Airworthiness Directives; Airbus Airplanes, 30958-30961 [2017-13763]

Download as PDF 30958 Federal Register / Vol. 82, No. 127 / Wednesday, July 5, 2017 / Rules and Regulations District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238–7125. (5) You may view this service information 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/ibrlocations.html. 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–2016– 0461. Issued in Burlington, Massachusetts, on May 11, 2017. Robert J. Ganley, Acting Manager, Engine & Propeller Directorate, Aircraft Certification Service. Examining the AD Docket [FR Doc. 2017–14050 Filed 7–3–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–0461; Directorate Identifier 2014–NM–159–AD; Amendment 39–18937; AD 2017–13–07] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus Model A319, A320, and A321 series airplanes. This AD was prompted by a report that a main landing gear (MLG) door could not be closed due to rupture of the actuator fitting. This AD requires repetitive inspections for cracking of the MLG door actuator fitting and its components, and corrective actions if necessary. This AD also requires eventual replacement of all affected MLG door actuator fittings with new monoblock fittings, which would terminate the repetitive inspections. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective August 9, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 9, 2017. ADDRESSES: For service information identified in this final rule, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this referenced service sradovich on DSK3GMQ082PROD with RULES SUMMARY: VerDate Sep<11>2014 16:11 Jul 03, 2017 Jkt 241001 You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 0461; 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 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A319, A320, and A321 series airplanes. The SNPRM published in the Federal Register on April 7, 2017 (82 FR 16948) (‘‘the SNPRM’’). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on January 28, 2016 (81 FR 4901) (‘‘the NPRM’’). The NPRM proposed to require repetitive inspections for cracking of the MLG door actuator fitting and its components, and corrective actions if necessary. The NPRM also proposed to require eventual replacement of all affected MLG door actuator fittings with new monoblock fittings, which would terminate the repetitive inspections. The NPRM was prompted by a report that an MLG door could not be closed due to rupture of the actuator fitting. The SNPRM proposed to revise the NPRM by reducing the compliance time for replacing the MLG actuator fitting and removing an inspection requirement for certain airplanes. We are issuing this PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 AD to prevent rupture of the door actuator fittings, which could result in detachment of an MLG door and subsequent exterior damage and consequent reduced structural integrity of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2016–0182, dated September 13, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A319, A320, and A321 series airplanes. The MCAI states: On one A320 aeroplane, it was reported that one of the main landing gear (MLG) doors could not be closed. Investigations revealed the rupture of the actuator fitting at the actuator attachment area on the door side. The MLG door is attached to the aeroplane by 2 (two) hinge fittings. This condition, if not corrected, could, under certain circumstances, lead to detachment of a MLG door from the aeroplane, possibly resulting in damage to the aeroplane, and/or injury to persons on the ground. Prompted by these findings, [Direction ´ ´ Generale de l’Aviation Civile] France issued * * * [an AD] * * *, to require a MLG door actuator fitting inspection for cracks and to check the grain direction on a batch of aeroplanes. Subsequently, DGAC France issued * * * [an AD], retaining the requirements of DGAC France AD * * *, which was superseded, to require an inspection of the lower part of the MLG door actuator fitting. After that [DGAC] AD was issued, additional investigations revealed that damage could also appear on the nerve area [of the forward monoblock fitting], in the upper part of the MLG door actuator fitting in the area of the hinge. Consequently, DGAC France issued F– 2003–434, dated December 10, 2003 [http:// ad.easa.europa.eu/ad/F-2003-454] (EASA approval 2003–1436), retaining the requirements of [a] DGAC France AD * * *, which was superseded, to require additional repetitive inspections. That [DGAC] AD also included an optional terminating action, by replacing the MLG door actuator fittings in accordance with the instructions of Airbus Service Bulletin (SB) A320–52–1073. After DGAC France AD F–2003–434 was issued, in the framework of the extended service goal campaign, it was decided to make replacement of the MLG door actuator fittings a required modification. Consequently, EASA issued AD 2014–0166 * * *, retaining the requirements of DGAC France AD F–2003–434, which was superseded, and requiring replacement of the MLG door actuator fittings with new monoblock fittings, which