81 FR 43472 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 128 (July 5, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 128 (July 5, 2016)
| Page Range | 43472-43475 | |
| FR Document | 2016-15356 |
[Federal Register Volume 81, Number 128 (Tuesday, July 5, 2016)] [Rules and Regulations] [Pages 43472-43475] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-15356] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-8134; Directorate Identifier 2014-NM-256-AD; Amendment 39-18572; AD 2016-13-08] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; and 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). This AD was prompted by a report of cracking of the lower tension bolt area at the rib one junction (both sides) of the lower wing. This AD requires repetitive inspections for cracking of the fasteners and of the fitting around the fastener holes at the frame (FR) 40 lower wing location, and corrective actions if necessary. We are issuing this AD to detect and correct crack initiation of the fittings of the FR40 lower wing locations, which could result in reduced structural integrity of the airplane. DATES: This AD becomes effective August 9, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 9, 2016. ADDRESSES: For Airbus 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 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-2015-8134. 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- 8134; 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 street address for the Docket Operations office (telephone 800-647-5527) is in the ADDRESSES section. 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: [[Page 43473]] Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A300 series airplanes; and 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). The NPRM published in the Federal Register on December 31, 2015 (80 FR 81786) (``the NPRM''). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0272, dated December 12, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A300 series airplanes; and 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). The MCAI states: Following the A300-600 Extended Service Goal (ESG2) exercise, specific inspections for cracks were performed in fittings of frame (FR) 40, in areas not covered by any existing task. Findings were identified on an A300-600 aeroplane withdrawn from service in the lower tension bolt area at rib one junction (both sides). This condition, if not detected and corrected, could lead to crack initiation, affecting the structural integrity of the aeroplane. To address this potential unsafe condition, an inspection programme was developed for the fitting around the fastener holes located at FR40 lower wing junction, left-hand (LH) and right-hand (RH) sides. For the reasons described above, this [EASA] AD requires repetitive High Frequency Eddy Current (HFEC) inspections and rototest inspections of the fitting around the fastener holes located at FR40 lower wing junction and, depending on findings, accomplishment of a repair. The corrective actions include a repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA Design Organization Approval (DOA). 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- 8134. 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 Clarify Corrective Actions FedEx asked that the corrective actions identified in paragraph (i) of the proposed AD be clarified. FedEx stated that paragraph (h)(1) of the proposed AD specifies ``If one or more of the hole diameters is outside the tolerance of the nominal diameter, and outside the tolerance of the first and second oversize: Do the applicable corrective actions required by paragraph (i) of this AD.'' FedEx added that paragraph (i) of the proposed AD specifies ``If, during any inspection required by this AD, any crack is found, or one or more of the hole diameters are outside the tolerance of the nominal diameter: Repair before further flight 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).'' FedEx noted that paragraph (i) should specify ``one or more of the hole diameters are outside the tolerance of the nominal diameter and outside the tolerance of the first and second oversize'' to match the language in paragraph (h)(1) of the proposed. We agree. We have confirmed that the language in paragraph (i) of this AD should match the language in paragraph (h)(1) of this AD. We have changed paragraph (i) of this AD accordingly. Request To Revise Compliance Time United Parcel Service (UPS) asked that we revise the compliance time for the rototest inspections specified by paragraph (h) of the proposed AD to a threshold based on total service time, rather than calendar time alone. UPS stated that, based on reported findings to date, the crack growth rate is so slow it will not affect the immediate airworthiness of the airplane. UPS suggested that we add a threshold of 11,900 total flight cycles. We do not agree with the commenter's request. The commenter provided no data to substantiate the proposed compliance time based on flight cycles. In developing an appropriate compliance time for this AD, we considered not only the urgency associated with the subject unsafe condition, but also the manufacturer's recommendations, EASA's recommendations, and the practical aspect of accomplishing the required inspections within a period of time that corresponds to the normal scheduled maintenance for most affected operators. After considering all the available information, we have determined that the compliance time, as proposed, represents an appropriate interval of time in which the required actions can be performed in a timely manner within the affected fleet, while still maintaining an adequate level of safety. However, affected operators may request an alternative method of compliance (AMOC) to request a change to the compliance time under the provisions of paragraph (j) of this AD by submitting data and analysis substantiating that the change would provide an acceptable level of safety. We have not changed this AD regarding this issue. Request To Remove High Frequency Eddy Current (HFEC) Inspections UPS asked that the HFEC inspections specified by paragraph (g) of the