81 FR 71596 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 201 (October 18, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 201 (October 18, 2016)
| Page Range | 71596-71602 | |
| FR Document | 2016-23261 |
[Federal Register Volume 81, Number 201 (Tuesday, October 18, 2016)] [Rules and Regulations] [Pages 71596-71602] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-23261] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-8470; Directorate Identifier 2013-NM-199-AD; Amendment 39-18674; AD 2016-20-08] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding 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 required repetitive inspections for cracking of the No. 2 flap beams, and replacement of the flap beams, if necessary; and provided optional modifications for extending certain inspection thresholds, and an optional terminating modification for certain inspections. This new AD requires reduced compliance times for inspections and also reduces the number of airplanes affected. 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. DATES: This AD is effective November 22, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 22, 2016. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of November 17, 1995 (60 FR 53847, October 18, 1995). ADDRESSES: For service information identified in this final rule, 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 [[Page 71597]] this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-8470. 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800- 647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: 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: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995) (``AD 95-21-09''). AD 95-21-09 applied to all Airbus Model A300 and A300-600 series airplanes. The NPRM published in the Federal Register on January 20, 2016 (81 FR 3045) (``the NPRM''). 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 [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 1986-187-076(B), 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, which superseded FAA AD 85-07-04, Amendment 39-5027 (50 FR 13013, 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. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Request To Remove Certain Exceptions in the Proposed Applicability United Parcel Service (UPS) requested that the applicability exceptions in paragraphs (c)(3) and (c)(4) of the proposed AD be revised to remove Airbus Modifications 11133 and 12699 as exceptions. UPS stated that the exceptions provided in paragraphs (c)(3) and (c)(4) of the proposed AD are inconsistent with the effectivity specified in the service information referenced in the NPRM. UPS pointed out that the effectivity of Airbus Service Bulletin A300-57-6005, Revision 06, dated November 14, 2013, applies to airplanes with manufacturer serial number (MSN) 775 and subsequent, with MSN 775 as the production cut-in for Airbus Modification 11133. UPS asserted that this service bulletin's effectivity also does not list all post-modification 11133 and 12699 airplanes. UPS stated that the determining factor for the service information effectivity is whether an airplane is approved for the extended service goal (ESG-2) operational life or not. UPS also pointed out that the effectivity of Airbus Service Bulletin A300-57- 6005, Revision 06, dated November 14, 2013, does not include Model A300 F4-622 airplanes that are in a UPS configuration (Airbus Modifications 11133, 12047, 12048, 12050, but not 12699), which would mean UPS would need to request an alternative method of compliance (AMOC) or other means to show compliance for those airplanes. We acknowledge the concern UPS identified regarding the clarity of the AD applicability. Therefore, we have revised the applicability to match the related MCAI, which should address UPS's concern. We do not intend for this AD to affect UPS's specified A300 F4-622R configuration (Airbus Modifications 11133, 12047, 12048, 12050, but not 12699). We have revised paragraph (c)(4) of this AD accordingly. However, we do not agree to delete references to both Airbus Modifications 11133 and 12699 from the applicability of this AD since there are airplanes with these modifications in the worldwide fleet that might be imported and placed on the U.S. Register. Therefore, we have not removed references to Airbus Modifications 11133 and 12699 from paragraphs (c)(3) and (c)(4) of this AD. Request To Remove Typographical Error UPS requested that paragraph (l)(2) of the proposed AD be revised to remove a typographical error that resulted in listing Model A300 F4- 622R airplanes twice. We agree that there was a typographical error, as described by UPS. We have removed the redundant reference in this AD. Additional Change to This AD We added new paragraph (m) to this AD to specify clearly the required calculation method for establishing the average flight times (AFT) for the compliance times for certain inspections required by this AD. We also redesignated subsequent paragraphs. Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously [[Page 71598]] and minor editorial changes. We have determined that these changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletins A300-57-0116, Revision 07, dated September 19, 2011, including Appendixes A and B; and A300-57- 6005, Revision 06, dated November 14, 2013. This service information describes procedures for ultrasonic inspections of the No. 2 flap beam base and side members. These documents are distinct since they apply to different airplane models. 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. Costs of Compliance We estimate that this AD affects 49 airplanes of U.S. registry. The actions required by AD 95-21-09 and retained in this 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 takes about 6 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this 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 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 AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), and adding the following new AD: 2016-20-08 Airbus: Amendment 39-18674; Docket No. FAA-2015-8470; Directorate Identifier 2013-NM-199-AD. (a) Effective Date This AD is effective November 22, 2016. (b) Affected ADs This AD replaces AD 95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995) (``AD 95-21-09''). (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) 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 the modifications identified in paragraph (c)(4)(i) or (c)(4)(ii) of this AD have been embodied. (i) All Airbus Modifications 11133, 12047, 12048, and 12050 have been embodied. (ii) 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 Incorporated and Additional Terminating Provisions This paragraph restates the requirements of paragraph (a) of AD 95-21-09, 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 (50 FR 13013, April 2, 1985) (``AD 85-07-04'')), 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. [[Page 71599]] (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 millimeters (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, 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, 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. (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 No. 