constitutes terminating action for the repetitive inspections. After EASA AD 2014–0166 [corresponding to the NPRM] was issued, errors were identified in the compliance time definitions. E:\FR\FM\05JYR1.SGM 05JYR1 Federal Register / Vol. 82, No. 127 / Wednesday, July 5, 2017 / Rules and Regulations Replacement of the MLG door actuator fittings was required ‘‘before exceeding 48,000 flight cycles (FC) or 96,000 flight hours (FH), whichever occurs later since aeroplane first flight’’, which should have been ‘‘whichever occurs first’’. Furthermore, since the MLG door is an interchangeable part, the compliance time must be defined as FC/FH accumulated by the MLG door. Furthermore, it was discovered that one of the required inspection[s] is applicable only to a batch of MLG door fittings. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2014–0166, which is superseded, but requires accomplishment of the terminating action within more stringent compliance times, and reduce[s] the applicability of one of the required inspection[s]. 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–2016– 0461. Comments We gave the public the opportunity to participate in developing this AD. We considered the comments received. United Airlines and commenter Lisa Stamps supported the SNPRM. Clarification of Provisions for Excluded Airplanes In paragraph (l)(1) of the proposed AD (in the SNPRM), we inadvertently omitted wording related to the prohibition on installing certain MLG door actuator fittings on modified airplanes, which is identified in step 10 of the EASA AD. We have added that provision to paragraph (l)(1) of this AD. sradovich on DSK3GMQ082PROD with RULES Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the change described previously, except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the SNPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the SNPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information: • Airbus Service Bulletin A320–52– 1073, Revision 04, dated August 10, 1999. • Airbus Service Bulletin A320–52– 1073, Revision 05, dated September 28, 2006. This service information describes procedures for replacement of MLG VerDate Sep<11>2014 16:11 Jul 03, 2017 Jkt 241001 30959 door actuator fittings with new monoblock fittings. These documents are distinct due to editorial revisions. Airbus has also issued the following service information: • Airbus Service Bulletin A320– 52A1086, Revision 01, dated September 10, 1999. This service information describes procedures for high frequency eddy current (HFEC) inspections for cracking of the MLG door fittings, and low frequency eddy current (LFEC) inspections to determine grain direction of raw material of each actuator fitting. • Airbus Service Bulletin A320–52– 1096, Revision 02, dated July 12, 2006. This service information describes procedures for HFEC inspections of both hinge and nerve areas of the MLG doors for cracking. 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. 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. Costs of Compliance We estimate that this AD affects 71 airplanes of U.S. registry. We also estimate that it takes about 136 work-hours per product to comply with the requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $6,258 per product. Based on these figures, we estimate the cost for the actions required by this AD on U.S. operators to be $1,265,078, or $17,818 per product. Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: 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 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): 2017–13–07 Airbus: Amendment 39–18937; Docket No. FAA–2016–0461; Directorate Identifier 2014–NM–159–AD. (a) Effective Date This AD is effective August 9, 2017. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes, certificated in any category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, all manufacturer serial numbers. (1) Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (2) Model A320–211, –212, –214, –231, –232, and –233 airplanes. (3) Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 52, Doors. (e) Reason This AD was prompted by a report that a main landing gear (MLG) door could not be closed due to rupture of the actuator fitting. E:\FR\FM\05JYR1.SGM 05JYR1 30960 Federal Register / Vol. 82, No. 127 / Wednesday, July 5, 2017 / Rules and Regulations Later reports indicated that the forward monoblock fitting of the MLG door actuator (referred to as the nerve area) could be damaged after rupture of the actuator fitting. We are issuing this AD to prevent rupture of the door actuator fittings, which could result in detachment of an MLG door and subsequent exterior damage and consequent reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. sradovich on DSK3GMQ082PROD with RULES (g) Repetitive Inspections of MLG Door Actuator Fittings For airplanes equipped with MLG door actuator fittings having part number (P/N) D52880224000 or P/N D52880224001 that were installed before the first flight of the airplane on MLG doors identified in paragraphs (g)(1) and (g)(2) of this AD: Within 500 flight hours since the most recent