Airworthiness Directives; Airbus SAS Airplanes, 63389-63392 [2018-26464]

Download as PDF Federal Register / Vol. 83, No. 236 / Monday, December 10, 2018 / Rules and Regulations (b) Totaling the results in section 13(a). Example: Assume you have a 100 percent share in 30 acres of type A forage in the unit, with an amount of insurance of $100 per acre. At the time of loss, the following findings are established: 10 acres had a remaining stand of 75 percent of an adequate stand or greater. 20 acres had a remaining stand less than 75 percent but more than 55 percent of an adequate stand. You also have a 100 percent share in 20 acres of type B forage in the unit, with an amount of insurance of $90 per acre. 10 acres had a remaining stand of 75 percent of an adequate stand or greater. 10 acres had a remaining stand less than 55 percent of an adequate stand. Your indemnity would be calculated as follows: 1. 30 acres × $100 = $3,000 amount of insurance for type A; 20 acres × $90 = $1,800 amount of insurance for type B; 2. 10 acres with 75% of an adequate stand or greater × $100 = $1,000 for type A; 10 acres with 75% of an adequate stand or greater × $900 = $900 for type B; 3. 20 acres with less than 75% but greater than 55% of an adequate stand × $100 × 50 percent = $1,000 for type A; 0 acres with less than 75% but greater than 55% of an adequate stand × $90 × 50 percent = $0 for type B; 4. $1,000 + $1,000 = $2,000 reduction for type A; $900 + $0 = $900 reduction for type B; 5. $3,000 ¥ $2,000 = $1,000 for type A $1,800 ¥ $900 = $900 for type B 6. $1,000 × 100 percent share = $1,000 for type A; $900 × 100 percent share = $900 for type B; 7. $1,000 + $900 = $1,900 total indemnity * * * * * Martin R. Barbre, Manager, Federal Crop Insurance Corporation. [FR Doc. 2018–26559 Filed 12–7–18; 8:45 am] BILLING CODE 3410–08–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0761; Product Identifier 2018–NM–088–AD; Amendment 39–19516; AD 2018–25–05] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain SUMMARY: VerDate Sep<11>2014 16:14 Dec 07, 2018 Jkt 247001 Airbus SAS Model A350–941 airplanes. This AD was prompted by reports that, for multimaterial (hybrid) joints of the passenger door frame fittings, the interfay sealant was not applied between all surfaces of the joint parts. This AD requires modification of the hybrid joints of the passenger doors by applying additional corrosion protection to the hybrid joints of the passenger door frame fittings. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 14, 2019. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 14, 2019. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office— EAL, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email continuedairworthiness.a350@airbus.com; internet https://www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2018– 0761. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0761; or in person at Docket Operations 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 Docket Operations (phone: 800–647–5527) is 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: Kathleen Arrigotti, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3218. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 63389 apply to certain Airbus SAS Model A350–941 airplanes. The NPRM published in the Federal Register on September 4, 2018 (83 FR 44844). The NPRM was prompted by reports that, for multimaterial (hybrid) joints of the passenger door frame fittings, the interfay sealant was not applied between all surfaces of the joint parts. The NPRM proposed to require modification of the hybrid joints of the passenger doors by applying additional corrosion protection to the hybrid joints of the passenger door frame fittings. We are issuing this AD to address water ingress in the hybrid joints and subsequent galvanic corrosion of the aluminum holes. This condition, if not corrected, could lead to failure of the door, resulting in reduced evacuation capacity from the airplane during an emergency and consequent injury to occupants. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2018–0108, dated May 15, 2018 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus SAS Model A350–941 airplanes. The MCAI states: Due to the misinterpretation of the prevailing requirements for multimaterial (hybrid) joints of the passenger door frame fittings, the interfay sealant, which prevents water ingress, was only applied on the surface in direct contact with the aluminum parts and not between all surfaces of the joint parts. For sealing of multi-material-stacks involving aluminum, application of interfay sealant is necessary between all assembled parts, even between parts made of corrosion resistant material, in order to ensure a double barrier to prevent water ingress in the joint and subsequent potential galvanic corrosion on the aluminum holes. This condition, if not corrected, could lead to failure of the door to perform its intended function, possibly resulting in reduced evacuation capacity from the aeroplane during an emergency and consequent injury to occupants. To address this unsafe condition, Airbus developed production mod 110790 and mod 109554 to improve protection against corrosion, and issued the SB [Airbus Service Bulletin A350–52–P012, dated September 7, 2017] to provide modification instructions for in-service pre-mod aeroplanes. For the reasons described above, this [EASA] AD requires a modification by adding sealant and protective treatment on the affected passenger doors. You may examine the MCAI in the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0761. E:\FR\FM\10DER1.SGM 10DER1 63390 Federal Register / Vol. 83, No. 236 / Monday, December 10, 2018 / Rules and Regulations Comments We gave the public the opportunity to participate in developing this final rule. The following presents the comments received on the NPRM and the FAA’s response to each comment. Support for the NPRM The Air Line Pilots Association, International (ALPA), Delta Air Lines (DAL), and JM, a private citizen, indicated their support for the NPRM. Request To Allow Alternative Method of Compliance DAL requested the addition of a paragraph in the final rule that would allow operators