 39- 9395 (60 FR 53847, October 18, 1995), are approved as AMOCs for the corresponding provisions of paragraphs (g) through (j) of 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 EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (m) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without [[Page 3051]] obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2013-0234R2, dated October 7, 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-2015-8470. (2) For service information identified in this 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. Issued in Renton, Washington, on January 6. 2016. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-00634 Filed 1-19-16; 8:45 am] BILLING CODE 4910-13-P
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(f) Compliance (i) Revision of Maintenance or Inspection (0)88–6280–111; email technicalservices@
Comply with this AD within the Program fokker.com; Internet http://
compliance times specified, unless already Before further flight after completing the www.myfokkerfleet.com. You may view this
installation specified in paragraph (g) of this service information at the FAA, Transport
done.
AD, or within 30 days after the effective date Airplane Directorate, 1601 Lind Avenue SW.,
(g) Modification of Main Fuel Tank Wiring of this AD, whichever occurs later: Revise the Renton, WA. For information on the
Within 24 months after the effective date airplane maintenance or inspection program, availability of this material at the FAA, call
as applicable, by incorporating the critical 425–227–1221.
of this AD, install fuses in the wiring of the
solenoid of the level control pilot valve, the design configuration control limitations Issued in Renton, Washington, on January
reed switch of the main tank overflow valve, (CDCCLs) specified in paragraph 1.L.(1)(c) of 6, 2016.
the level float switch of the collector tank, Fokker Services Proforma Service Bulletin Victor Wicklund,
and the solenoid of the main tank fueling SBF28–28–056, dated January 9, 2014,
including Appendix SBF28–28–056/APP01, Acting Manager, Transport Airplane
shut-off valve, as applicable, in accordance Directorate, Aircraft Certification Service.
dated July 15, 2014.
with the Accomplishment Instructions of [FR Doc. 2016–00700 Filed 1–19–16; 8:45 am]
Fokker Services Proforma Service Bulletin (j) No Alternative CDCCLs
BILLING CODE 4910–13–P
SBF28–28–056, dated January 9, 2014, After accomplishing the revision required
including Appendix SBF28–28–056/APP01, by paragraph (i) of this AD, no alternative
dated July 15, 2014. CDCCLs may be used unless the CDCCLs are DEPARTMENT OF TRANSPORTATION
approved as an alternative method of
(h) Concurrent Requirements
compliance (AMOC) in accordance with the
Prior to or concurrently with Federal Aviation Administration
procedures specified in paragraph (k)(1) of
accomplishing the requirements of paragraph this AD.
(g) of this AD, do the actions specified in 14 CFR Part 39
(k) Other FAA AD Provisions
paragraphs (h)(1) and (h)(2) of this AD.
The following provisions also apply to this [Docket No. FAA–2015–8470; Directorate
(1) Install fuses packed in jiffy junctions Identifier 2013–NM–199–AD]
(i.e., crimped wire in-line junction device(s)), AD:
in accordance with the Accomplishment (1) Alternative Methods of Compliance: RIN 2120–AA64
Instructions of Fokker Service Bulletin The Manager, International Branch, ANM–
SBF28–28–049, Revision 2, dated November 116, Transport Airplane Directorate, FAA, Airworthiness Directives; Airbus
3, 2014, including Fokker Drawing W57273, has the authority to approve AMOCs for this
AD, if requested using the procedures found
Airplanes
Sheet 002, Issue C, undated, Fokker Drawing
in 14 CFR 39.19. In accordance with 14 CFR AGENCY: Federal Aviation
W58048, Sheet 1, undated, and Fokker
39.19, send your request to your principal Administration (FAA), DOT.