high frequency eddy current (HFEC) inspection done as specified in Airbus Service Bulletin A320–52A1086, Revision 01, dated September 10, 1999, or within 30 days after the effective date of this AD, whichever occurs later, perform an HFEC inspection for cracking of the MLG door fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 52A1086, Revision 01, dated September 10, 1999. Repeat the inspection thereafter at intervals not to exceed 500 flight hours, except as provided by paragraphs (i), (j), and (k) of this AD. (1) Left-hand MLG doors with serial numbers (S/Ns) 1206 through 1237 inclusive, 1239 through 1247 inclusive, and 1249 through 1251 inclusive. (2) Right-hand MLG doors with S/Ns 1208 through 1239 inclusive, 1241 through 1249 inclusive, and 1251. (h) Repetitive Inspections of MLG Hinge and Nerve Areas For airplanes equipped with MLG door actuator fittings having P/N D52880224000, P/N D52880224001, P/N D52880235000, or P/N D52880235001 that were installed before the first flight of the airplane on MLG doors identified in paragraphs (h)(1) and (h)(2) of this AD: Within 400 flight cycles after the effective date of this AD, or before the accumulation of 9,000 total flight cycles since first flight of the airplane, whichever occurs later, perform an HFEC inspection of both hinge and nerve areas of the MLG doors for cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–52–1096, Revision 02, dated July 12, 2006. Repeat the inspection thereafter at intervals not to exceed 800 flight cycles, except as provided by paragraphs (i)(1), (j), and (k) of this AD. (1) Left-hand MLG doors with S/Ns 1206 through 1510 inclusive, 1548, 1564, and 2000 through 2065 inclusive. (2) Right-hand MLG doors with S/Ns 1208 through 1519 inclusive, 1551, and 2000 through 2065 inclusive. (i) Inspections/Corrective Actions (1) If any crack is found during any inspection required by paragraph (g) or (h) of VerDate Sep<11>2014 16:11 Jul 03, 2017 Jkt 241001 this AD: Before further flight, replace the affected MLG door actuator fittings with new monoblock fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–52–1073, Revision 05, dated September 28, 2006. Accomplishing this replacement terminates the repetitive inspections required by paragraphs (g) and (h) of this AD. (2) If, during any HFEC inspection required by paragraph (g) of this AD, no crack is found: Before further flight, perform a low frequency eddy current (LFEC) inspection to determine the grain direction of the raw material of each MLG actuator fitting, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 52A1086, Revision 01, dated September 10, 1999. (i) If the grain direction of the raw material is correct, the repetitive inspections required by paragraph (g) of this AD may be terminated. (ii) If the grain direction of the raw material is incorrect, repeat the HFEC inspection required by paragraph (g) of this AD at the time specified in paragraph (g) of this AD. Replacement of the MLG door actuator fittings with new monoblock fittings as specified in paragraph (i)(1) of this AD terminates the repetitive inspections required by paragraphs (g) and (i)(2)(ii) of this AD. (j) MLG Door Actuator Fitting Replacement For airplanes equipped with any MLG door actuator fitting having P/N D52880102000, P/ N D52880102001, P/N D52880220000, P/N D52880220001, P/N D52880224000, P/N D52880224001, P/N D52880235000, or P/N D52880235001: At the later of the times specified in paragraphs (j)(1) and (j)(2) of this AD, replace the MLG door actuator fittings with new monoblock fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–52–1073, Revision 05, dated September 28, 2006. Accomplishing this replacement terminates the repetitive inspections required by paragraphs (g) and (h) of this AD. (1) Before the accumulation of 48,000 total flight cycles or 96,000 total flight hours on the MLG door, whichever occurs first. (2) Within 30 days after the effective date of this AD. (k) Optional Terminating Action Replacement of the MLG door actuator fittings with new monoblock fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 52–1073, Revision 04, dated August 10, 1999; or Airbus Service Bulletin A320–52–1073, Revision 05, dated September 28, 2006; terminates the repetitive inspections required by paragraphs (g) and (h) of this AD. (l) Airplanes Excluded From Certain AD Requirements (1) For airplanes on which Airbus Modification 24903, or Airbus Modification 25372, or Airbus Modification 36979 has been embodied in production, no action is required by this AD, provided that no MLG door actuator fitting having any part number identified in paragraph (j) of this AD has been reinstalled on the airplane since first flight; except the requirements of paragraph PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 (m) of this AD remain applicable to post-mod 24903, post-mod 25372 and post-mod 36979 airplanes. (2) Modification of an airplane by installing a version (P/N) of the MLG door actuator fitting approved after the effective date of this AD is acceptable for compliance with the requirements in paragraph (j) of this AD, provided the conditions specified in paragraphs (l)(2)(i) and (l)(2)(ii) are met. (i) The MLG door actuator fitting (P/N) must be 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). (ii) The modification must be accomplished in accordance with instructions approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; EASA; or Airbus’s EASA DOA. (m) Parts Installation Prohibition As of the effective date of this AD, no person may install an MLG door actuator fitting having any part number identified in paragraph (j) of this AD on any airplane. (n) 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 the person identified in paragraph (o)(2) of this AD. Information may be emailed to: 9-ANM116-AMOC-REQUESTS@faa.gov. 