proposed AD be removed. UPS stated that the HFEC inspection requirement does not enhance airplane safety because only substantial damage can be detected by this method, due to a restricted inspection area. UPS also stated that the smallest crack detectable by an HFEC inspection method is calculated to be 7.5 mm in length, not taking into account the inspection surface radius and the limited access to the inspection area. UPS added that fastener location and potential obstacles affect consistent probe movement, which increases the chance for inconsistent inspection readings. We do not agree with the commenter's request. The HFEC inspection required by paragraph (g) of this AD is a necessary interim measure intended to find cracking before the required compliance time for the rototest inspection in paragraph (h) of this AD. As the commenter acknowledged, a 7.5-mm crack may be detected during an HFEC inspection within 1,000 flight hours. That same 7.5-mm crack, undetected for 3 years until the rototest inspection is done, could grow and result in reduced structural integrity of the airplane; therefore, the repetitive HFEC inspections must be retained in this AD. If no cracking is found, the HFEC inspection can be repeated, or terminated when the rototest inspection is accomplished. However, affected operators may request approval of an AMOC to do the rototest inspections only, under the provisions of paragraph (j) of this AD by submitting data and analysis, and a compliance schedule, substantiating that the change would provide an acceptable level of safety. We have not changed this AD regarding this issue. [[Page 43474]] Request To Correct Typographical Errors in Service Information FedEx asked that the typographical errors for the structural repair manual (SRM) references in Airbus Service Bulletin A300-57-6115, dated April 4, 2014, be corrected so FedEx can use them to comply with the NPRM requirements. FedEx stated that Airbus was informed of and acknowledged these typographical errors, but currently no changes have been made to the service information. FedEx noted that the service information listed SRM 51-40-13 for the application of special coatings, but the correct reference is SRM 51-23-20. FedEx also noted that the service information listed SRM 51-40-12 for the application of paint coatings, but the correct reference is SRM 51-23-10. We agree with the commenter's concerns. We have changed paragraph (g) of this AD to clarify the correct SRM references to be used. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor 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 We reviewed the following service information. Airbus Service Bulletin A300-57-0257, excluding Appendix 01 and including Appendix 02, dated April 4, 2014. Airbus Service Bulletin A300-57-6115, dated April 4, 2014. The service information describes procedures for repetitive inspections for cracking of the fasteners and of the fitting around the fastener holes at the FR40 lower wing location. 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 166 airplanes of U.S. registry. We also estimate that it takes about 12 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 $169,320, or $1,020 per product. We have received no definitive data that would enable us to provide a cost estimate 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 adding the following new airworthiness directive (AD): 2016-13-08 Airbus: Amendment 39-18572. Docket No. FAA-2015-8134; Directorate Identifier 2014-NM-256-AD. (a) Effective Date This AD becomes effective August 9, 2016. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus airplanes identified in paragraphs (c)(1) and (c)(2) 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. (2) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a report of cracking of the lower tension bolt area at rib one junction (both sides) of the lower wing. We are issuing this AD to detect and correct crack initiation of the fittings of the frame (FR) 40 lower wing locations, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive High Frequency Eddy Current (HFEC) Inspections Within 1,000 flight hours after the effective date of this AD: Do an HFEC inspection for cracking of fasteners 1 through 3 at the left-hand and right-hand sides of the FR40 lower junction, and of the fitting around the fastener holes, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0257, excluding Appendix 01 and including Appendix 02, dated April 4, 2014 (for Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4- 203 airplanes); or Airbus Service Bulletin A300-57-6115, dated April 4, 2014 (for Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4- 622R, F4-605R, F4-622R, and C4-605R Variant F airplanes). If no cracking is found, repeat the HFEC inspection at intervals not to exceed 1,000 flight hours until a rototest inspection required by paragraph (h)(2) of this AD has been done. Where Airbus Service Bulletin [[Page 43475]] A300-57-6115, dated April 4, 2014, refers to Structural Repair Manual (SRM) 51-40-13 for applying special protection, the correct reference is SRM 51-23-20; and to SRM 51-40-12 for applying paint coatings, the correct reference is SRM 51-23-10. (h) Repetitive Rototest Inspections Within 36 months after the effective date of this AD: Remove the fasteners and measure the diameter of the fastener holes; and, before further flight, do the applicable actions required by paragraph (h)(1) or (h)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0257, excluding Appendix 01 and including Appendix 02, dated April 4, 2014 (for Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4- 203 airplanes); or Airbus Service Bulletin A300-57-6115, dated April 4, 2014 (for Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4- 622R, F4-605R, F4-622R, and C4-605R Variant F airplanes). (1) If one or more of the hole diameters is outside the tolerance of the nominal diameter, and outside the tolerance of the first and second oversize: Do the applicable corrective actions required by paragraph (i) of this AD. (2) If all of the hole diameters are within the tolerance of the nominal diameter or the first or second oversize: Do detailed and rototest