Manual Change Notification MCNM–F28–
inspector or local Flight Standards District
035, Rev 1, dated January 9, 2014. Office, as appropriate. If sending information ACTION: Notice of proposed rulemaking
Accomplishment of the actions in this directly to the International Branch, send it (NPRM).
paragraph terminates the requirement of to ATTN: Tom Rodriguez, Aerospace
paragraph (g) of AD 2011–17–03, Engineer, International Branch, ANM–116, SUMMARY: We propose to supersede
Amendment 39–16767 (76 FR 50115, August Transport Airplane Directorate, FAA, 1601 Airworthiness Directive (AD) 95–21–09,
12, 2011). Lind Avenue SW., Renton, WA 98057–3356; for all Airbus Model A300 series
Note 1 to paragraph (h)(1) of this AD: telephone 425–227–1137; fax 425–227–1149. airplanes, and Airbus Model A300 B4–
Accomplishment of this action is required by Information may be emailed to: 9-ANM-116- 600, B4–600R, and F4–600R series
AD 2011–17–03, Amendment 39–16767 (76 AMOC-REQUESTS@faa.gov. Before using airplanes, and Model A300 C4–605R
FR 50115, August 12, 2011). any approved AMOC, notify your appropriate
(2) Rework the wiring and install fuses
Variant F airplanes (collectively called
principal inspector, or lacking a principal
packed in jiffy junctions in the power supply inspector, the manager of the local flight
Model A300–600 series airplanes). AD
wire of the solenoid in the left and right level standards district office/certificate holding 95–21–09 currently requires repetitive
control pilot valve, in accordance with the district office. The AMOC approval letter inspections for cracking of the No. 2 flap
Accomplishment Instructions of Fokker must specifically reference this AD. beams, and replacement of the flap
Service Bulletin SBF28–28–051, Revision 2, (2) Contacting the Manufacturer: For any beams, if necessary; and provides
dated November 3, 2014, including Drawing requirement in this AD to obtain corrective optional modifications for extending
W57231, Sheets 010 and 011, Issue K, actions from a manufacturer, the action must certain inspection thresholds, and an
undated; Drawing W58048, Sheet 2, dated be accomplished using a method approved optional terminating modification for
April 29, 2010; and Manual Change by the Manager, International Branch, ANM– certain inspections. Since we issued AD
Notification—Maintenance Document 116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency
95–21–09, we have determined that the
MCNM–F28–034, Rev 1, dated January 9, compliance times must be reduced. This
2014. Accomplishment of the actions in this (EASA); or Fokker B.V. Service’s EASA
Design Organization Approval (DOA). If proposed AD would reduce the
paragraph terminates the requirement of
approved by the DOA, the approval must compliance times for inspections and
paragraph (g) of AD 2011–21–01,
Amendment 39–16824 (76 FR 63156, October include the DOA-authorized signature. also reduce the number of airplanes
12, 2011), for the actions specified in the (l) Related Information
affected. We are proposing this AD to
Accomplishment Instructions of Fokker detect and correct cracking of the No. 2
(1) Refer to Mandatory Continuing flap beams, which could result in
Service Bulletin SBF28–28–051, Revision 2, Airworthiness Information (MCAI) European
dated November 3, 2014, including Drawing Aviation Safety Agency Airworthiness
rupture of the flap beams and reduced
W57231, Sheets 010 and 011, Issue K, Directive 2014–0107, dated May 7, 2014, for structural integrity of the airplane.
undated; Drawing W58048, Sheet 2, dated related information. This MCAI may be DATES: We must receive comments on
tkelley on DSK3SPTVN1PROD with PROPOSALS
April 29, 2010; and Manual Change found in the AD docket on the Internet at this proposed AD by March 7, 2016.
Notification—Maintenance Document http://www.regulations.gov. by searching for
MCNM–F28–034, Rev 1, dated January 9, ADDRESSES: You may send comments by
and locating Docket No. FAA–2015–8472.
2014, only. (2) For service information identified in
any of the following methods:
Note 2 to paragraph (h)(2) of this AD: this AD, contact Fokker Services B.V., • Federal eRulemaking Portal: Go to
Accomplishment of this action is required by Technical Services Dept., P.O. Box 1357, http://www.regulations.gov. Follow the
AD 2011–21–01, Amendment 39–16824 (76 2130 EL Hoofddorp, the Netherlands; instructions for submitting comments.
FR 63156, October 12, 2011). telephone +31 (0)88–6280–350; fax +31 • Fax: 202–493–2251.