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. (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. (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2016–0182, dated September 13, 2016, 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–2016–0461. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. E:\FR\FM\05JYR1.SGM 05JYR1 Federal Register / Vol. 82, No. 127 / Wednesday, July 5, 2017 / Rules and Regulations (p) 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 A320–52–1073, Revision 04, dated August 10, 1999. (ii) Airbus Service Bulletin A320–52–1073, Revision 05, dated September 28, 2006. (iii) Airbus Service Bulletin A320– 52A1086, Revision 01, dated September 10, 1999. (iv) Airbus Service Bulletin A320–52– 1096, Revision 02, dated July 12, 2006. (3) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; 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/ibrlocations.html. Issued in Renton, Washington, on June 19, 2017. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–13763 Filed 7–3–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0126; Directorate Identifier 2016–NM–211–AD; Amendment 39–18943; AD 2017–13–13] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. sradovich on DSK3GMQ082PROD with RULES AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. This AD was prompted by reports of frame web cracking at certain locations. This AD requires repetitive inspections in certain SUMMARY: VerDate Sep<11>2014 16:11 Jul 03, 2017 Jkt 241001 locations of the frame web, and corrective action if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective August 9, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 9, 2017. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; Internet https://www.myboeingfleet.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227– 1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2017–0126. 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–2017– 0126; 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 final rule, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Galib Abumeri, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5324; fax: 562–627–5210; email: galib.abumeri@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. The NPRM published in the Federal Register on March 2, 2017 (82 FR 12303) (‘‘the NPRM’’). The NPRM was prompted by reports of frame web PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 30961 cracking at the station (STA) 344 system penetration holes between stringer S– 22L and stringer S–24L. The NPRM proposed to require repetitive inspections in certain locations of the frame web, and corrective action if necessary. We are issuing this AD to detect and correct frame web cracking, which could grow in size until frames sever. Multiple adjacent severed frames, or a severed frame near cracks in the chem-milled fuselage skin, could result in uncontrolled decompression of the airplane. 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 Change Inspection and Corrective Actions for Group 1 Airplanes Boeing requested that we change the language in paragraph (g) of the proposed AD to remove a reference to Parts 2 and 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1354, dated December 2, 2016. Boeing noted that Group 1 airplanes are those that have exceeded their limit of validity, and that the inspections are not applicable to those airplanes. Boeing stated that it believes the intent of paragraph (g) of the proposed AD is for the operator to obtain maintenance actions in accordance with a method approved by the FAA. Boeing further pointed out that the language in paragraph (g) of the proposed AD allows operators to perform inspections in accordance with Boeing Alert Service Bulletin 737– 53A1354, dated December 2, 2016, rather than in accordance with paragraph (j) of the proposed AD (obtaining an alternative method of compliance). We agree with the commenter’s request for the reasons provided. We have revised paragraph (g) of this AD to clarify the appropriate actions for Group 1 airplanes. Request To Correct a Service Bulletin Number Boeing requested that we change two sentences in paragraph (h) of the proposed AD that refer to ‘‘Boeing Alert Service Bulletin 757–53A1354.’’ Boeing noted that the correct service bulletin number is ‘‘737–53A1354.’’ We agree with the commenter’s request and have revised paragraph (h) of this AD accordingly. E:\FR\FM\05JYR1.SGM 05JYR1