inspections for cracking of the fastener holes at the left- hand and right-hand sides of the FR40 lower junction, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0257, excluding Appendix 01 and including Appendix 02, dated April 4, 2014 (for Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes); or Airbus Service Bulletin A300-57- 6115, dated April 4, 2014 (for Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes). If no cracking is found, before further flight, install new fasteners of the same diameter in special clearance fit for fasteners 1 through 3 of the FR40 lower junction, in accordance with the Accomplishment Instructions of Airbus Service Bulletins A300-57- 0257, excluding Appendix 01 and including Appendix 02, dated April 4, 2014; or Airbus Service Bulletin A300-57-6115, dated April 4, 2014. Repeat the rototest inspection thereafter at intervals not to exceed 7,000 flight cycles. Accomplishment of a rototest inspection required by this paragraph terminates the repetitive HFEC inspections required by paragraph (g) of this AD. (i) Corrective Actions If, during any inspection required by this AD, any crack is found, or one or more of the hole diameters is outside the tolerance of the nominal diameter, and outside the tolerance of the first and second oversize: Repair before further flight in accordance with 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). (j) 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]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (i) 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. (k) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0272, dated December 12, 2014, 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-2015-8134. (l) 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. (i) Airbus Service Bulletin A300-57-0257, excluding Appendix 01 and including Appendix 02, dated April 4, 2014. (ii) Airbus Service Bulletin A300-57-6115, dated April 4, 2014. (3) For Airbus 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. (4) 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. (5) 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 June 21, 2016. Dorr M. Anderson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-15356 Filed 7-1-16; 8:45 am] BILLING CODE 4910-13-P
![43472 Federal Register / Vol. 81, No. 128 / Tuesday, July 5, 2016 / Rules and Regulations
additional analysis and tests may be 6. Femur Criteria Airbus Model A300 series airplanes;
required to demonstrate that the injury Axial rotation of the upper leg (about and Model A300 B4–600, B4–600R, and
criteria are met for the area that an the Z-axis of the femur, per SAE J211/ F4–600R series airplanes, and Model
occupant could contact. For example, if 1) must be limited to 35 degrees in the A300 C4–605R Variant F airplanes
different yaw angles could result in strike direction from the normal seating (collectively called Model A300–600
different airbag device performance, position. Evaluation during rebound series airplanes). This AD was prompted
then additional analysis or separate tests need not be considered. by a report of cracking of the lower
may be necessary to evaluate tension bolt area at the rib one junction
performance. 7. ATD and Test Conditions (both sides) of the lower wing. This AD
Longitudinal tests conducted to requires repetitive inspections for
3. Neck Injury Criteria
measure the injury criteria above must cracking of the fasteners and of the
a. The seating system must protect the be performed with the FAA Hybrid III fitting around the fastener holes at the
occupant from experiencing serious ATD, as described in SAE 1999–01– frame (FR) 40 lower wing location, and
neck injury. The assessment of neck 1609, ‘‘A Lumbar Spine Modification to corrective actions if necessary. We are
injury must be conducted with the the Hybrid III ATD For Aircraft Seat issuing this AD to detect and correct
airbag device activated, unless there is Tests.’’ The tests must be conducted crack initiation of the fittings of the
reason to also consider that the neck- with an undeformed floor, at the most- FR40 lower wing locations, which could
injury potential would be higher for critical yaw cases for injury, and with result in reduced structural integrity of
impacts below the airbag-device all lateral structural supports (e.g. the airplane.
deployment threshold. armrests or walls) installed. DATES: This AD becomes effective
b. The Nij, calculated in accordance
Inflatable Lapbelt Special Conditions August 9, 2016.
with 49 CFR 571.208, must be below
The Director of the Federal Register
1.0, where Nij =Fz/Fzc + My/Myc, and Nij The inflatable lapbelts must meet
approved the incorporation by reference
critical values are: special conditions no. 25–187A–SC,
‘‘Boeing Model 777 Series Airplanes; of certain publications listed in this AD
i. Fzc = 1530 lb for tension as of August 9, 2016.
ii. Fzc = 1385 lb for compression Seats with Inflatable Lapbelts.’’
iii. Myc = 229 lb-ft in flexion 1. Because this type of protection ADDRESSES: For Airbus service
iv. Myc = 100 lb-ft in extension system may or may not activate during information identified in this final rule,
c. In addition, peak upper neck Fz various crash conditions, the applicant contact Airbus SAS, Airworthiness
must be below 937 lb in tension and 899 must demonstrate that the injury criteria Office—EAW, 1 Rond Point Maurice
lb in compression. listed in these special conditions are not Bellonte, 31707 Blagnac Cedex, France;
d. Rotation of the head about its exceeded in an event which is slightly telephone +33 5 61 93 36 96; fax +33 5
vertical axis relative to the torso is below the activation level of the airbag 61 93 44 51; email account.airworth-
limited to 105 degrees in either system. eas@airbus.com; Internet http://
direction from forward-facing. 2. Additionally, as indicated in www.airbus.com. You may view this
e. The neck must not impact any special conditions no. 25–187A–SC, referenced service information at the
surface that would produce inflatable lapbelts must be shown to not FAA, Transport Airplane Directorate,
concentrated loading on the neck. affect emergency-egress capabilities in 1601 Lind Avenue SW., Renton, WA.