to use certain Airbus Model A350 Airplane Maintenance Manual (AMM) tasks, identified in the comment, to accomplish the actions that would be required by the final rule. The commenter noted that the Airbus Model A350 AMM includes tasks related to maintenance of the passenger door frame fittings, including installation of the fittings with sealant applied between the fitting and the door, similar to what is described in the Accomplishment Instructions of Airbus Service Bulletin A350–52–P012, dated September 7, 2017. The commenter also pointed out that the Airbus Model A350 AMM tasks do not include application of a top coat spray or corrosion prevention compound after installation of passenger door frame fittings, or include application of top coat sealant and application of primer over the fasteners, which are included in the Accomplishment Instructions of Airbus Service Bulletin A350–52–P012, dated September 7, 2017. The commenter observed that replacement of passenger door frame fittings in-service is customary, and that if an operator uses the Airbus Model A350 AMM tasks inservice to rework the passenger door frame fittings, the operator could be out of compliance with the requirements of the final rule because of the differences in the procedures between the Airbus Model A350 AMM tasks and the Accomplishment Instructions of Airbus Service Bulletin A350–52–P012, dated September 7, 2017. The commenter also indicated that some operators may perceive using the fay surface sealant as described in the Airbus Model A350 AMM tasks to be a more robust solution than the spray-on corrosion inhibitor compounds or top coating of fasteners described in the Accomplishment Instructions of Airbus Service Bulletin A350–52–P012, dated September 7, 2017. The commenter observed that some operators may prefer to remove the passenger door frame fittings, apply the fay surface sealant, and re-install the passenger door frame fittings. The commenter clarified that the language in the suggested paragraph would not mandate the use of the Airbus Model A350 AMM tasks, but would state that operators would have to apply for an alternative method of compliance (AMOC) in order to use the Airbus Model A350 AMM tasks instead of the procedures in the Accomplishment Instructions of Airbus Service Bulletin A350–52–P012, dated September 7, 2017. We disagree with the commenter’s request. The Airbus Model A350 AMM task numbers provided by the commenter do not match the Airbus Model A350 AMM task numbers specified in Airbus Service Bulletin A350–52–P012, dated September 7, 2017. Also, the commenter did not provide sufficient documentation to show that, in regard to the unsafe condition identified in this AD, the Airbus Model A350 AMM tasks provide an equivalent level of safety as the procedures described in Airbus Service Bulletin A350–52–P012, dated September 7, 2017. Under the provisions of paragraph (h)(1) of this AD, operators may apply for an AMOC to use other Airbus Model A350 AMM tasks instead of the procedures in the Accomplishment Instructions of Airbus Service Bulletin A350–52–P012, dated September 7, 2017. We have not changed this AD in regard to this issue. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this final rule as proposed, except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus SAS has issued Service Bulletin A350–52–P012, dated September 7, 2017. This service information describes procedures for modification of the hybrid joints of the left-hand and right-hand sides of the passenger door frame fittings at doors 1, 2, 3 and 4, by applying additional corrosion protection. 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 1 airplane of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Labor cost Parts cost Cost per product Cost on U.S. operators 60 work-hours × $85 per hour = $5,100 ..................................................................................... $0 $5,100 $5,100 According to the manufacturer, some or all of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all known costs in our cost estimate. VerDate Sep<11>2014 16:14 Dec 07, 2018 Jkt 247001 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. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 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 E:\FR\FM\10DER1.SGM 10DER1 Federal Register / Vol. 83, No. 236 / Monday, December 10, 2018 / Rules and Regulations because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes and associated appliances to the Director of the System Oversight Division. Regulatory Findings 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 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): ■ VerDate Sep<11>2014 16:14 Dec 07, 2018 Jkt 247001 2018–25–05 Airbus SAS: Amendment 39– 19516; Docket No. FAA–2018–0761; Product Identifier 2018–NM–088–AD. (a) Effective Date This AD is effective January 14, 2019. (b) Affected ADs None. (c) Applicability This AD applies to Airbus SAS Model A350–941 airplanes, certificated in any category, as identified in Airbus Service Bulletin A350–52–P012, dated September 7, 2017. (d) Subject Air Transport Association (ATA) of America Code 52, Doors. (e) Reason This AD was prompted by reports that, for multimaterial (hybrid) joints of the passenger door frame fittings, the interfay sealant was not applied between all surfaces of the joint parts. We are issuing this AD to address water ingress in the hybrid joints and subsequent galvanic corrosion of the aluminum holes. This condition, if not corrected, could lead to failure of the door, resulting in reduced evacuation capacity from the airplane during an emergency and consequent injury to occupants. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Modification of Passenger Door Hybrid Joints Within 48 months after the date of issuance of the original certificate of airworthiness or the original export certificate of airworthiness, whichever occurs earlier: Apply additional corrosion protection (e.g. primer/topcoat or corrosion prevention compound) to the hybrid joints of the lefthand and right-hand sides of the passenger door frame fittings at doors 1, 2, 3 and 4, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A350– 52–P012, dated September 7, 2017. (h) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Section, send it to the attention of the person identified in paragraph (i)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@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. PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 63391 (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 Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus SAS’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized signature. (3) Required for Compliance (RC): 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. (i) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2018–0108, dated May 15, 2018, for related information. This MCAI may be found in the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018–0761. (2) For more information about this AD, contact Kathleen Arrigotti, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3218. (j) 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 A350–52–P012, dated September 7, 2017. (ii) [Reserved] (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email continuedairworthiness.a350@airbus.com; internet https://www.airbus.com. (4) You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. E:\FR\FM\10DER1.SGM 10DER1 63392 Federal Register / Vol. 83, No. 236 / Monday, December 10, 2018 / Rules and Regulations Issued in Des Moines, Washington, on November 23, 2018. John P. Piccola, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–26464 Filed 12–7–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0767; Product Identifier 2018–NM–068–AD; Amendment 39–19514; AD 2018–25–03] RIN 2120–AA64 Airworthiness Directives; Fokker Services B.V. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD was prompted by reports that debris from the parking brake shut off valve (PBSOV) could create a partial blockage of the restrictor check valve in the hydraulic return line of the PBSOV. This AD requires replacing the restrictor check valve with an improved valve that has a filter screen. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 14, 2019. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 14, 2019. ADDRESSES: For service information identified in this final rule, contact Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL Hoofddorp, the Netherlands; telephone +31 (0)88–6280–350; fax +31 (0)88– 6280–111; email technicalservices@ fokker.com; internet https:// www.myfokkerfleet.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2018– 0767. SUMMARY: Examining the AD Docket You may examine the AD docket on the internet at https:// VerDate Sep<11>2014 16:14 Dec 07, 2018 Jkt 247001 www.regulations.gov by searching for and locating Docket No. FAA–2018– 0767; or in person at Docket Operations 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 Docket Operations (phone: 800–647–5527) is 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: Tom Rodriguez, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3226. 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 all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. The NPRM published in the Federal Register on September 7, 2018 (83 FR 45362). The NPRM was prompted by reports that debris from the PBSOV could create a partial blockage of the restrictor check valve in the hydraulic return line of the PBSOV. The NPRM proposed to require replacing the restrictor check valve with an improved valve that has a filter screen. We are issuing this AD to address debris from the PBSOV that could create a partial blockage of the restrictor check valve in the hydraulic return line of the PBSOV, which, if not corrected, may prevent complete main landing gear extension, possibly resulting in damage to the airplane during landing, and consequent injury to occupants. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2018–0077 dated April 6, 2018 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. The MCAI states: Service experience with Fokker 70 and Fokker 100 aeroplanes has shown that debris from the parking brake shut-off valve (PBSOV) can eventually block the restrictor check valve in the hydraulic return line of the PBSOV. Prompted by these findings, Fokker Services issued [Service Bulletin] SBF100–32–159 to introduce a new PBSOV and a one-time inspection for debris in the affected part of the hydraulic return system. PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 EASA issued AD 2009–0220 [which corresponds to FAA AD 2010–22–05 (75 FR 66649, October 29, 2010) (‘‘AD 2010–22– 05’’)] to require those actions. In addition, Fokker Services issued SBF100–32–163 to introduce the option to install a restrictor check valve with a filter screen in the return line of the PBSOV. A recent review of inservice experience and the SBF100–32–159 inspection results revealed new occurrences of debris that obstructed (but did not completely block) the restrictor check valve. This condition, if not corrected, might prevent complete main landing gear extension, possibly resulting in damage to the aeroplane during landing, and consequent injury to occupants. To address this potential unsafe condition, Fokker Services issued Revision 1 of SBF100–32–163, providing instructions to replace the restrictor check valve with the improved valve incorporating a filter screen. For the reason described above, this [EASA] AD requires the replacement of the restrictor check valve in the return line of the PBSOV with the improved valve. You may examine the MCAI in the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0767. Comments We gave the public the opportunity to participate in developing this final rule. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this final rule as proposed, except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing 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 Fokker Services B.V. has issued Service Bulletin SBF100–32–163, Revision 1, dated February 21, 2018. This service information describes procedures for removing the restrictor check valve in the hydraulic return line of the PBSOV and installing an improved restrictor check valve that has a filter screen. 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. E:\FR\FM\10DER1.SGM 10DER1