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• Mail: U.S. Department of We will post all comments we France AD 1986–187–076(B)R4, which is
Transportation, Docket Operations, M– receive, without change, to http:// superseded, and requires those inspections to
30, West Building Ground Floor, Room www.regulations.gov, including any be accomplished at reduced thresholds and
W12–140, 1200 New Jersey Avenue SE., personal information you provide. We intervals.
This [EASA] AD has been revised to
Washington, DC 20590. will also post a report summarizing each correct typographical errors in some
• Hand Delivery: U.S. Department of substantive verbal contact we receive compliance times defined in Appendix 1,
Transportation, Docket Operations, M– about this proposed AD. Tables 1 and 2.
30, West Building Ground Floor, Room
Discussion The MCAI also reduces the number of
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5 On October 3, 1995, we issued AD airplanes identified in the applicability
p.m., Monday through Friday, except 95–21–09, Amendment 39–9395 (60 FR by exempting certain Model A300–600
Federal holidays. 53847, October 18, 1995). AD 95–21–09 airplanes on which certain Airbus
For service information identified in requires actions intended to address an modifications have been embodied. You
this proposed AD, contact Airbus SAS, unsafe condition on Airbus Model A300 may examine the MCAI in the AD
Airworthiness Office—EAW, 1 Rond and A300–600 series airplanes. docket on the Internet at http://
Point Maurice Bellonte, 31707 Blagnac Since we issued AD 95–21–09, www.regulations.gov by searching for
Cedex, France; telephone +33 5 61 93 36 Amendment 39–9395 (60 FR 53847, and locating Docket No. FAA–2015–
96; fax +33 5 61 93 44 51; email October 18, 1995), we have received a 8470.
account.airworth-eas@airbus.com; report that analyses showed a need for Related Service Information Under 1
Internet http://www.airbus.com. You reduced compliance times. CFR Part 51
may view this referenced service The European Aviation Safety Agency
(EASA), which is the Technical Agent Airbus has issued Service Bulletins
information at the FAA, Transport
for the Member States of the European A300–57–0116, Revision 07, dated
Airplane Directorate, 1601 Lind Avenue
Union, has issued EASA AD 2013– September 19, 2011; and A300–57–
SW., Renton, WA. For information on
0234R2, dated October 7, 2013 (referred 6005, Revision 06, dated November 14,
the availability of this material at the
to after this as the Mandatory 2013. This service information describes
FAA, call 425–227–1221.
Continuing Airworthiness Information, procedures for ultrasonic inspections of
Examining the AD Docket or ‘‘the MCAI’’), to correct an unsafe the number 2 flap beam base and side
You may examine the AD docket on condition for certain Airbus Model members. The actions described in this
the Internet at http:// A300 and A300–600 series airplanes. service information are intended to
www.regulations.gov by searching for The MCAI states: correct the unsafe condition identified
and locating Docket No. FAA–2015– in the MCAI. This service information is
Fatigue and ‘‘fail safe’’ tests developed on reasonably available because the
8470; or in person at the Docket a test specimen confirmed that cracks may
Management Facility between 9 a.m. interested parties have access to it
appear and propagate from the bolt holes of
and 5 p.m., Monday through Friday, the base member and the side members of
through their normal course of business
except Federal holidays. The AD docket flap beam No. 2. or by the means identified in the
The development of such cracks, if not ADDRESSES section.