the main aisle, cross-aisle, and For information on the availability of
4. Spine and Torso Injury Criteria passageway. this material at the FAA, call 425–227–
a. The lumbar spine tension (Fz) Issued in Renton, Washington, on June 17, 1221. It is also available on the Internet
cannot exceed 1200 lb. 2016. at http://www.regulations.gov by
b. Significant concentrated loading on Michael Kaszycki, searching for and locating Docket No.
the occupant’s spine, in the area Assistant Manager, Transport Airplane FAA–2015–8134.
between the pelvis and shoulders Directorate, Aircraft Certification Service.
during impact, including rebound, is Examining the AD Docket
[FR Doc. 2016–15784 Filed 7–1–16; 8:45 am]
not acceptable. During this type of You may examine the AD docket on
BILLING CODE 4910–13–P
contact, the interval for any rearward the Internet at http://
(X-axis direction) acceleration www.regulations.gov by searching for
exceeding 20g must be less than 3 DEPARTMENT OF TRANSPORTATION and locating Docket No. FAA–2015–
milliseconds as measured by the 8134; or in person at the Docket
thoracic instrumentation specified in 49 Federal Aviation Administration Management Facility between 9 a.m.
CFR part 572, subpart E, filtered in and 5 p.m., Monday through Friday,
accordance with SAE recommended 14 CFR Part 39 except Federal holidays. The AD docket
practice J211/1, ‘‘Instrumentation for contains this AD, the regulatory
[Docket No. FAA–2015–8134; Directorate
Impact Test—Part 1—Electronic Identifier 2014–NM–256–AD; Amendment evaluation, any comments received, and
Instrumentation.’’ 39–18572; AD 2016–13–08] other information. The street address for
c. The occupant must not interact the Docket Operations office (telephone
with the armrest or other seat RIN 2120–AA64 800–647–5527) is in the ADDRESSES
components in any manner significantly section.
different than would be expected for a Airworthiness Directives; Airbus
forward-facing seat installation. Airplanes FOR FURTHER INFORMATION CONTACT: Dan
sradovich on DSK3GDR082PROD with RULES
Rodina, Aerospace Engineer,
5. Pelvis Criteria AGENCY: Federal Aviation
International Branch, ANM–116,
Administration (FAA), Department of
Any part of the load-bearing portion Transport Airplane Directorate, FAA,
Transportation (DOT).
of the bottom of the ATD pelvis must 1601 Lind Avenue SW., Renton, WA
ACTION: Final rule.
not translate beyond the edges of the 98057–3356; telephone 425–227–2125;
seat bottom seat-cushion supporting SUMMARY: We are adopting a new fax 425–227–1149.
structure. airworthiness directive (AD) for all SUPPLEMENTARY INFORMATION:
VerDate Sep<11>2014 16:06 Jul 01, 2016 Jkt 238001 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 E:\FR\FM\05JYR1.SGM 05JYR1](https://thefederalregister.org/doc/81_FR_43600/page/1.svg)
![Federal Register / Vol. 81, No. 128 / Tuesday, July 5, 2016 / Rules and Regulations 43473
Discussion received on the NPRM and the FAA’s the compliance time, as proposed,
response to each comment. represents an appropriate interval of
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR Request To Clarify Corrective Actions time in which the required actions can
part 39 by adding an AD that would be performed in a timely manner within
FedEx asked that the corrective the affected fleet, while still maintaining
apply to all Airbus Model A300 series actions identified in paragraph (i) of the
airplanes; and Model A300 B4–600, B4– an adequate level of safety. However,
proposed AD be clarified. FedEx stated
600R, and F4–600R series airplanes, and affected operators may request an
that paragraph (h)(1) of the proposed AD
Model A300 C4–605R Variant F alternative method of compliance
specifies ‘‘If one or more of the hole
airplanes (collectively called Model diameters is outside the tolerance of the (AMOC) to request a change to the
A300–600 series airplanes). The NPRM nominal diameter, and outside the compliance time under the provisions of
published in the Federal Register on tolerance of the first and second paragraph (j) of this AD by submitting
December 31, 2015 (80 FR 81786) (‘‘the oversize: Do the applicable corrective data and analysis substantiating that the
NPRM’’). actions required by paragraph (i) of this change would provide an acceptable
The European Aviation Safety Agency AD.’’ FedEx added that paragraph (i) of level of safety. We have not changed
(EASA), which is the Technical Agent the proposed AD specifies ‘‘If, during this AD regarding this issue.