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. (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 No. 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, 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 Incorporated and Changes To Terminating Action This paragraph restates the provisions of paragraph (e) of AD 95-21-09, 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, Revision 4, dated July 25, 1994 (Modification No. 5815), 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, was accomplished concurrently with Airbus Service Bulletin A300-57-6006, Revision 3, dated December 16, 1993 (Modification No. 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 No. 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; or Airbus Service Bulletin A300-57-6005, Revision 06, dated November 14, 2013; as applicable. For the purposes of this AD, average flight time [[Page 71600]] (AFT) must be established as specified in paragraph (m) of this AD. 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 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 for Compliance times for airplanes with an Airplane configuration airplanes with an AFT of more than or AFT of less than 1.5 equal to 1.5 ------------------------------------------------------------------------ Model A300 B2-1A, B2-1C, B2K- Within 15,000 flight Within 15,000 flight 3C, B2-203 airplanes on cycles or 16,900 cycles or 16,900 which Airbus Modifications flight hours since flight hours since 4740 and 5815 have not been first flight of the first flight of the embodied. airplane, whichever airplane, whichever occurs first. occurs first. Model A300 B4-103 airplanes Within 15,000 flight Within 15,000 flight on which Airbus cycles or 20,500 cycles or 20,500 Modifications 4740 and 5815 flight hours since flight hours since have not been embodied. first flight of the first flight of the airplane, whichever airplane, whichever occurs first. occurs first. Model A300 B4-2C, and B4-203 Within 16,200 flight Within 15,000 flight airplanes on which Airbus cycles or 22,200 cycles or 34,000 Modifications 4740 and 5815 flight hours since flight hours since have not been embodied. first flight of the first flight of the airplane, whichever airplane, whichever occurs first. occurs first. Model A300 B2-1A, B2-1C, B2K- Within 12,000 flight Within 12,000 flight 3C, B2-203 airplanes on cycles or 13,500 cycles or 13,500 which Airbus Modification flight hours since flight hours since 4740 has been embodied. embodiment of embodiment of Airbus Modification Airbus Modification 4740, whichever 4740, whichever occurs first. occurs first. Model A300 B4-103 airplanes Within 12,000 flight Within 12,000 flight on which Airbus cycles or 16,400 cycles or 16,400 Modification 4740 has been flight hours since flight hours since embodied. embodiment of embodiment of Airbus Modification Airbus Modification 4740, whichever 4740, whichever occurs first. occurs first. Model A300 B4-2C, and B4-203 Within 12,900 flight Within 12,000 flight airplanes on which Airbus cycles or 17,700 cycles or 27,200 Modification 4740 has been flight hours since flight hours since embodied. embodiment of embodiment of Airbus Modification Airbus Modification 4740, whichever 4740, whichever occurs first. occurs first. Model A300 B2-1A, B2-1C, B2K- Within 33,000 flight Within 33,000 flight 3C, B2-203 airplanes on cycles or 37,200 cycles or 37,200 which Airbus Modification flight hours since flight hours since 5815 has been embodied and embodiment of embodiment of no bolt larger than \7/16\- Airbus Modification Airbus Modification inch diameter is fitted. 5815, whichever 5815, whichever occurs first. occurs first. Model A300 B4-103 airplanes Within 33,000 flight Within 33,000 flight on which Airbus cycles or 45,200 cycles or 45,200 Modification 5815 has been flight hours since flight hours since embodied and no bolt larger embodiment of embodiment of than \7/16\-inch diameter Airbus Modification Airbus Modification is fitted. 5815, whichever 5815, whichever occurs first. occurs first. Model A300 B4-2C, and B4-203 Within 35,600 flight Within 33,000 flight airplanes on which Airbus cycles or 48,800 cycles or 74,900 Modification 5815 has been flight hours since flight hours since embodied and no bolt larger embodiment of embodiment of than \7/16\-inch diameter Airbus Modification Airbus Modification is fitted. 5815, whichever 5815, whichever occurs first. occurs first. Model A300 B2-1A, B2-1C, B2K- Within 22,000 flight Within 22,000 flight 3C, B2-203 airplanes on cycles or 24,800 cycles or 24,800 which Airbus Modification flight hours since flight hours since 5815 has been embodied and embodiment of embodiment of at least one bolt with a Airbus Modification Airbus Modification \15/32\-inch diameter is 5815, whichever 5815, whichever fitted. occurs first. occurs first. Model A300 B4-103 airplanes Within 22,000 flight Within 22,000 flight on which Airbus cycles or 30,100 cycles or 30,100 Modification 5815 has been flight hours since flight hours since embodied and at least one embodiment of embodiment of bolt with a \15/32\-inch Airbus Modification Airbus Modification diameter is fitted. 5815, whichever 5815, whichever occurs first. occurs first. Model A300 B4-2C, and B4- Within 23,700 flight Within 22,000 flight 203, airplanes on which cycles or 32,500 cycles or 49,900 Airbus Modification 5815 flight hours since flight hours since has been embodied and at embodiment of embodiment of least one bolt with a \15/ Airbus Modification Airbus Modification 32\-inch diameter is fitted. 5815, whichever 5815, whichever occurs first. occurs first. ------------------------------------------------------------------------ Table 2 to Paragraph (1) of This AD--Compliance Times for Model A300-600 Series Airplanes ------------------------------------------------------------------------ Compliance times for Compliance times for airplanes with an Airplane configuration airplanes with an AFT of more than or AFT of less than 1.5 equal to 1.5 ------------------------------------------------------------------------ Model A300-600 series Within 16,200 flight Within 15,000 flight airplanes on which Airbus cycles or 24,300 cycles or 32,400 Modification 5815 and flight hours since flight hours since Airbus Modification 11133 first flight of the first flight of the have not been embodied. airplane, whichever airplane, whichever occurs first. occurs first. Model A300-600 series Within 35,600 flight Within 33,000 flight airplanes on which Airbus cycles or 53,400 cycles or 71,200 Modification 5815 has been flight hours since flight hours since embodied and no bolt larger embodiment of embodiment of than \7/16\-inch diameter Airbus Modification Airbus Modification is fitted. 5815, whichever 5815, whichever occurs first. occurs first. Model A300-600 series Within 23,700 flight Within 22,000 flight airplanes on which Airbus cycles or 35,600 cycles or 47,500 Modification 5815 has been flight hours since flight hours since embodied and at least one embodiment of embodiment of bolt \15/32\-inch diameter Airbus Modification Airbus Modification is fitted. 