contains this proposed AD, the
regulatory evaluation, any comments detected, could result in a rupture of flap
FAA’s Determination and Requirements
received, and other information. The beams No. 2, which could adversely affect
the structural integrity of the airframe. of This Proposed AD
street address for the Docket Operations To address this potential unsafe condition, This product has been approved by
office (telephone 800–647–5527) is in Airbus issued Service Bulletin (SB) A300– the aviation authority of another
the ADDRESSES section. Comments will 57–0116 and SB A300–57–6005 and DGAC country, and is approved for operation
be available in the AD docket shortly France issued AD 1986–187–076(B)
in the United States. Pursuant to our
after receipt. [available at http://ad.easa.europa.eu/blob/
1986-187-076%28B%29R4en.pdf/AD_F- bilateral agreement with the State of
FOR FURTHER INFORMATION CONTACT: Dan Design Authority, we have been notified
Rodina, Aerospace Engineer, 1986-187-076R4_1], later revised, to require a
repetitive inspection programme [and of the unsafe condition described in the
International Branch, ANM–116, corrective action] for A300 and A300–600 MCAI and service information
Transport Airplane Directorate, FAA, aeroplanes. [French AD 86–187–076(B)R3, referenced above. We are proposing this
1601 Lind Avenue SW., Renton, WA dated March 2, 1994, corresponds to FAA AD AD because we evaluated all pertinent
98057–3356; telephone 425–227–2125; 95–21–09, Amendment 39–9395 (60 FR information and determined an unsafe
fax 425–227–1149. 53847, October 18, 1995), which superseded condition exists and is likely to exist or
SUPPLEMENTARY INFORMATION: FAA AD 85–07–04, Amendment 39–5027 (49 develop on other products of the same
FR 45755, April 2, 1985).]
Comments Invited For A300 aeroplanes, and in the frame of
type design.
the Extended Service Goal (ESG) exercise, it Differences Between This Proposed AD
We invite you to send any written was shown that design changes (Airbus Mod.
relevant data, views, or arguments about and the MCAI or Service Information
4740/Airbus SB A300–57–0128 or Airbus
this proposed AD. Send your comments Mod. 5815/Airbus SB A300–57–0141) were Although the MCAI or service
to an address listed under the not sufficient to enable full ESG life without information allows further flight after
ADDRESSES section. Include ‘‘Docket No. inspections. cracks are found during compliance
FAA–2015–8470; Directorate Identifier For A300–600 aeroplanes, since DGAC with the required action, paragraph (m)
France AD 1986–187–076(B) was issued, a
tkelley on DSK3SPTVN1PROD with PROPOSALS
2013–NM–199–AD’’ at the beginning of of this proposed AD requires that you
your comments. We specifically invite fleet survey and updated Fatigue and Damage replace the flap beam before further
comments on the overall regulatory, Tolerance analyses have been performed in
order to substantiate the second A300–600
flight.
economic, environmental, and energy ESG2 exercise. Airbus SB A300–57–6005 has
aspects of this proposed AD. We will Explanation of ‘‘RC’’ Procedures and
been revised accordingly to decrease the Tests in Service Information
consider all comments received by the inspection thresholds and intervals.
closing date and may amend this For the reasons described above, this The FAA worked in conjunction with
proposed AD based on those comments. [EASA] AD retains the requirements of DGAC industry, under the Airworthiness
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Directive Implementation Aviation Authority for This Rulemaking § 39.13 [Amended]
Rulemaking Committee (ARC), to Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by
enhance the AD system. One specifies the FAA’s authority to issue removing Airworthiness Directive (AD)
enhancement was a new process for rules on aviation safety. Subtitle I, 95–21–09, Amendment 39–9395 (60 FR
annotating which procedures and tests 53847, October 18, 1995), and adding
section 106, describes the authority of
in the service information are required the following new AD:
the FAA Administrator. ‘‘Subtitle VII:
for compliance with an AD. Airbus: Docket No. FAA–2015–8470;
Aviation Programs,’’ describes in more
Differentiating these procedures and Directorate Identifier 2013–NM–199–AD.
detail the scope of the Agency’s
tests from other tasks in the service
authority. (a) Comments Due Date
information is expected to improve an
We are issuing this rulemaking under We must receive comments by March 7,
owner’s/operator’s understanding of
the authority described in ‘‘Subtitle VII, 2016.
crucial AD requirements and help
provide consistent judgment in AD Part A, Subpart III, Section 44701:
General requirements.’’ Under that (b) Affected ADs
compliance. The procedures and tests This AD replaces AD 95–21–09,
identified as Required for Compliance section, Congress charges the FAA with
promoting safe flight of civil aircraft in Amendment 39–9395 (60 FR 53847, October
(RC) in any service information have a 18, 1995).