for the Member States of the European any inspection required by this AD, any
Request To Remove High Frequency
Union, has issued EASA Airworthiness crack is found, or one or more of the
Eddy Current (HFEC) Inspections
Directive 2014–0272, dated December hole diameters are outside the tolerance
12, 2014 (referred to after this as the of the nominal diameter: Repair before UPS asked that the HFEC inspections
Mandatory Continuing Airworthiness further flight using a method approved specified by paragraph (g) of the
Information, or ‘‘the MCAI’’), to correct by the Manager, International Branch, proposed AD be removed. UPS stated
an unsafe condition for all Airbus ANM–116, Transport Airplane that the HFEC inspection requirement
Model A300 series airplanes; and Model Directorate, FAA; or the European
does not enhance airplane safety
A300 B4–600, B4–600R, and F4–600R Aviation Safety Agency (EASA); or
because only substantial damage can be
series airplanes, and Model A300 C4– Airbus’s EASA Design Organization
Approval (DOA).’’ FedEx noted that detected by this method, due to a
605R Variant F airplanes (collectively
paragraph (i) should specify ‘‘one or restricted inspection area. UPS also
called Model A300–600 series
airplanes). The MCAI states: more of the hole diameters are outside stated that the smallest crack detectable
the tolerance of the nominal diameter by an HFEC inspection method is
Following the A300–600 Extended Service calculated to be 7.5 mm in length, not
Goal (ESG2) exercise, specific inspections for and outside the tolerance of the first and
cracks were performed in fittings of frame second oversize’’ to match the language taking into account the inspection
(FR) 40, in areas not covered by any existing in paragraph (h)(1) of the proposed. surface radius and the limited access to
task. We agree. We have confirmed that the the inspection area. UPS added that
Findings were identified on an A300–600 language in paragraph (i) of this AD fastener location and potential obstacles
aeroplane withdrawn from service in the should match the language in paragraph affect consistent probe movement,
lower tension bolt area at rib one junction (h)(1) of this AD. We have changed which increases the chance for
(both sides). paragraph (i) of this AD accordingly. inconsistent inspection readings.
This condition, if not detected and
corrected, could lead to crack initiation, Request To Revise Compliance Time We do not agree with the commenter’s
affecting the structural integrity of the request. The HFEC inspection required
United Parcel Service (UPS) asked
aeroplane. by paragraph (g) of this AD is a
To address this potential unsafe condition, that we revise the compliance time for
the rototest inspections specified by necessary interim measure intended to
an inspection programme was developed for
the fitting around the fastener holes located paragraph (h) of the proposed AD to a find cracking before the required
at FR40 lower wing junction, left-hand (LH) threshold based on total service time, compliance time for the rototest
and right-hand (RH) sides. rather than calendar time alone. UPS inspection in paragraph (h) of this AD.
For the reasons described above, this stated that, based on reported findings As the commenter acknowledged, a 7.5-
[EASA] AD requires repetitive High to date, the crack growth rate is so slow mm crack may be detected during an
Frequency Eddy Current (HFEC) inspections it will not affect the immediate HFEC inspection within 1,000 flight
and rototest inspections of the fitting around
airworthiness of the airplane. UPS hours. That same 7.5-mm crack,
the fastener holes located at FR40 lower wing
junction and, depending on findings, suggested that we add a threshold of undetected for 3 years until the rototest
accomplishment of a repair. 11,900 total flight cycles. inspection is done, could grow and
We do not agree with the commenter’s result in reduced structural integrity of
The corrective actions include a request. The commenter provided no the airplane; therefore, the repetitive
repair using a method approved by the data to substantiate the proposed HFEC inspections must be retained in
Manager, International Branch, ANM– compliance time based on flight cycles. this AD. If no cracking is found, the
116, Transport Airplane Directorate, In developing an appropriate HFEC inspection can be repeated, or
FAA; or the EASA; or Airbus’s EASA compliance time for this AD, we
Design Organization Approval (DOA). terminated when the rototest inspection
considered not only the urgency
is accomplished. However, affected
You may examine the MCAI in the associated with the subject unsafe
operators may request approval of an
AD docket on the Internet at http:// condition, but also the manufacturer’s
www.regulations.gov by searching for recommendations, EASA’s AMOC to do the rototest inspections
only, under the provisions of paragraph
sradovich on DSK3GDR082PROD with RULES
and locating Docket No. FAA–2015– recommendations, and the practical
8134. aspect of accomplishing the required (j) of this AD by submitting data and
inspections within a period of time that analysis, and a compliance schedule,
Comments substantiating that the change would
corresponds to the normal scheduled
We gave the public the opportunity to maintenance for most affected operators. provide an acceptable level of safety.
participate in developing this AD. The After considering all the available We have not changed this AD regarding
following presents the comments information, we have determined that this issue.
VerDate Sep<11>2014 16:06 Jul 01, 2016 Jkt 238001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\05JYR1.SGM 05JYR1](https://thefederalregister.org/doc/81_FR_43600/page/2.svg)
![43474 Federal Register / Vol. 81, No. 128 / Tuesday, July 5, 2016 / Rules and Regulations
Request To Correct Typographical Based on these figures, we estimate the PART 39—AIRWORTHINESS
Errors in Service Information cost of this AD on U.S. operators to be DIRECTIVES
FedEx asked that the typographical $169,320, or $1,020 per product.