Agencies

[Federal Register Volume 83, Number 236 (Monday, December 10, 2018)]
[Rules and Regulations]
[Pages 63389-63392]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-26464]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0761; Product Identifier 2018-NM-088-AD; Amendment 
39-19516; AD 2018-25-05]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

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

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus SAS Model A350-941 airplanes. This AD was prompted by reports 
that, for multimaterial (hybrid) joints of the passenger door frame 
fittings, the interfay sealant was not applied between all surfaces of 
the joint parts. This AD requires modification of the hybrid joints of 
the passenger doors by applying additional corrosion protection to the 
hybrid joints of the passenger door frame fittings. We are issuing this 
AD to address the unsafe condition on these products.

DATES: This AD is effective January 14, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 14, 
2019.

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile 
Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 
96; fax +33 5 61 93 45 80; email continued-
[email protected]; internet https://www.airbus.com. You may 
view this service information at the FAA, Transport Standards Branch, 
2200 South 216th St., Des Moines, WA. For information on the 
availability of this material at the FAA, call 206-231-3195. It is also 
available on the internet at https://www.regulations.gov by searching 
for and locating Docket No. FAA-2018-0761.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0761; or in person at Docket Operations 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 Docket Operations (phone: 800-647-
5527) is 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: Kathleen Arrigotti, Aerospace 
Engineer, International Section, Transport Standards Branch, FAA, 2200 
South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3218.