direct effect on detecting, preventing, air commerce by prescribing regulations
resolving, or eliminating an identified for practices, methods, and procedures (c) Applicability
unsafe condition. the Administrator finds necessary for This AD applies to the Airbus airplanes
As specified in a NOTE under the safety in air commerce. This regulation identified in paragraphs (c)(1) through (c)(5)
Accomplishment Instructions of the is within the scope of that authority of this AD, certificated in any category.
because it addresses an unsafe condition (1) Model Airbus Model A300 B2–1A, B2–
specified service information, 1C, B2K–3C, B2–203, B4–2C, B4–103, and
procedures and tests that are identified that is likely to exist or develop on
products identified in this rulemaking B4–203 airplanes, all manufacturer serial
as RC in any service information must numbers (MSNs).
be done to comply with the proposed action. (2) Airbus Model A300 B4–601, B4–603,
AD. However, procedures and tests that Regulatory Findings B4–620, B4–622, B4–605R, and B4–622R
are not identified as RC are airplanes, all MSNs.
recommended. Those procedures and We determined that this proposed AD (3) Airbus Model A300 F4–605R, all MSNs,
tests that are not identified as RC may would not have federalism implications except those airplanes on which both Airbus
be deviated from using accepted under Executive Order 13132. This Modifications 11133 and 12699 have been
proposed AD would not have a embodied.
methods in accordance with the (4) Airbus Model A300 F4–622R airplanes,
operator’s maintenance or inspection substantial direct effect on the States, on
all MSNs, except those airplanes on which
program without obtaining approval of the relationship between the national
all Airbus Modifications 11133, 12047,
an alternative method of compliance Government and the States, or on the 12048, and 12050 have been embodied, and
(AMOC), provided the procedures and distribution of power and except those airplanes on which both Airbus
tests identified as RC can be done and responsibilities among the various Modifications 11133 and 12699 have been
the airplane can be put back in an levels of government. embodied.
airworthy condition. Any substitutions For the reasons discussed above, I (5) Airbus Model A300 C4–605R Variant F
certify this proposed regulation: airplanes, all MSNs.
or changes to procedures or tests
identified as RC will require approval of 1. Is not a ‘‘significant regulatory (d) Subject
an AMOC. action’’ under Executive Order 12866; Air Transport Association (ATA) of
2. Is not a ‘‘significant rule’’ under the America Code 57, Wings.
Costs of Compliance DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); (e) Reason
We estimate that this proposed AD
affects 49 airplanes of U.S. registry. 3. Will not affect intrastate aviation in This AD was prompted by a determination
The actions that are required by AD Alaska; and that the compliance times must be reduced.
95–21–09, Amendment 39–9395 (60 FR We are issuing this AD to detect and correct
4. Will not have a significant cracking of the No. 2 flap beams, which
53847, October 18, 1995), and retained economic impact, positive or negative, could result in rupture of the flap beams and
in this proposed AD take about 6 work- on a substantial number of small entities reduced structural integrity of the airplane.
hours per product, at an average labor under the criteria of the Regulatory
rate of $85 per work-hour. Required Flexibility Act. (f) Compliance
parts cost about $0 per product. Based Comply with this AD within the
on these figures, the estimated cost of List of Subjects in 14 CFR Part 39 compliance times specified, unless already
the actions that were required by AD Air transportation, Aircraft, Aviation done.