We have received no definitive data ■ 1. The authority citation for part 39
errors for the structural repair manual continues to read as follows:
(SRM) references in Airbus Service that would enable us to provide a cost
Bulletin A300–57–6115, dated April 4, estimate for the on-condition actions Authority: 49 U.S.C. 106(g), 40113, 44701.
2014, be corrected so FedEx can use specified in this AD.
§ 39.13 [Amended]
them to comply with the NPRM Authority for This Rulemaking
requirements. FedEx stated that Airbus ■ 2. The FAA amends § 39.13 by adding
was informed of and acknowledged Title 49 of the United States Code the following new airworthiness
these typographical errors, but currently specifies the FAA’s authority to issue directive (AD):
no changes have been made to the rules on aviation safety. Subtitle I, 2016–13–08 Airbus: Amendment 39–18572.
service information. FedEx noted that section 106, describes the authority of Docket No. FAA–2015–8134; Directorate
the service information listed SRM 51– the FAA Administrator. ‘‘Subtitle VII: Identifier 2014–NM–256–AD.
40–13 for the application of special Aviation Programs,’’ describes in more
(a) Effective Date
coatings, but the correct reference is detail the scope of the Agency’s
authority. This AD becomes effective August 9, 2016.
SRM 51–23–20. FedEx also noted that
the service information listed SRM 51– We are issuing this rulemaking under (b) Affected ADs
40–12 for the application of paint the authority described in ‘‘Subtitle VII, None.
coatings, but the correct reference is Part A, Subpart III, Section 44701:
(c) Applicability
SRM 51–23–10. General requirements.’’ Under that
section, Congress charges the FAA with This AD applies to all Airbus airplanes
We agree with the commenter’s identified in paragraphs (c)(1) and (c)(2) of
concerns. We have changed paragraph promoting safe flight of civil aircraft in
this AD, certificated in any category.
(g) of this AD to clarify the correct SRM air commerce by prescribing regulations (1) Airbus Model A300 B2–1A, B2–1C,
references to be used. for practices, methods, and procedures B2K–3C, B2–203, B4–2C, B4–103, and B4–
the Administrator finds necessary for 203 airplanes.
Conclusion safety in air commerce. This regulation (2) Airbus Model A300 B4–601, B4–603,
We reviewed the available data and is within the scope of that authority B4–620, B4–622, B4–605R, B4–622R, F4–
determined that air safety and the because it addresses an unsafe condition 605R, F4–622R, and C4–605R Variant F
public interest require adopting this AD that is likely to exist or develop on airplanes.
with the changes described previously products identified in this rulemaking (d) Subject
and minor editorial changes. We have action. Air Transport Association (ATA) of
determined that these minor changes: Regulatory Findings America Code 57, Wings.
• Are consistent with the intent that
We determined that this AD will not (e) Reason
was proposed in the NPRM for
correcting the unsafe condition; and have federalism implications under This AD was prompted by a report of
• Do not add any additional burden Executive Order 13132. This AD will cracking of the lower tension bolt area at rib
not have a substantial direct effect on one junction (both sides) of the lower wing.
upon the public than was already We are issuing this AD to detect and correct
proposed in the NPRM. the States, on the relationship between
crack initiation of the fittings of the frame
the national government and the States,
Related Service Information Under 1 (FR) 40 lower wing locations, which could
or on the distribution of power and result in reduced structural integrity of the
CFR Part 51 responsibilities among the various airplane.
We reviewed the following service levels of government.
(f) Compliance
information. For the reasons discussed above, I
• Airbus Service Bulletin A300–57– certify that this AD: Comply with this AD within the
0257, excluding Appendix 01 and 1. Is not a ‘‘significant regulatory compliance times specified, unless already
done.