5815, whichever 5815, whichever occurs first. occurs first. [[Page 71601]] Model A300-600 series Within 35,600 flight Within 33,000 flight airplanes on which Airbus cycles or 53,400 cycles or 71,200 Modification 11133 has been flight hours since flight hours since embodied. first flight, first flight, whichever occurs whichever occurs first. first. ------------------------------------------------------------------------ Table 3 to Paragraph (1) of This AD--Repetitive Inspection Intervals ------------------------------------------------------------------------ Repetitive interval Repetitive interval (not to exceed) for Airplane models (not to exceed) for airplanes with an airplanes with an AFT equal to or more AFT of less than 1.5 than 1.5 ------------------------------------------------------------------------ A300 B2-1A, B2-1C, B2K-3C, 1,500 flight cycles 1,500 flight cycles B2-203. or 1,600 flight or 1,600 flight hours, whichever hours, whichever occurs first. occurs first. A300 B4-103 airplanes....... 1,500 flight cycles 1,500 flight cycles or 2,000 flight or 2,000 flight hours, whichever hours, whichever occurs first. occurs first. A300 B4-2C, and B4-203...... 1,600 flight cycles 1,500 flight cycles or 2,200 flight or 3,400 flight hours, whichever hours, whichever occurs first. occurs first. A300-600 series airplanes... 1,600 flight cycles 1,500 flight cycles or 2,400 flight or 3,200 flight hours, whichever hours, whichever occurs first. occurs first. ------------------------------------------------------------------------ (m) Calculating the AFT For the purpose of this AD, the AFT must be established as specified in paragraphs (m)(1), (m)(2), and (m)(3) of this AD. (1) For the initial inspection, the average flight time is the total accumulated flight hours, counted from take-off to touch-down, divided by the total accumulated flight cycles at the effective date of this AD. (2) For the first repeated inspection interval, the average flight time is the total accumulated flight hours divided by the total accumulated flight cycles at the time of the inspection threshold. (3) For all inspection intervals onward, the average flight time is the flight hours divided by the flight cycles accumulated between the last two inspections. (n) 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. (o) 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) 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 (o)(2)(i) through (o)(2)(x) of this AD. (i) 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). (ii) Airbus Service Bulletin A300-57-6005, Revision 03, dated November 25, 1997. (iii) Airbus Service Bulletin A300-57-6005, Revision 04, dated October 25, 1999. (iv) Airbus Service Bulletin A300-57-6005, Revision 05, dated April 25, 2013. (v) Airbus Service Bulletin A300-57-116, Revision 1, dated August 27, 1983. (vi) Airbus Service Bulletin A300-57-116, Revision 2, dated April 24, 1984. (vii) Airbus Service Bulletin A300-57-116, Revision 3, dated July 20, 1984. (viii) Airbus Service Bulletin A300-57-116, Revision 4, dated August 13, 1986. (ix) Airbus Service Bulletin A300-57-116, Revision 5, dated July 10, 1989. (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). (p) 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. (ii) AMOCs approved previously for AD 95-21-09, 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 (n) 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 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. (q) 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) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (r)(5) and (r)(6) of this AD. [[Page 71602]] (r) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on November 22, 2016. (i) Airbus Service Bulletin A300-57-0116, Revision 07, dated September 19, 2011, including Appendixes A and B. Only the first page of Appendixes A and B of this document are identified as appendixes. (ii) Airbus Service Bulletin A300-57-6005, Revision 06, dated November 14, 2013. (4) The following service information was approved for IBR on November 17, 1995 (60 FR 53847, October 18, 1995). (i) Airbus Service Bulletin A300-57-116, Revision 6, dated July 16, 1993, which contains the following effective pages: Pages 1 through 11 of this document are identified as Revision 6, dated July 16, 1993. (ii) Airbus Service Bulletin A300-57-128, Revision 3, dated January 26, 1990, which contains the following effective pages: Page 1 is identified as Revision 3, dated January 26, 1990; pages 2 through 5 are identified as Revision 1, dated February 7, 1986; and pages 6 through 14 are identified as the original issue, dated August 27, 1983. (iii) Airbus Service Bulletin A300-57-141, Revision 7, dated July 16, 1993, which contains the following effective pages: Pages 1 through 24 of this document are identified as Revision 7, dated July 16, 1993. (iv) Airbus Service Bulletin A300-57-6005, Revision 2, dated December 16, 1993, which contains the following effective pages: Pages 1 through 4 are identified as Revision 2, dated December 16, 1993; pages 5 through 7 and 9 are identified as Revision 1, dated February 26, 1993; and page 8 is identified as the original issue, dated August 13, 1986. (v) Airbus Service Bulletin A300-57-6006, Revision 4, dated July 25, 1994, which contains the following effective pages: Pages 1, 2, 5, and 7 are identified as Revision 4, dated July 25, 1994; and pages 3, 4, 6, and 8 through 20 are identified as Revision 3, dated December 16, 1993. (5) 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. (6) 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. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on September 19, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-23261 Filed 10-17-16; 8:45 am] BILLING CODE 4910-13-P
![71596 Federal Register / Vol. 81, No. 201 / Tuesday, October 18, 2016 / Rules and Regulations
required by paragraph (k)(1) or (k)(2) of this with this AD; any procedures or tests that are DEPARTMENT OF TRANSPORTATION
AD, as applicable. not identified as RC are recommended. Those
(1) For an airplane that does not have an procedures and tests that are not identified Federal Aviation Administration
affected fuel pump installed: After the as RC may be deviated from using accepted
identification of the fuel pump part numbers methods in accordance with the operator’s 14 CFR Part 39
required by paragraph (g) of this AD, no
maintenance or inspection program without
person may install an affected fuel pump on [Docket No. FAA–2015–8470; Directorate
obtaining approval of an AMOC, provided
the airplane. Identifier 2013–NM–199–AD; Amendment
(2) For an airplane that has an affected fuel the procedures and tests identified as RC can 39–18674; AD 2016–20–08]
pump installed: After modification of the be done and the airplane can be put back in
airplane as required by paragraph (h) of this an airworthy condition. Any substitutions or RIN 2120–AA64
AD, no person may install an affected fuel changes to procedures or tests identified as
pump on the airplane. RC require approval of an AMOC. Airworthiness Directives; Airbus
Airplanes
(l) Credit for Previous Actions (n) Related Information
This paragraph provides credit for actions AGENCY: Federal Aviation
(1) Refer to Continuing Airworthiness
required by paragraphs (g) and (h) of this AD, Administration (FAA), Department of
Information (MCAI) EASA AD 2015–0194,
if those actions were performed before the dated September 22, 2015, for related
Transportation (DOT).
effective date of this AD using the applicable information. You may examine the MCAI on ACTION: Final rule.
service information specified in paragraphs
the Internet at http://www.regulations.gov by
(l)(1), (l)(2), (l)(3), and (l)(4) of this AD. This SUMMARY: We are superseding
service information is not incorporated by searching for and locating Docket No. FAA–
Airworthiness Directive (AD) 95–21–09
reference in this AD. 2016–6418.
for all Airbus Model A300 series
(1) Airbus Service Bulletin A330–28–3127, (o) Material Incorporated by Reference airplanes, and Airbus Model A300 B4–
dated July 14, 2015.
(1) The Director of the Federal Register 600, B4–600R, and F4–600R series
(2) Airbus Service Bulletin A330–28–3127,
Revision 01, dated September 24, 2015. approved the incorporation by reference airplanes, and Model A300 C4–605R
(3) Airbus Service Bulletin A340–28–4138, (IBR) of the service information listed in this Variant F airplanes (collectively called
dated July 14, 2015. paragraph under 5 U.S.C. 552(a) and 1 CFR Model A300–600 series airplanes). AD
(4) Airbus Service Bulletin A340–28–5060, part 51. 95–21–09 required repetitive
dated July 14, 2015. (2) You must use this service information inspections for cracking of the No. 2 flap
(m) Other FAA AD Provisions as applicable to do the actions required by beams, and replacement of the flap
this AD, unless this AD specifies otherwise. beams, if necessary; and provided
The following provisions also apply to this
(i) Airbus Service Bulletin A330–28–3127, optional modifications for extending
AD:
(1) Alternative Methods of Compliance Revision 02, dated April 14, 2016. certain inspection thresholds, and an
(AMOCs): The Manager, International (ii) Airbus Service Bulletin A340–28–4138, optional terminating modification for
Branch, ANM–116, Transport Airplane Revision 01, dated September 24, 2015. certain inspections. This new AD
Directorate, FAA, has the authority to (iii) Airbus Service Bulletin A340–28– requires reduced compliance times for
approve AMOCs for this AD, if requested 5060, Revision 01, dated September 24, 2015. inspections and also reduces the
using the procedures found in 14 CFR 39.19. (3) For service information identified in number of airplanes affected. This AD
In accordance with 14 CFR 39.19, send your this AD, contact Airbus SAS, Airworthiness was prompted by a determination that
request to your principal inspector or local Office—EAL, 1 Rond Point Maurice Bellonte, the compliance times must be reduced.
Flight Standards District Office, as 31707 Blagnac Cedex, France; telephone: +33 We are issuing this AD to detect and
appropriate. If sending information directly
5 61 93 36 96; fax: +33 5 61 93 45 80; email: correct cracking of the No. 2 flap beams,
to the International Branch, send it to ATTN:
Vladimir Ulyanov, Aerospace Engineer, airworthiness.A330–A340@airbus.com; which could result in rupture of the flap
International Branch, ANM–116, Transport Internet: http://www.airbus.com. You may beams and reduced structural integrity
Airplane Directorate, FAA, 1601 Lind view this service information at the FAA, of the airplane.
Avenue SW., Renton, WA 98057–3356; Transport Airplane Directorate, 1601 Lind DATES: This AD is effective November
telephone: 425–227–1138; fax: 425–227– Avenue SW., Renton, WA. For information
22, 2016.
1149. Information may be emailed to: 9- on the availability of this material at the
The Director of the Federal Register
ANM-116-AMOC-REQUESTS@faa.gov. FAA, call 425–227–1221.
Before using any approved AMOC, notify approved the incorporation by reference
(4) You may view this service information
your appropriate principal inspector, or of certain publications listed in this AD
at the FAA, Transport Airplane Directorate,
lacking a principal inspector, the manager of as of November 22, 2016.