95–21–09 is $510 per product, per safety, Incorporation by reference, (g) Retained Inspection and Corrective
inspection cycle. Safety. Actions for Model A300 Series Airplanes,
We also estimate that it would take With Note 3 of AD 95–21–09, Amendment
about 6 work-hours per product to The Proposed Amendment 39–9395 (60 FR 53847, October 18, 1995),
comply with the basic requirements of Accordingly, under the authority Incorporated and Additional Terminating
this proposed AD. The average labor delegated to me by the Administrator, Provisions
rate is $85 per work-hour. Based on the FAA proposes to amend 14 CFR part This paragraph restates the requirements of
paragraph (a) of AD 95–21–09, Amendment
tkelley on DSK3SPTVN1PROD with PROPOSALS
these figures, we estimate the cost of 39 as follows:
this proposed AD on U.S. operators to 39–9395 (60 FR 53847, October 18, 1995),
PART 39—AIRWORTHINESS with Note 3 of AD 95–21–09 incorporated
be $24,990 per inspection cycle, or $510 and additional terminating provisions. For
per product, per inspection cycle. DIRECTIVES
Model A300 series airplanes: Prior to the
We have received no definitive data accumulation of 15,000 total landings, or
that would enable us to provide cost ■ 1. The authority citation for part 39
within the next 120 days after May 9, 1985
estimates for the on-condition actions continues to read as follows: (the effective date of AD 85–07–04,
specified in this proposed AD. Authority: 49 U.S.C. 106(g), 40113, 44701. Amendment 39–5027 (49 FR 45755, April 2,
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obtaining approval of an AMOC, provided this AD to prevent an ignition source in Comments Invited
the procedures and tests identified as RC can the fuel tank vapor space, which could
be done and the airplane can be put back in We invite you to send any written
result in a fuel tank explosion and relevant data, views, or arguments about
an airworthy condition. Any substitutions or consequent loss of the airplane.
changes to procedures or tests identified as this proposed AD. Send your comments
RC require approval of an AMOC. DATES: We must receive comments on to an address listed under the
this proposed AD by March 7, 2016. ADDRESSES section. Include ‘‘Docket No.
(p) Related Information
ADDRESSES: You may send comments, FAA–2015–8467; Directorate Identifier
(1) Refer to Mandatory Continuing 2014–NM–107–AD’’ at the beginning of
Airworthiness Information (MCAI) EASA AD using the procedures found in 14 CFR
11.43 and 11.45, by any of the following your comments. We specifically invite
2013–0234R2, dated October 7, 2013, for
related information. This MCAI may be methods: comments on the overall regulatory,
economic, environmental, and energy
found in the AD docket on the Internet at • Federal eRulemaking Portal: Go to
http://www.regulations.gov by searching for aspects of this proposed AD. We will
http://www.regulations.gov. Follow the
and locating Docket No. FAA–2015–8470. consider all comments received by the
instructions for submitting comments.
(2) For service information identified in closing date and may amend this
this AD, contact Airbus SAS, Airworthiness • Fax: 202–493–2251. proposed AD based on those comments.
Office—EAW, 1 Rond Point Maurice • Mail: U.S. Department of We will post all comments we
Bellonte, 31707 Blagnac Cedex, France; Transportation, Docket Operations, M– receive, without change, to http://
telephone +33 5 61 93 36 96; fax +33 5 61 30, West Building Ground Floor, Room www.regulations.gov, including any
93 44 51; email account.airworth-eas@ W12–140, 1200 New Jersey Avenue SE., personal information you provide. We
airbus.com; Internet http://www.airbus.com.
Washington, DC 20590. will also post a report summarizing each
You may view this service information at the
FAA, Transport Airplane Directorate, 1601 • Hand Delivery: U.S. Department of substantive verbal contact we receive
Lind Avenue SW., Renton, WA. For Transportation, Docket Operations, M– about this proposed AD.
information on the availability of this 30, West Building Ground Floor, Room Discussion
material at the FAA, call 425–227–1221. W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5 The European Aviation Safety Agency
Issued in Renton, Washington, on January
6. 2016. p.m., Monday through Friday, except (EASA), which is the Technical Agent
Federal holidays. for the Member States of the European
Victor Wicklund,
For service information identified in Union, has issued EASA Airworthiness
Acting Manager, Transport Airplane
this proposed AD, contact Fokker Directive 2014–0108, dated May 8, 2014
Directorate, Aircraft Certification Service.