including Appendix 02, dated April 4, action’’ under Executive Order 12866;
2014. 2. Is not a ‘‘significant rule’’ under the (g) Repetitive High Frequency Eddy Current
• Airbus Service Bulletin A300–57– DOT Regulatory Policies and Procedures (HFEC) Inspections
6115, dated April 4, 2014. (44 FR 11034, February 26, 1979); Within 1,000 flight hours after the effective
The service information describes 3. Will not affect intrastate aviation in date of this AD: Do an HFEC inspection for
procedures for repetitive inspections for Alaska; and cracking of fasteners 1 through 3 at the left-
hand and right-hand sides of the FR40 lower
cracking of the fasteners and of the 4. Will not have a significant
junction, and of the fitting around the
fitting around the fastener holes at the economic impact, positive or negative, fastener holes, in accordance with the
FR40 lower wing location. This service on a substantial number of small entities Accomplishment Instructions of Airbus
information is reasonably available under the criteria of the Regulatory Service Bulletin A300–57–0257, excluding
because the interested parties have Flexibility Act. Appendix 01 and including Appendix 02,
access to it through their normal course dated April 4, 2014 (for Model A300 B2–1A,
List of Subjects in 14 CFR Part 39 B2–1C, B2K–3C, B2–203, B4–2C, B4–103,
of business or by the means identified
in the ADDRESSES section. Air transportation, Aircraft, Aviation and B4–203 airplanes); or Airbus Service
safety, Incorporation by reference, Bulletin A300–57–6115, dated April 4, 2014
Costs of Compliance
sradovich on DSK3GDR082PROD with RULES
Safety. (for Model A300 B4–601, B4–603, B4–620,
B4–622, B4–605R, B4–622R, F4–605R, F4–
We estimate that this AD affects 166
Adoption of the Amendment 622R, and C4–605R Variant F airplanes). If
airplanes of U.S. registry. no cracking is found, repeat the HFEC
We also estimate that it takes about 12 Accordingly, under the authority inspection at intervals not to exceed 1,000
work-hours per product to comply with delegated to me by the Administrator, flight hours until a rototest inspection
the basic requirements of this AD. The the FAA amends 14 CFR part 39 as required by paragraph (h)(2) of this AD has
average labor rate is $85 per work-hour. follows: been done. Where Airbus Service Bulletin
VerDate Sep<11>2014 16:06 Jul 01, 2016 Jkt 238001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\05JYR1.SGM 05JYR1](https://thefederalregister.org/doc/81_FR_43600/page/3.svg)
![Federal Register / Vol. 81, No. 128 / Tuesday, July 5, 2016 / Rules and Regulations 43475
A300–57–6115, dated April 4, 2014, refers to (j) Other FAA AD Provisions (ii) Airbus Service Bulletin A300–57–6115,
Structural Repair Manual (SRM) 51–40–13 The following provisions also apply to this dated April 4, 2014.
for applying special protection, the correct AD: (3) For Airbus service information
reference is SRM 51–23–20; and to SRM 51– (1) Alternative Methods of Compliance identified in this final rule, contact Airbus
40–12 for applying paint coatings, the correct (AMOCs): The Manager, International SAS, Airworthiness Office—EAW, 1 Rond
reference is SRM 51–23–10. Branch, ANM–116, Transport Airplane Point Maurice Bellonte, 31707 Blagnac
Directorate, FAA, has the authority to Cedex, France; telephone +33 5 61 93 36 96;
(h) Repetitive Rototest Inspections fax +33 5 61 93 44 51; email
approve AMOCs for this AD, if requested
Within 36 months after the effective date using the procedures found in 14 CFR 39.19. account.airworth-eas@airbus.com; Internet
of this AD: Remove the fasteners and In accordance with 14 CFR 39.19, send your http://www.airbus.com.
measure the diameter of the fastener holes; request to your principal inspector or local (4) You may view this service information
and, before further flight, do the applicable Flight Standards District Office, as at the FAA, Transport Airplane Directorate,
actions required by paragraph (h)(1) or (h)(2) appropriate. If sending information directly 1601 Lind Avenue SW., Renton, WA. For
of this AD, in accordance with the to the International Branch, send it to ATTN: information on the availability of this
Accomplishment Instructions of Airbus Dan Rodina, Aerospace Engineer, material at the FAA, call 425–227–1221.
International Branch, ANM–116, Transport (5) You may view this service information
Service Bulletin A300–57–0257, excluding
Airplane Directorate, FAA, 1601 Lind that is incorporated by reference at the
Appendix 01 and including Appendix 02,
Avenue SW., Renton, WA 98057–3356; National Archives and Records
dated April 4, 2014 (for Model A300 B2–1A,
telephone 425–227–2125; fax 425–227–1149. Administration (NARA). For information on
B2–1C, B2K–3C, B2–203, B4–2C, B4–103, the availability of this material at NARA, call
and B4–203 airplanes); or Airbus Service Information may be emailed to: 9-ANM-116-
AMOC-REQUESTS@faa.gov. Before using 202–741–6030, or go to: http://
Bulletin A300–57–6115, dated April 4, 2014 www.archives.gov/federal-register/cfr/ibr-
(for Model A300 B4–601, B4–603, B4–620, any approved AMOC, notify your appropriate
principal inspector, or lacking a principal locations.html.
B4–622, B4–605R, B4–622R, F4–605R, F4–
622R, and C4–605R Variant F airplanes). inspector, the manager of the local flight Issued in Renton, Washington, on June 21,
(1) If one or more of the hole diameters is standards district office/certificate holding 2016.
outside the tolerance of the nominal district office. The AMOC approval letter Dorr M. Anderson,
diameter, and outside the tolerance of the must specifically reference this AD.
Acting Manager, Transport Airplane
first and second oversize: Do the applicable (2) Contacting the Manufacturer: For any
Directorate, Aircraft Certification Service.
corrective actions required by paragraph (i) of requirement in this AD to obtain corrective
actions from a manufacturer, the action must [FR Doc. 2016–15356 Filed 7–1–16; 8:45 am]
this AD.