Agencies

[Federal Register Volume 82, Number 127 (Wednesday, July 5, 2017)]
[Rules and Regulations]
[Pages 30958-30961]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-13763]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-0461; Directorate Identifier 2014-NM-159-AD; 
Amendment 39-18937; AD 2017-13-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A319, A320, and A321 series airplanes. This AD was 
prompted by a report that a main landing gear (MLG) door could not be 
closed due to rupture of the actuator fitting. This AD requires 
repetitive inspections for cracking of the MLG door actuator fitting 
and its components, and corrective actions if necessary. This AD also 
requires eventual replacement of all affected MLG door actuator 
fittings with new monoblock fittings, which would terminate the 
repetitive inspections. We are issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective August 9, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 9, 
2017.

ADDRESSES: For service information identified in this final rule, 
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 44 51; email account.airworth-eas@airbus.com; 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-2016-
0461.

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-2016-
0461; 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 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: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 by adding an AD that would apply to all Airbus 
Model A319, A320, and A321 series airplanes. The SNPRM published in the 
Federal Register on April 7, 2017 (82 FR 16948) (``the SNPRM''). We 
preceded the SNPRM with a notice of proposed rulemaking (NPRM) that 
published in the Federal Register on January 28, 2016 (81 FR 4901) 
(``the NPRM''). The NPRM proposed to require repetitive inspections for 
cracking of the MLG door actuator fitting and its components, and 
corrective actions if necessary. The NPRM also proposed to require 
eventual replacement of all affected MLG door actuator fittings with 
new monoblock fittings, which would terminate the repetitive 
inspections. The NPRM was prompted by a report that an MLG door could 
not be closed due to rupture of the actuator fitting. The SNPRM 
proposed to revise the NPRM by reducing the compliance time for 
replacing the MLG actuator fitting and removing an inspection 
requirement for certain airplanes. We are issuing this AD to prevent 
rupture of the door actuator fittings, which could result in detachment 
of an MLG door and subsequent exterior damage and consequent reduced 
structural integrity of the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2016-0182, dated September 13, 2016 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A319, A320, and A321 series airplanes. The MCAI states:

    On one A320 aeroplane, it was reported that one of the main 
landing gear (MLG) doors could not be closed. Investigations 
revealed the rupture of the actuator fitting at the actuator 
attachment area on the door side. The MLG door is attached to the 
aeroplane by 2 (two) hinge fittings.
    This condition, if not corrected, could, under certain 
circumstances, lead to detachment of a MLG door from the aeroplane, 
possibly resulting in damage to the aeroplane, and/or injury to 
persons on the ground.
    Prompted by these findings, [Direction G[eacute]n[eacute]rale de 
l'Aviation Civile] France issued * * * [an AD] * * *, to require a 
MLG door actuator fitting inspection for cracks and to check the 
grain direction on a batch of aeroplanes. Subsequently, DGAC France 
issued * * * [an AD], retaining the requirements of DGAC France AD * 
* *, which was superseded, to require an inspection of the lower 
part of the MLG door actuator fitting.
    After that [DGAC] AD was issued, additional investigations 
revealed that damage could also appear on the nerve area [of the 
forward monoblock fitting], in the upper part of the MLG door 
actuator fitting in the area of the hinge.
    Consequently, DGAC France issued F-2003-434, dated December 10, 
2003 [http://ad.easa.europa.eu/ad/F-2003-454] (EASA approval 2003-
1436), retaining the requirements of [a] DGAC France AD * * *, which 
was superseded, to require additional repetitive inspections. That 
[DGAC] AD also included an optional terminating action, by replacing 
the MLG door actuator fittings in accordance with the instructions 
of Airbus Service Bulletin (SB) A320-52-1073.
    After DGAC France AD F-2003-434 was issued, in the framework of 
the extended service goal campaign, it was decided to make 
replacement of the MLG door actuator fittings a required 
modification. Consequently, EASA issued AD 2014-0166 * * *, 
retaining the requirements of DGAC France AD F-2003-434, which was 
superseded, and requiring replacement of the MLG door actuator 
fittings with new monoblock fittings, which constitutes terminating 
action for the repetitive inspections.
    After EASA AD 2014-0166 [corresponding to the NPRM] was issued, 
errors were identified in the compliance time definitions.

[[Page 30959]]

Replacement of the MLG door actuator fittings was required ``before 
exceeding 48,000 flight cycles (FC) or 96,000 flight hours (FH), 
whichever occurs later since aeroplane first flight'', which should 
have been ``whichever occurs first''. Furthermore, since the MLG 
door is an interchangeable part, the compliance time must be defined 
as FC/FH accumulated by the MLG door. Furthermore, it was discovered 
that one of the required inspection[s] is applicable only to a batch 
of MLG door fittings.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0166, which is superseded, but requires 
accomplishment of the terminating action within more stringent 
compliance times, and reduce[s] the applicability of one of the 
required inspection[s].

    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-2016-
0461.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received. United Airlines and 
commenter Lisa Stamps supported the SNPRM.

Clarification of Provisions for Excluded Airplanes

    In paragraph (l)(1) of the proposed AD (in the SNPRM), we 
inadvertently omitted wording related to the prohibition on installing 
certain MLG door actuator fittings on modified airplanes, which is 
identified in step 10 of the EASA AD. We have added that provision to 
paragraph (l)(1) of this AD.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the change described previously, except for minor 
editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
SNPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information:
     Airbus Service Bulletin A320-52-1073, Revision 04, dated 
August 10, 1999.
     Airbus Service Bulletin A320-52-1073, Revision 05, dated 
September 28, 2006.
    This service information describes procedures for replacement of 
MLG door actuator fittings with new monoblock fittings. These documents 
are distinct due to editorial revisions.
    Airbus has also issued the following service information:
     Airbus Service Bulletin A320-52A1086, Revision 01, dated 
September 10, 1999. This service information describes procedures for 
high frequency eddy current (HFEC) inspections for cracking of the MLG 
door fittings, and low frequency eddy current (LFEC) inspections to 
determine grain direction of raw material of each actuator fitting.
     Airbus Service Bulletin A320-52-1096, Revision 02, dated 
July 12, 2006. This service information describes procedures for HFEC 
inspections of both hinge and nerve areas of the MLG doors for 
cracking.
    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 71 airplanes of U.S. registry.
    We also estimate that it takes about 136 work-hours per product to 
comply with the requirements of this AD. The average labor rate is $85 
per work-hour. Required parts will cost about $6,258 per product. Based 
on these figures, we estimate the cost for the actions required by this 
AD on U.S. operators to be $1,265,078, or $17,818 per product.

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):

2017-13-07 Airbus: Amendment 39-18937; Docket No. FAA-2016-0461; 
Directorate Identifier 2014-NM-159-AD.

(a) Effective Date

    This AD is effective August 9, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes, certificated in any 
category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of 
this AD, all manufacturer serial numbers.
    (1) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes.
    (2) Model A320-211, -212, -214, -231, -232, and -233 airplanes.
    (3) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 52, Doors.

(e) Reason

    This AD was prompted by a report that a main landing gear (MLG) 
door could not be closed due to rupture of the actuator fitting.

[[Page 30960]]

Later reports indicated that the forward monoblock fitting of the 
MLG door actuator (referred to as the nerve area) could be damaged 
after rupture of the actuator fitting. We are issuing this AD to 
prevent rupture of the door actuator fittings, which could result in 
detachment of an MLG door and subsequent exterior damage and 
consequent reduced structural integrity of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Repetitive Inspections of MLG Door Actuator Fittings

    For airplanes equipped with MLG door actuator fittings having 
part number (P/N) D52880224000 or P/N D52880224001 that were 
installed before the first flight of the airplane on MLG doors 
identified in paragraphs (g)(1) and (g)(2) of this AD: Within 500 
flight hours since the most recent high frequency eddy current 
(HFEC) inspection done as specified in Airbus Service Bulletin A320-
52A1086, Revision 01, dated September 10, 1999, or within 30 days 
after the effective date of this AD, whichever occurs later, perform 
an HFEC inspection for cracking of the MLG door fittings, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-52A1086, Revision 01, dated September 10, 1999. Repeat 
the inspection thereafter at intervals not to exceed 500 flight 
hours, except as provided by paragraphs (i), (j), and (k) of this 
AD.
    (1) Left-hand MLG doors with serial numbers (S/Ns) 1206 through 
1237 inclusive, 1239 through 1247 inclusive, and 1249 through 1251 
inclusive.
    (2) Right-hand MLG doors with S/Ns 1208 through 1239 inclusive, 
1241 through 1249 inclusive, and 1251.

(h) Repetitive Inspections of MLG Hinge and Nerve Areas

    For airplanes equipped with MLG door actuator fittings having P/
N D52880224000, P/N D52880224001, P/N D52880235000, or P/N 
D52880235001 that were installed before the first flight of the 
airplane on MLG doors identified in paragraphs (h)(1) and (h)(2) of 
this AD: Within 400 flight cycles after the effective date of this 
AD, or before the accumulation of 9,000 total flight cycles since 
first flight of the airplane, whichever occurs later, perform an 
HFEC inspection of both hinge and nerve areas of the MLG doors for 
cracking, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-52-1096, Revision 02, dated July 12, 
2006. Repeat the inspection thereafter at intervals not to exceed 
800 flight cycles, except as provided by paragraphs (i)(1), (j), and 
(k) of this AD.
    (1) Left-hand MLG doors with S/Ns 1206 through 1510 inclusive, 
1548, 1564, and 2000 through 2065 inclusive.
    (2) Right-hand MLG doors with S/Ns 1208 through 1519 inclusive, 
1551, and 2000 through 2065 inclusive.

(i) Inspections/Corrective Actions

    (1) If any crack is found during any inspection required by 
paragraph (g) or (h) of this AD: Before further flight, replace the 
affected MLG door actuator fittings with new monoblock fittings, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-52-1073, Revision 05, dated September 28, 2006. 
Accomplishing this replacement terminates the repetitive inspections 
required by paragraphs (g) and (h) of this AD.
    (2) If, during any HFEC inspection required by paragraph (g) of 
this AD, no crack is found: Before further flight, perform a low 
frequency eddy current (LFEC) inspection to determine the grain 
direction of the raw material of each MLG actuator fitting, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-52A1086, Revision 01, dated September 10, 1999.
    (i) If the grain direction of the raw material is correct, the 
repetitive inspections required by paragraph (g) of this AD may be 
terminated.
    (ii) If the grain direction of the raw material is incorrect, 
repeat the HFEC inspection required by paragraph (g) of this AD at 
the time specified in paragraph (g) of this AD. Replacement of the 
MLG door actuator fittings with new monoblock fittings as specified 
in paragraph (i)(1) of this AD terminates the repetitive inspections 
required by paragraphs (g) and (i)(2)(ii) of this AD.

(j) MLG Door Actuator Fitting Replacement

    For airplanes equipped with any MLG door actuator fitting having 
P/N D52880102000, P/N D52880102001, P/N D52880220000, P/N 
D52880220001, P/N D52880224000, P/N D52880224001, P/N D52880235000, 
or P/N D52880235001: At the later of the times specified in 
paragraphs (j)(1) and (j)(2) of this AD, replace the MLG door 
actuator fittings with new monoblock fittings, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A320-52-
1073, Revision 05, dated September 28, 2006. Accomplishing this 
replacement terminates the repetitive inspections required by 
paragraphs (g) and (h) of this AD.
    (1) Before the accumulation of 48,000 total flight cycles or 
96,000 total flight hours on the MLG door, whichever occurs first.
    (2) Within 30 days after the effective date of this AD.

(k) Optional Terminating Action

    Replacement of the MLG door actuator fittings with new monoblock 
fittings, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-52-1073, Revision 04, dated August 10, 
1999; or Airbus Service Bulletin A320-52-1073, Revision 05, dated 
September 28, 2006; terminates the repetitive inspections required 
by paragraphs (g) and (h) of this AD.

(l) Airplanes Excluded From Certain AD Requirements

    (1) For airplanes on which Airbus Modification 24903, or Airbus 
Modification 25372, or Airbus Modification 36979 has been embodied 
in production, no action is required by this AD, provided that no 
MLG door actuator fitting having any part number identified in 
paragraph (j) of this AD has been reinstalled on the airplane since 
first flight; except the requirements of paragraph (m) of this AD 
remain applicable to post-mod 24903, post-mod 25372 and post-mod 
36979 airplanes.
    (2) Modification of an airplane by installing a version (P/N) of 
the MLG door actuator fitting approved after the effective date of 
this AD is acceptable for compliance with the requirements in 
paragraph (j) of this AD, provided the conditions specified in 
paragraphs (l)(2)(i) and (l)(2)(ii) are met.
    (i) The MLG door actuator fitting (P/N) must be 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).
    (ii) The modification must be accomplished in accordance with 
instructions approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; EASA; or Airbus's EASA DOA.

(m) Parts Installation Prohibition

    As of the effective date of this AD, no person may install an 
MLG door actuator fitting having any part number identified in 
paragraph (j) of this AD on any airplane.

(n) 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 the person 
identified in paragraph (o)(2) of this AD. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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.
    (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.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2016-0182, dated September 13, 
2016, 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-2016-0461.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149.

[[Page 30961]]

(p) 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 A320-52-1073, Revision 04, dated 
August 10, 1999.
    (ii) Airbus Service Bulletin A320-52-1073, Revision 05, dated 
September 28, 2006.
    (iii) Airbus Service Bulletin A320-52A1086, Revision 01, dated 
September 10, 1999.
    (iv) Airbus Service Bulletin A320-52-1096, Revision 02, dated 
July 12, 2006.
    (3) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email account.airworth-eas@airbus.com; 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 19, 2017.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-13763 Filed 7-3-17; 8:45 am]
 BILLING CODE 4910-13-P