Services B.V., Technical Services Dept., (referred to after this the Mandatory
[FR Doc. 2016–00634 Filed 1–19–16; 8:45 am]
P.O. Box 1357, 2130 EL Hoofddorp, the Continuing Airworthiness Information,
BILLING CODE 4910–13–P
Netherlands; telephone +31 (0)88–6280– or ‘‘the MCAI’’), to correct an unsafe
350; fax +31 (0)88–6280–111; email condition for all Fokker Services B.V.
technicalservices@fokker.com; Internet Model F.28 Mark 1000, 2000, 3000, and
DEPARTMENT OF TRANSPORTATION
http://www.myfokkerfleet.com. You may 4000 airplanes. The MCAI states:
Federal Aviation Administration view this referenced service information Prompted by an accident * * *, the
at the FAA, Transport Airplane Federal Aviation Administration (FAA)
14 CFR Part 39 Directorate, 1601 Lind Avenue SW., published Special Federal Aviation
Regulation (SFAR) 88 [(66 FR 23086, May 7,
[Docket No. FAA–2015–8467; Directorate Renton, WA. For information on the 2001)], and the Joint Aviation Authorities
Identifier 2014–NM–107–AD] availability of this material at the FAA, (JAA) published Interim Policy INT/POL/25/
call 425–227–1221. 12.
RIN 2120–AA64 The review conducted by Fokker Services
Examining the AD Docket on the Fokker F28 design, in response to
Airworthiness Directives; Fokker these regulations, revealed that no controlled
Services B.V. Airplanes You may examine the AD docket on
the Internet at http:// bonding provisions are present on a number
of critical locations, inside the fuel tank or
AGENCY: Federal Aviation www.regulations.gov by searching for connected to the fuel tank wall.
Administration (FAA), DOT. and locating Docket No. FAA–2015– This condition, if not corrected, could
ACTION: Notice of proposed rulemaking 8467; or in person at the Docket create an ignition source in the fuel tank
(NPRM). Operations office between 9 a.m. and 5 vapour space, possibly resulting in a fuel
p.m., Monday through Friday, except tank explosions and consequent loss of the
SUMMARY: We propose to adopt a new Federal holidays. The AD docket aeroplane.
airworthiness directive (AD) for all contains this proposed AD, the To address this potential unsafe condition,
Fokker Services B.V. Model F.28 Mark Fokker Services developed a set of fuel tank
regulatory evaluation, any comments
1000, 2000, 3000, and 4000 airplanes. bonding modifications.
received, and other information. The For the reasons described above, this
This proposed AD was prompted by a street address for the Docket Operations [EASA] AD requires the Installation of
design review that revealed no office (telephone 800–647–5527) is in additional and improved bonding provisions
controlled bonding provisions are the ADDRESSES section. Comments will [and a revision of the maintenance or
present on a number of critical locations be available in the AD docket shortly inspection program, as applicable]. These
inside the fuel tanks or connected to the after receipt. modifications require opening of the fuel
walls of the fuel tanks. This proposed tank access panels.
FOR FURTHER INFORMATION CONTACT: Tom More information on this subject can be
tkelley on DSK3SPTVN1PROD with PROPOSALS
AD would require installing additional
and improved bonding provisions in the Rodriguez, Aerospace Engineer, found in Fokker Services All Operators
fuel tanks and revising the airplane International Branch, ANM–116, Message AOF28.038#02.
maintenance or inspection program, as Transport Airplane Directorate, FAA, You may examine the MCAI in the
applicable, by incorporating fuel 1601 Lind Avenue SW., Renton, WA AD docket on the Internet at http://
airworthiness limitation items and 98057–3356; telephone 425–227–1137; www.regulations.gov by searching for
critical design configuration control fax 425–227–1149. and locating Docket No. FAA–2015–
limitations (CDCCLs). We are proposing SUPPLEMENTARY INFORMATION: 8467.
VerDate Sep<11>2014 16:49 Jan 19, 2016 Jkt 238001 PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 E:\FR\FM\20JAP1.SGM 20JAP1](https://thefederalregister.org/doc/81_FR_3057/page/7.svg)
Document Created: 2016-01-19 23:43:34
Document Modified: 2016-01-19 23:43:34
| 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 March 7, 2016. | |
| 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 | 81 FR 3045 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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