(2) If all of the hole diameters are within be accomplished using a method approved BILLING CODE 4910–13–P
by the Manager, International Branch, ANM–
the tolerance of the nominal diameter or the
116, Transport Airplane Directorate, FAA; or
first or second oversize: Do detailed and
the EASA; or Airbus’s EASA DOA. If DEPARTMENT OF TRANSPORTATION
rototest inspections for cracking of the
approved by the DOA, the approval must
fastener holes at the left-hand and right-hand
include the DOA-authorized signature. Federal Aviation Administration
sides of the FR40 lower junction, in
(3) Required for Compliance (RC): Except
accordance with the Accomplishment
as required by paragraph (i) of this AD: If any 14 CFR Part 39
Instructions of Airbus Service Bulletin A300–
service information contains procedures or
57–0257, excluding Appendix 01 and [Docket No. FAA–2015–8131; Directorate
tests that are identified as RC, those
including Appendix 02, dated April 4, 2014 Identifier 2015–NM–073–AD; Amendment
procedures and tests must be done to comply
(for Model A300 B2–1A, B2–1C, B2K–3C, 39–18575; AD 2016–13–11]
with this AD; any procedures or tests that are
B2–203, B4–2C, B4–103, and B4–203 not identified as RC are recommended. Those
airplanes); or Airbus Service Bulletin A300– RIN 2120–AA64
procedures and tests that are not identified
57–6115, dated April 4, 2014 (for Model as RC may be deviated from using accepted
A300 B4–601, B4–603, B4–620, B4–622, B4– methods in accordance with the operator’s
Airworthiness Directives; The Boeing
605R, B4–622R, F4–605R, F4–622R, and C4– maintenance or inspection program without Company Airplanes
605R Variant F airplanes). If no cracking is obtaining approval of an AMOC, provided
found, before further flight, install new AGENCY: Federal Aviation
the procedures and tests identified as RC can Administration (FAA), DOT.
fasteners of the same diameter in special be done and the airplane can be put back in
clearance fit for fasteners 1 through 3 of the an airworthy condition. Any substitutions or ACTION: Final rule.
FR40 lower junction, in accordance with the changes to procedures or tests identified as
Accomplishment Instructions of Airbus SUMMARY: We are superseding
RC require approval of an AMOC.
Service Bulletins A300–57–0257, excluding Airworthiness Directive (AD) 2008–05–
Appendix 01 and including Appendix 02, (k) Related Information 06 for certain The Boeing Company
dated April 4, 2014; or Airbus Service Refer to Mandatory Continuing Model 737–100, –200, –300, –400, and
Bulletin A300–57–6115, dated April 4, 2014. Airworthiness Information (MCAI) EASA –500 series airplanes. AD 2008–05–06
Repeat the rototest inspection thereafter at Airworthiness Directive 2014–0272, dated required repetitive inspections for
intervals not to exceed 7,000 flight cycles. December 12, 2014, for related information. fatigue cracking in the longitudinal floor
Accomplishment of a rototest inspection This MCAI may be found in the AD docket
required by this paragraph terminates the
beam web, upper chord, and lower
on the Internet at http://www.regulations.gov
repetitive HFEC inspections required by chord located at certain body stations,
by searching for and locating Docket No.
paragraph (g) of this AD. FAA–2015–8134. and repair if necessary. This new AD
requires, for certain airplanes, an
(i) Corrective Actions (l) Material Incorporated by Reference inspection to determine if tapered fillers
If, during any inspection required by this (1) The Director of the Federal Register are installed, and related investigative
AD, any crack is found, or one or more of the approved the incorporation by reference and corrective actions if necessary. This
hole diameters is outside the tolerance of the (IBR) of the service information listed in this AD was prompted by reports of cracks
sradovich on DSK3GDR082PROD with RULES
nominal diameter, and outside the tolerance paragraph under 5 U.S.C. 552(a) and 1 CFR in the center wing box longitudinal floor
of the first and second oversize: Repair before part 51.
further flight in accordance with a method
beams, upper chord, and lower chord.
(2) You must use this service information
approved by the Manager, International as applicable to do the actions required by We are issuing this AD to detect and
Branch, ANM–116, Transport Airplane this AD, unless this AD specifies otherwise. correct fatigue cracking of the upper and
Directorate, FAA; or the European Aviation (i) Airbus Service Bulletin A300–57–0257, lower chords and web of the
Safety Agency (EASA); or Airbus’s EASA excluding Appendix 01 and including longitudinal floor beams, which could
Design Organization Approval (DOA). Appendix 02, dated April 4, 2014. result in rapid loss of cabin pressure.
VerDate Sep<11>2014 16:06 Jul 01, 2016 Jkt 238001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 E:\FR\FM\05JYR1.SGM 05JYR1](https://thefederalregister.org/doc/81_FR_43600/page/4.svg)
Document Created: 2016-07-01 23:50:14
Document Modified: 2016-07-01 23:50:14
| 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 becomes effective August 9, 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 43472 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR