Airworthiness Directives; Airbus SAS Airplanes, 30052-30055 [2019-13421]

Download as PDF 30052 Federal Register / Vol. 84, No. 123 / Wednesday, June 26, 2019 / Proposed Rules Considerations in Airborne Systems and Equipment Certification, provides software design assurance levels most commonly used for the major, hazardous/severe-major, and catastrophic failure condition categories. The AP/SAS system equipment must be qualified for the expected installation environment. The test procedures prescribed in RTCA Document DO–160G, Environmental Conditions and Test Procedures for Airborne Equipment, are recognized by the FAA as acceptable methodologies for finding compliance with the environmental requirements. Equivalent environment test standards may also be acceptable. Environmental qualification provides data to show that the AP/SAS system can perform its intended function under the expected operating condition. Some of the main considerations for environmental concerns are installation locations and the resulting exposure to environmental conditions for the AP/SAS system equipment, including considerations for other equipment that may also be affected environmentally by the AP/SAS equipment installation. The level of environmental qualification must be related to the severity of the considered failure conditions and effects on the rotorcraft. Applicability These special conditions are applicable to the AP/SAS installed as an amended TC approval in Robinson Model R66 helicopter, TC Number R00015LA. Conclusion This action affects only certain novel or unusual design features for an AP/ SAS amended TC installed on one model helicopter. It is not a rule of general applicability and affects only the applicant who applied to the FAA for approval of these features. List of Subjects in 14 CFR Part 27 Aircraft, Aviation safety, Reporting and recordkeeping requirements. The authority citation for these special conditions is as follows: jbell on DSK3GLQ082PROD with PROPOSALS Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. The Proposed Special Conditions Accordingly, the Federal Aviation Administration (FAA) proposes the following special conditions as part of the amended type certification basis for installation of the AP/SAS system on Robinson Model R66 helicopters. Instead of the requirements of 14 CFR 27.1309(b) and (c), the following must be met for certification of the AP/SAS VerDate Sep<11>2014 16:20 Jun 25, 2019 Jkt 247001 system installed on Robinson Model R66 helicopters: a. The equipment and systems must be designed and installed so that any equipment and systems do not adversely affect the safety of the rotorcraft or its occupants. b. The rotorcraft systems and associated components considered separately and in relation to others systems, must be designed and installed so that: (1) The occurrence of any catastrophic failure condition is extremely improbable; (2) The occurrence of any hazardous failure condition is extremely remote; and (3) The occurrence of any major failure condition is remote. c. Compliance with the requirements of these special conditions may be shown by a variety of methods, which typically consist of analysis, flight tests, ground tests, and simulation, as a minimum. Compliance methodology is related to the associated failure condition category. Compliance with the requirements for failure conditions classified as ‘‘major’’ may be shown by analysis, in combination with appropriate testing to validate the analysis. Compliance with the requirements for failure conditions classified as ‘‘hazardous/severe-major’’ may be shown by flight-testing in combination with analysis and simulation, and the appropriate testing to validate the analysis. Flight tests may be limited for ‘‘hazardous/severe-major’’ failure conditions and effects due to safety considerations. Compliance with the requirements for failure conditions classified as ‘‘catastrophic’’ may be shown by analysis, and appropriate testing in combination with simulation to validate the analysis. Very limited flight tests in combination with simulation are used as a part of a showing of compliance for ‘‘catastrophic’’ failure conditions. Flight tests are performed only in circumstances that use operational variations, or extrapolations from other flight performance aspects to address flight safety. d. These special conditions require that the AP/SAS system installed on a Robinson Model R66 helicopter, Type Certificate Number R00015LA, meet these requirements to adequately address the failure effects identified by the FHA, and subsequently verified by the SSA, within the defined design system integrity requirements. e. Information concerning an unsafe system operating condition must be provided in a timely manner to the crew to enable them to take appropriate PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 corrective action. An appropriate alert must be provided if immediate pilot awareness and immediate or subsequent corrective action is required. Systems and controls, including indications and annunciations, must be designed to minimize crew errors that could create additional hazards. Issued in Fort Worth, Texas, on