1601 Lind Avenue SW., Renton, WA. For
the local flight standards district office/ The Director of the Federal Register
information on the availability of this
certificate holding district office. The AMOC approved the incorporation by reference
material at the FAA, call 425–227–1221.
approval letter must specifically reference of certain other publications listed in
this AD. (5) You may view this service information
that is incorporated by reference at the
this AD as of November 17, 1995 (60 FR
(2) Contacting the Manufacturer: For any 53847, October 18, 1995).
requirement in this AD to obtain corrective National Archives and Records
actions from a manufacturer, the action must Administration (NARA). For information on ADDRESSES: For service information
be accomplished using a method approved the availability of this material at NARA, call identified in this final rule, contact
by the Manager, International Branch, ANM– 202–741–6030, or go to: http:// Airbus SAS, Airworthiness Office—
116, Transport Airplane Directorate, FAA; or www.archives.gov/federal-register/cfr/ibr- EAW, 1 Rond Point Maurice Bellonte,
the European Aviation Safety Agency locations.html. 31707 Blagnac Cedex, France; telephone
(EASA); or Airbus’s EASA Design +33 5 61 93 36 96; fax +33 5 61 93 44
Organization Approval (DOA). If approved by Issued in Renton, Washington, on
51; email account.airworth-eas@
Lhorne on DSK30JT082PROD with RULES
the DOA, the approval must include the September 26, 2016.
airbus.com; Internet http://
DOA-authorized signature. Dionne Palermo,
(3) Required for Compliance (RC): Except
www.airbus.com. You may view this
Acting Manager, Transport Airplane referenced service information at the
as provide by paragraph (j) of this AD, if any
Directorate, Aircraft Certification Service. FAA, Transport Airplane Directorate,
service information contains procedures or
tests that are identified as RC, those [FR Doc. 2016–23647 Filed 10–17–16; 8:45 am] 1601 Lind Avenue SW., Renton, WA.
procedures and tests must be done to comply BILLING CODE 4910–13–P For information on the availability of
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![Federal Register / Vol. 81, No. 201 / Tuesday, October 18, 2016 / Rules and Regulations 71597
this material at the FAA, call 425–227– France issued AD 1986–187–076(B), later effectivity also does not list all post-
1221. It is also available on the Internet revised, to require a repetitive inspection modification 11133 and 12699
at http://www.regulations.gov by programme [and corrective action] for A300 airplanes. UPS stated that the
and A300–600 aeroplanes. [French AD 86–
searching for and locating Docket No. 187–076(B)R3, dated March 2, 1994,
determining factor for the service
FAA–2015–8470. corresponds to FAA AD 95–21–09, which information effectivity is whether an
superseded FAA AD 85–07–04, Amendment airplane is approved for the extended
Examining the AD Docket
39–5027 (50 FR 13013, April 2, 1985).] service goal (ESG–2) operational life or
You may examine the AD docket on For A300 aeroplanes, and in the frame of not. UPS also pointed out that the
the Internet at http:// the Extended Service Goal (ESG) exercise, it effectivity of Airbus Service Bulletin
www.regulations.gov by searching for was shown that design changes (Airbus Mod. A300–57–6005, Revision 06, dated
and locating Docket No. FAA–2015– 4740/Airbus SB A300–57–0128 or Airbus
November 14, 2013, does not include
Mod. 5815/Airbus SB A300–57–0141) were
8470; or in person at the Docket Model A300 F4–622 airplanes that are
not sufficient to enable full ESG life without
Management Facility between 9 a.m. inspections. in a UPS configuration (Airbus
and 5 p.m., Monday through Friday, For A300–600 aeroplanes, since DGAC Modifications 11133, 12047, 12048,
except Federal holidays. The AD docket France AD 1986–187–076(B) was issued, a 12050, but not 12699), which would
contains this AD, the regulatory fleet survey and updated Fatigue and Damage mean UPS would need to request an
evaluation, any comments received, and Tolerance analyses have been performed in alternative method of compliance
other information. The address for the order to substantiate the second A300–600 (AMOC) or other means to show
Docket Office (telephone 800–647–5527) ESG2 exercise. Airbus SB A300–57–6005 has
compliance for those airplanes.
been revised accordingly to decrease the
is Docket Management Facility, U.S. We acknowledge the concern UPS
inspection thresholds and intervals.
Department of Transportation, Docket For the reasons described above, this identified regarding the clarity of the
Operations, M–30, West Building [EASA] AD retains the requirements of DGAC AD applicability. Therefore, we have
Ground Floor, Room W12–140, 1200 France AD 1986–187–076(B)R4, which is revised the applicability to match the
New Jersey Avenue SE., Washington, superseded, and requires those inspections to related MCAI, which should address
DC 20590. be accomplished at reduced thresholds and UPS’s concern. We do not intend for
FOR FURTHER INFORMATION CONTACT: Dan intervals.
this AD to affect UPS’s specified A300
This [EASA] AD has been revised to
Rodina, Aerospace Engineer, correct typographical errors in some F4–622R configuration (Airbus
International Branch, ANM–116, compliance times defined in Appendix 1, Modifications 11133, 12047, 12048,
Transport Airplane Directorate, FAA, Tables 1 and 2. 12050, but not 12699). We have revised
1601 Lind Avenue SW., Renton, WA paragraph (c)(4) of this AD accordingly.
The MCAI also reduces the number of
98057–3356; telephone 425–227–2125; However, we do not agree to delete
airplanes identified in the applicability
fax 425–227–1149. references to both Airbus Modifications
by exempting certain Model A300–600
SUPPLEMENTARY INFORMATION: 11133 and 12699 from the applicability
airplanes on which certain Airbus
of this AD since there are airplanes with
Discussion modifications have been embodied. You
these modifications in the worldwide
may examine the MCAI in the AD
We issued a notice of proposed fleet that might be imported and placed
docket on the Internet at http://
rulemaking (NPRM) to amend 14 CFR on the U.S. Register. Therefore, we have
www.regulations.gov by searching for
part 39 to supersede AD 95–21–09, not removed references to Airbus
and locating Docket No. FAA–2015–
Amendment 39–9395 (60 FR 53847, Modifications 11133 and 12699 from
8470.