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 Airbus SAS Model 
A350-941 airplanes. The NPRM published in the Federal Register on 
September 4, 2018 (83 FR 44844). The NPRM was prompted by reports that, 
for multimaterial (hybrid) joints of the passenger door frame fittings, 
the interfay sealant was not applied between all surfaces of the joint 
parts. The NPRM proposed to require modification of the hybrid joints 
of the passenger doors by applying additional corrosion protection to 
the hybrid joints of the passenger door frame fittings.
    We are issuing this AD to address water ingress in the hybrid 
joints and subsequent galvanic corrosion of the aluminum holes. This 
condition, if not corrected, could lead to failure of the door, 
resulting in reduced evacuation capacity from the airplane during an 
emergency and consequent injury to occupants.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2018-0108, dated May 15, 2018 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for certain Airbus SAS Model A350-941 airplanes. The 
MCAI states:

    Due to the misinterpretation of the prevailing requirements for 
multimaterial (hybrid) joints of the passenger door frame fittings, 
the interfay sealant, which prevents water ingress, was only applied 
on the surface in direct contact with the aluminum parts and not 
between all surfaces of the joint parts. For sealing of multi-
material-stacks involving aluminum, application of interfay sealant 
is necessary between all assembled parts, even between parts made of 
corrosion resistant material, in order to ensure a double barrier to 
prevent water ingress in the joint and subsequent potential galvanic 
corrosion on the aluminum holes.
    This condition, if not corrected, could lead to failure of the 
door to perform its intended function, possibly resulting in reduced 
evacuation capacity from the aeroplane during an emergency and 
consequent injury to occupants.
    To address this unsafe condition, Airbus developed production 
mod 110790 and mod 109554 to improve protection against corrosion, 
and issued the SB [Airbus Service Bulletin A350-52-P012, dated 
September 7, 2017] to provide modification instructions for in-
service pre-mod aeroplanes.
    For the reasons described above, this [EASA] AD requires a 
modification by adding sealant and protective treatment on the 
affected passenger doors.

    You may examine the MCAI in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0761.

[[Page 63390]]

Comments

    We gave the public the opportunity to participate in developing 
this final rule. The following presents the comments received on the 
NPRM and the FAA's response to each comment.

Support for the NPRM

    The Air Line Pilots Association, International (ALPA), Delta Air 
Lines (DAL), and JM, a private citizen, indicated their support for the 
NPRM.

Request To Allow Alternative Method of Compliance

    DAL requested the addition of a paragraph in the final rule that 
would allow operators to use certain Airbus Model A350 Airplane 
Maintenance Manual (AMM) tasks, identified in the comment, to 
accomplish the actions that would be required by the final rule. The 
commenter noted that the Airbus Model A350 AMM includes tasks related 
to maintenance of the passenger door frame fittings, including 
installation of the fittings with sealant applied between the fitting 
and the door, similar to what is described in the Accomplishment 
Instructions of Airbus Service Bulletin A350-52-P012, dated September 
7, 2017.
    The commenter also pointed out that the Airbus Model A350 AMM tasks 
do not include application of a top coat spray or corrosion prevention 
compound after installation of passenger door frame fittings, or 
include application of top coat sealant and application of primer over 
the fasteners, which are included in the Accomplishment Instructions of 
Airbus Service Bulletin A350-52-P012, dated September 7, 2017. The 
commenter observed that replacement of passenger door frame fittings 
in-service is customary, and that if an operator uses the Airbus Model 
A350 AMM tasks in-service to rework the passenger door frame fittings, 
the operator could be out of compliance with the requirements of the 
final rule because of the differences in the procedures between the 
Airbus Model A350 AMM tasks and the Accomplishment Instructions of 
Airbus Service Bulletin A350-52-P012, dated September 7, 2017.
    The commenter also indicated that some operators may perceive using 
the fay surface sealant as described in the Airbus Model A350 AMM tasks 
to be a more robust solution than the spray-on corrosion inhibitor 
compounds or top coating of fasteners described in the Accomplishment 
Instructions of Airbus Service Bulletin A350-52-P012, dated September 
7, 2017. The commenter observed that some operators may prefer to 
remove the passenger door frame fittings, apply the fay surface 
sealant, and re-install the passenger door frame fittings.
    The commenter clarified that the language in the suggested 
paragraph would not mandate the use of the Airbus Model A350 AMM tasks, 
but would state that operators would have to apply for an alternative 
method of compliance (AMOC) in order to use the Airbus Model A350 AMM 
tasks instead of the procedures in the Accomplishment Instructions of 
Airbus Service Bulletin A350-52-P012, dated September 7, 2017.
    We disagree with the commenter's request. The Airbus Model A350 AMM 
task numbers provided by the commenter do not match the Airbus Model 
A350 AMM task numbers specified in Airbus Service Bulletin A350-52-
P012, dated September 7, 2017. Also, the commenter did not provide 
sufficient documentation to show that, in regard to the unsafe 
condition identified in this AD, the Airbus Model A350 AMM tasks 
provide an equivalent level of safety as the procedures described in 
Airbus Service Bulletin A350-52-P012, dated September 7, 2017. Under 
the provisions of paragraph (h)(1) of this AD, operators may apply for 
an AMOC to use other Airbus Model A350 AMM tasks instead of the 
procedures in the Accomplishment Instructions of Airbus Service 
Bulletin A350-52-P012, dated September 7, 2017. We have not changed 
this AD in regard to this issue.