October 18, 1995) (‘‘AD 95–21–09’’). AD paragraphs (c)(3) and (c)(4) of this AD.
95–21–09 applied to all Airbus Model Comments
Request To Remove Typographical
A300 and A300–600 series airplanes. We gave the public the opportunity to Error
The NPRM published in the Federal participate in developing this AD. The
Register on January 20, 2016 (81 FR following presents the comments UPS requested that paragraph (l)(2) of
3045) (‘‘the NPRM’’). received on the NPRM and the FAA’s the proposed AD be revised to remove
The European Aviation Safety Agency response to each comment. a typographical error that resulted in
(EASA), which is the Technical Agent listing Model A300 F4–622R airplanes
for the Member States of the European Request To Remove Certain Exceptions twice.
Union, has issued EASA AD 2013– in the Proposed Applicability We agree that there was a
0234R2, dated October 7, 2013 (referred United Parcel Service (UPS) requested typographical error, as described by
to after this as the Mandatory that the applicability exceptions in UPS. We have removed the redundant
Continuing Airworthiness Information, paragraphs (c)(3) and (c)(4) of the reference in this AD.
or ‘‘the MCAI’’), to correct an unsafe proposed AD be revised to remove
condition for certain Airbus Model Additional Change to This AD
Airbus Modifications 11133 and 12699
A300 and A300–600 series airplanes. as exceptions. UPS stated that the We added new paragraph (m) to this
The MCAI states: exceptions provided in paragraphs (c)(3) AD to specify clearly the required
Fatigue and ‘‘fail safe’’ tests developed on and (c)(4) of the proposed AD are calculation method for establishing the
a test specimen confirmed that cracks may inconsistent with the effectivity average flight times (AFT) for the
appear and propagate from the bolt holes of specified in the service information compliance times for certain inspections
the base member and the side members of referenced in the NPRM. UPS pointed required by this AD. We also
flap beam No. 2. out that the effectivity of Airbus Service redesignated subsequent paragraphs.
The development of such cracks, if not Bulletin A300–57–6005, Revision 06,
Conclusion
Lhorne on DSK30JT082PROD with RULES
detected, could result in a rupture of flap dated November 14, 2013, applies to
beams No. 2, which could adversely affect
the structural integrity of the airframe.
airplanes with manufacturer serial We reviewed the available data,
To address this potential unsafe condition, number (MSN) 775 and subsequent, including the comments received, and
Airbus issued Service Bulletin (SB) A300– with MSN 775 as the production cut-in determined that air safety and the
57–0116 and SB A300–57–6005 and DGAC for Airbus Modification 11133. UPS public interest require adopting this AD
[Direction Générale de l’Aviation Civile] asserted that this service bulletin’s with the changes described previously
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![71598 Federal Register / Vol. 81, No. 201 / Tuesday, October 18, 2016 / Rules and Regulations
and minor editorial changes. We have for practices, methods, and procedures (c) Applicability
determined that these changes: the Administrator finds necessary for This AD applies to the Airbus airplanes
• Are consistent with the intent that safety in air commerce. This regulation identified in paragraphs (c)(1) through (c)(5)
was proposed in the NPRM for is within the scope of that authority of this AD, certificated in any category.
correcting the unsafe condition; and because it addresses an unsafe condition (1) Airbus Model A300 B2–1A, B2–1C,
• Do not add any additional burden that is likely to exist or develop on B2K–3C, B2–203, B4–2C, B4–103, and B4–
upon the public than was already 203 airplanes, all manufacturer serial
products identified in this rulemaking numbers (MSNs).
proposed in the NPRM. action. (2) Airbus Model A300 B4–601, B4–603,
Related Service Information Under 1 Regulatory Findings B4–620, B4–622, B4–605R, and B4–622R
CFR Part 51 airplanes, all MSNs.
We determined that this AD will not (3) Airbus Model A300 F4–605R, all MSNs,
Airbus has issued Service Bulletins have federalism implications under except those airplanes on which both Airbus
A300–57–0116, Revision 07, dated Executive Order 13132. This AD will Modifications 11133 and 12699 have been
September 19, 2011, including not have a substantial direct effect on embodied.
Appendixes A and B; and A300–57– the States, on the relationship between (4) Airbus Model A300 F4–622R airplanes,
6005, Revision 06, dated November 14, all MSNs, except those airplanes on which
the national government and the States, the modifications identified in paragraph
2013. This service information describes or on the distribution of power and (c)(4)(i) or (c)(4)(ii) of this AD have been
procedures for ultrasonic inspections of responsibilities among the various embodied.
the No. 2 flap beam base and side levels of government. (i) All Airbus Modifications 11133, 12047,
members. These documents are distinct For the reasons discussed above, I 12048, and 12050 have been embodied.
since they apply to different airplane certify that this AD: (ii) Both Airbus Modifications 11133 and
models. This service information is 1. Is not a ‘‘significant regulatory 12699 have been embodied.
reasonably available because the action’’ under Executive Order 12866; (5) Airbus Model A300 C4–605R Variant F
interested parties have access to it airplanes, all MSNs.
2. Is not a ‘‘significant rule’’ under the
through their normal course of business DOT Regulatory Policies and Procedures (d) Subject
or by the means identified in the (44 FR 11034, February 26, 1979); Air Transport Association (ATA) of
ADDRESSES section.
3. Will not affect intrastate aviation in America Code 57, Wings.
Costs of Compliance Alaska; and (e) Reason
We estimate that this AD affects 49 4. Will not have a significant
This AD was prompted by a determination
airplanes of U.S. registry. economic impact, positive or negative, that the compliance times must be reduced.
The actions required by AD 95–21–09 on a substantial number of small entities We are issuing this AD to detect and correct
and retained in this AD, take about 6 under the criteria of the Regulatory cracking of the No. 2 flap beams, which
work-hours per product, at an average Flexibility Act. could result in rupture of the flap beams and
labor rate of $85 per work-hour. reduced structural integrity of the airplane.
List of Subjects in 14 CFR Part 39
Required parts cost about $0 per (f) Compliance
product. Based on these figures, the Air transportation, Aircraft, Aviation
safety, Incorporation by reference, Comply with this AD within the
estimated cost of the actions that were compliance times specified, unless already
required by AD 95–21–09 is $510 per Safety. done.
product, per inspection cycle. Adoption of the Amendment (g) Retained Inspection and Corrective
We also estimate that it takes about 6 Actions for Model A300 Series Airplanes,
work-hours per product to comply with Accordingly, under the authority
delegated to me by the Administrator, With Note 3 of AD 95–21–09 Incorporated
the basic requirements of this AD. The and Additional Terminating Provisions
average labor rate is $85 per work-hour. the FAA amends 14 CFR part 39 as
follows: This paragraph restates the requirements of
Based on these figures, we estimate the paragraph (a) of AD 95–21–09, with Note 3
cost of this AD on U.S. operators to be PART 39—AIRWORTHINESS of AD 95–21–09 incorporated and additional
$24,990 per inspection cycle, or $510 DIRECTIVES terminating provisions. For Model A300
per product, per inspection cycle. series airplanes: Prior to the accumulation of
We have received no definitive data ■ 1. The authority citation for part 39 15,000 total landings, or within the next 120
that would enable us to provide cost days after May 9, 1985 (the effective date of
continues to read as follows: AD 85–07–04, Amendment 39–5027 (50 FR
estimates for the on-condition actions
specified in this AD. Authority: 49 U.S.C. 106(g), 40113, 44701. 13013, April 2, 1985) (‘‘AD 85–07–04’’)),
whichever occurs later, inspect for cracking
Authority for This Rulemaking § 39.13 [Amended] of the base steel member and light alloy side
■ 2. The FAA amends § 39.13 by members of the No. 2 flap beams, left hand
Title 49 of the United States Code and right hand, in accordance with the
specifies the FAA’s authority to issue removing Airworthiness Directive (AD)
Accomplishment Instructions of Airbus
rules on aviation safety. Subtitle I, 95–21–09, Amendment 39–9395 (60 FR Service Bulletin A300–57–116, Revision 6,
section 106, describes the authority of 53847, October 18, 1995), and adding dated July 16, 1993. Accomplishing the
the FAA Administrator. ‘‘Subtitle VII: the following new AD: requirements of paragraph (h) or (l) of this
Aviation Programs,’’ describes in more 2016–20–08 Airbus: Amendment 39–18674; AD terminates the requirements of this
detail the scope of the Agency’s Docket No. FAA–2015–8470; Directorate paragraph. Measurement of crack length is
authority. Identifier 2013–NM–199–AD. performed by measurement of the probe
We are issuing this rulemaking under displacement (perpendicular to symmetry
(a) Effective Date
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plane of beam) between defect indication
the authority described in ‘‘Subtitle VII,
This AD is effective November 22, 2016. appearance and its complete disappearance.
Part A, Subpart III, Section 44701: The bolt hole indication should not be
General requirements.’’ Under that (b) Affected ADs interpreted as an indication of a defect. These
section, Congress charges the FAA with This AD replaces AD 95–21–09, two indications appear very close together
promoting safe flight of civil aircraft in Amendment 39–9395 (60 FR 53847, October because the defects originate from the bolt
air commerce by prescribing regulations 18, 1995) (‘‘AD 95–21–09’’). holes.
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![71602 Federal Register / Vol. 81, No. 201 / Tuesday, October 18, 2016 / Rules and Regulations
(r) Material Incorporated by Reference Issued in Renton, Washington, on www.regulations.gov by searching for
(1) The Director of the Federal Register September 19, 2016. and locating Docket No. FAA–2015–
approved the incorporation by reference Dionne Palermo, 8132.
(IBR) of the service information listed in this Acting Manager, Transport Airplane
paragraph under 5 U.S.C. 552(a) and 1 CFR Directorate, Aircraft Certification Service.
Examining the AD Docket
part 51. [FR Doc. 2016–23261 Filed 10–17–16; 8:45 am] You may examine the AD docket on
(2) You must use this service information BILLING CODE 4910–13–P
the Internet at http://
as applicable to do the actions required by www.regulations.gov by searching for
this AD, unless this AD specifies otherwise. and locating Docket No. FAA–2015–
(3) The following service information was 8132; or in person at the Docket
DEPARTMENT OF TRANSPORTATION
approved for IBR on November 22, 2016. Management Facility between 9 a.m.
(i) Airbus Service Bulletin A300–57–0116, and 5 p.m., Monday through Friday,
Federal Aviation Administration
Revision 07, dated September 19, 2011,
except Federal holidays. The AD docket
including Appendixes A and B. Only the first
page of Appendixes A and B of this 14 CFR Part 39 contains this AD, the regulatory
document are identified as appendixes. evaluation, any comments received, and
[Docket No. FAA–2015–8132; Directorate
(ii) Airbus Service Bulletin A300–57–6005, Identifier 2015–NM–127–AD; Amendment other information. The street address for
Revision 06, dated November 14, 2013. 39–18663; AD 2016–19–14] the Docket Office (telephone 800–647–
(4) The following service information was 5527) is Docket Management Facility,
approved for IBR on November 17, 1995 (60 RIN 2120–AA64 U.S. Department of Transportation,
FR 53847, October 18, 1995). Docket Operations, M–30, West
(i) Airbus Service Bulletin A300–57–116, Airworthiness Directives; Airbus Building Ground Floor, Room W12–140,
Revision 6, dated July 16, 1993, which Airplanes 1200 New Jersey Avenue SE.,
contains the following effective pages: Pages Washington, DC 20590.
AGENCY: Federal Aviation
1 through 11 of this document are identified
Administration (FAA), Department of FOR FURTHER INFORMATION CONTACT:
as Revision 6, dated July 16, 1993.
(ii) Airbus Service Bulletin A300–57–128, Transportation (DOT). Sanjay Ralhan, Aerospace Engineer,
Revision 3, dated January 26, 1990, which ACTION: Final rule. International Branch, ANM–116,
contains the following effective pages: Page Transport Airplane Directorate, FAA,
1 is identified as Revision 3, dated January SUMMARY: We are adopting a new 1601 Lind Avenue SW., Renton, WA
26, 1990; pages 2 through 5 are identified as airworthiness directive (AD) for certain 98057–3356; telephone 425–227–1405;
Revision 1, dated February 7, 1986; and Airbus Model A318 and A319 series fax 425–227–1149.
pages 6 through 14 are identified as the airplanes; Model A320–211, –212, –214, SUPPLEMENTARY INFORMATION:
original issue, dated August 27, 1983. –231, –232, and –233 airplanes; and
(iii) Airbus Service Bulletin A300–57–141, Model A321 series airplanes. This AD Discussion
Revision 7, dated July 16, 1993, which was prompted by a report of cracks We issued a notice of proposed
contains the following effective pages: Pages found during maintenance inspections rulemaking (NPRM) to amend 14 CFR
1 through 24 of this document are identified part 39 by adding an AD that would
on certain lugs of the 10VU rack side
as Revision 7, dated July 16, 1993. apply to certain Airbus Model A318,
(iv) Airbus Service Bulletin A300–57–
fittings in the cockpit. This AD requires
repetitive inspections for cracking of the A319, A320, and A321 series airplanes.
6005, Revision 2, dated December 16, 1993,
which contains the following effective pages: lugs on the 10VU rack side fittings, and The NPRM published in the Federal
Pages 1 through 4 are identified as Revision repair of any cracking. We are issuing Register on December 31, 2015 (80 FR
2, dated December 16, 1993; pages 5 through this AD to prevent reading difficulties of 81792) (‘‘the NPRM’’). The NPRM was
7 and 9 are identified as Revision 1, dated flight-critical information displayed to prompted by a report of cracks found
February 26, 1993; and page 8 is identified the flightcrew during a critical phase of during maintenance inspections on
as the original issue, dated August 13, 1986. flight, such as an approach or takeoff, certain lugs of the 10VU rack side
(v) Airbus Service Bulletin A300–57–6006, which could result in loss of airplane fittings in the cockpit. The NPRM
Revision 4, dated July 25, 1994, which control at an altitude insufficient for proposed to require repetitive
contains the following effective pages: Pages recovery. inspections for cracking of the lugs on
1, 2, 5, and 7 are identified as Revision 4, the 10VU rack side fittings, and repair
dated July 25, 1994; and pages 3, 4, 6, and DATES: This AD is effective November
of any cracking. We are issuing this AD
8 through 20 are identified as Revision 3, 22, 2016. to prevent reading difficulties of flight-
dated December 16, 1993. The Director of the Federal Register critical information displayed to the
(5) For service information identified in approved the incorporation by reference flightcrew during a critical phase of
this AD, contact Airbus SAS, Airworthiness of a certain publication listed in this AD flight, such as an approach or takeoff,
Office—EAW, 1 Rond Point Maurice as of November 22, 2016.
Bellonte, 31707 Blagnac Cedex, France; which could result in loss of airplane
telephone +33 5 61 93 36 96; fax +33 5 61 ADDRESSES: For service information control at an altitude insufficient for
93 44 51; email account.airworth-eas@ identified in this final rule, contact recovery.
airbus.com; Internet http://www.airbus.com. Airbus, Airworthiness Office—EIAS, 1 The European Aviation Safety Agency
(6) You may view this service information Rond Point Maurice Bellonte, 31707 (EASA), which is the Technical Agent
at the FAA, Transport Airplane Directorate, Blagnac Cedex, France; telephone +33 5 for the Member States of the European
1601 Lind Avenue SW., Renton, WA. For 61 93 36 96; fax +33 5 61 93 44 51; email Union, has issued EASA Airworthiness
information on the availability of this account.airworth-eas@airbus.com; Directive 2015–0170, dated August 18,
material at the FAA, call 425–227–1221. Internet http://www.airbus.com. You 2015 (referred to after this as the
(7) You may view this service information may view this referenced service Mandatory Continuing Airworthiness
Lhorne on DSK30JT082PROD with RULES
that is incorporated by reference at the
National Archives and Records
information at the FAA, Transport Information, or ‘‘the MCAI’’), to correct
Administration (NARA). For information on Airplane Directorate, 1601 Lind Avenue an unsafe condition for certain Airbus
the availability of this material at NARA, call SW., Renton, WA. For information on Model A318 and A319 series airplanes;
202–741–6030, or go to: http:// the availability of this material at the Model A320–211, –212, –214, –231,
www.archives.gov/federal-register/cfr/ibr- FAA, call 425–227–1221. It is also –232, and –233 airplanes; and Model
locations.html. available on the Internet at http:// A321 series airplanes. The MCAI states:
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Document Created: 2016-10-17 23:52:14
Document Modified: 2016-10-17 23:52:14
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective November 22, 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 71596 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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