Conclusion

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

Related Service Information Under 1 CFR Part 51

    Airbus SAS has issued Service Bulletin A350-52-P012, dated 
September 7, 2017. This service information describes procedures for 
modification of the hybrid joints of the left-hand and right-hand sides 
of the passenger door frame fittings at doors 1, 2, 3 and 4, by 
applying additional corrosion protection. 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 1 airplane of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
60 work-hours x $85 per hour = $5,100........................              $0           $5,100           $5,100
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some or all of the costs of this AD 
may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all known costs in our cost 
estimate.

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

[[Page 63391]]

because it addresses an unsafe condition that is likely to exist or 
develop on products identified in this rulemaking action.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes and 
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

    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):

2018-25-05 Airbus SAS: Amendment 39-19516; Docket No. FAA-2018-0761; 
Product Identifier 2018-NM-088-AD.

(a) Effective Date

    This AD is effective January 14, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus SAS Model A350-941 airplanes, 
certificated in any category, as identified in Airbus Service 
Bulletin A350-52-P012, dated September 7, 2017.

(d) Subject

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

(e) Reason

    This AD was prompted by reports that, for multimaterial (hybrid) 
joints of the passenger door frame fittings, the interfay sealant 
was not applied between all surfaces of the joint parts. We are 
issuing this AD to address water ingress in the hybrid joints and 
subsequent galvanic corrosion of the aluminum holes. This condition, 
if not corrected, could lead to failure of the door, resulting in 
reduced evacuation capacity from the airplane during an emergency 
and consequent injury to occupants.

(f) Compliance

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

(g) Modification of Passenger Door Hybrid Joints

    Within 48 months after the date of issuance of the original 
certificate of airworthiness or the original export certificate of 
airworthiness, whichever occurs earlier: Apply additional corrosion 
protection (e.g. primer/topcoat or corrosion prevention compound) to 
the hybrid joints of the left-hand and right-hand sides of the 
passenger door frame fittings at doors 1, 2, 3 and 4, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A350-52-P012, dated September 7, 2017.

(h) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Section, send it to the attention of 
the person identified in paragraph (i)(2) of this AD. 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.
    (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 
Section, Transport Standards Branch, FAA; or the European Aviation 
Safety Agency (EASA); or Airbus SAS's EASA Design Organization 
Approval (DOA). If approved by the DOA, the approval must include 
the DOA-authorized signature.
    (3) Required for Compliance (RC): 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.

(i) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2018-0108, dated May 15, 2018, for related 
information. This MCAI may be found in the AD docket on the internet 
at https://www.regulations.gov by searching for and locating Docket 
No. FAA-2018-0761.
    (2) For more information about this AD, contact Kathleen 
Arrigotti, Aerospace Engineer, International Section, Transport 
Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; 
telephone and fax 206-231-3218.

(j) 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 A350-52-P012, dated September 7, 
2017.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile Dewoitine 
No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 45 80; email continued-[email protected]; 
internet https://www.airbus.com.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 
206-231-3195.
    (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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.


[[Page 63392]]


    Issued in Des Moines, Washington, on November 23, 2018.
John P. Piccola,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-26464 Filed 12-7-18; 8:45 am]
 BILLING CODE 4910-13-P
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