June 19, 2019. Stephen Barbini, Acting Manager, Rotorcraft Standards Branch, Policy and Innovation Division, Aircraft Certification Service. [FR Doc. 2019–13651 Filed 6–25–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0485; Product Identifier 2019–NM–064–AD] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for all Airbus SAS Model A330–243, A330– 243F, A330–341, A330–342, and A330– 343 airplanes. This proposed AD was prompted by reports of thrust reverser unit (TRU) beams found with evidence of thermally caused material degradation in the rearmost section of the TRU beam at certain latches. This proposed AD would require an inspection for heat damage of each lefthand and right-hand TRU beam. Depending on findings, this proposed AD might also require inspections of the TRU beam latches, the TRU beam clevises, and the thrust reverser outer fixed structure rear area; corrective actions; and replacement of TRU beams; as specified in a European Aviation Safety Agency (EASA) AD, which will be incorporated by reference. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by August 12, 2019. SUMMARY: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: ADDRESSES: E:\FR\FM\26JNP1.SGM 26JNP1 Federal Register / Vol. 84, No. 123 / Wednesday, June 26, 2019 / Proposed Rules • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For the material identified in this proposed AD that will be incorporated by reference (IBR) contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 89990 1000; email ADs@easa.europa.eu; internet www.easa.europa.eu. You may find this IBR material on the EASA website at https://ad.easa.europa.eu. You may view this IBR material 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 in the AD docket on the internet at https:// www.regulations.gov. 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–2019– 0485; 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 NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3229. SUPPLEMENTARY INFORMATION: jbell on DSK3GLQ082PROD with PROPOSALS Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2019–0485; Product Identifier 2019–NM–064–AD’’ at the beginning of your comments. The FAA specifically invites comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. The FAA will consider all comments received by the closing date VerDate Sep<11>2014 16:20 Jun 25, 2019 Jkt 247001 and may amend this NPRM based on those comments. The FAA will post all comments, without change, to https:// www.regulations.gov, including any personal information you provide. The FAA will also post a report summarizing each substantive verbal contact the agency receives about this NPRM. Discussion The EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2018–0148R1, dated April 5, 2019 (‘‘EASA AD 2018–0148R1’’) (also referred to as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus SAS Model A330–243, A330–243F, A330–341, A330–342, and A330–343 airplanes. The MCAI states: Occurrences have been reported on A330 aeroplanes fitted with Trent 700 engines where a TRU beam was found with evidence of thermally caused material degradation in the rearmost section of the TRU beam at latches 5, 6 and 7 areas. Subsequent fatigue analysis determined that the static strength margins of the material of the TRU beam could be reduced, with detrimental effect on the operational fatigue life of the beam. This condition, if not detected and corrected, could lead to disconnection of the TRU from the engine, with possible damage to the engine adjacent structure and controls, and/or damage to the aeroplane, and injury to persons on the ground. To address this potential unsafe condition, Airbus issued the SB [service bulletin], which includes reference to the instructions of the NMSB [non-modification service bulletin], providing instructions to inspect each TRU beam. For the reasons described above, EASA issued AD 2018–0148 to require repetitive special detailed inspections (SDI) of the TRU beams and, depending on findings, accomplishment of applicable corrective action(s). Since that [EASA] AD was issued, it was found that there may be cases where the flight cycles (FC) accumulated by a TRU beam are unknown (at that time, not a tracked part). This [EASA] AD is revised to clarify that the FC accumulated by the TRU assembly can be used to determine the first inspection. This revised [EASA] AD also introduces a new Table 1 (previous Table 1 becomes Table 2) to improve understanding of the initial compliance time and clarifies the area to be inspected, as specified in Table 2 of this revised AD. Related IBR Material Under 1 CFR part 51 EASA AD 2018–0148R1 describes procedures for a special detailed inspection for heat damage of each lefthand and right-hand TRU beam, detailed inspections of the TRU beam latches for bush migration and cracks or PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 30053 deformation, detailed inspections of the TRU beam clevises for cracks and deformation, ultrasonic inspections of the thrust reverser outer fixed structure rear area for delamination, replacement of TRU beams, and corrective actions. Corrective actions include restoring paint, repairing delaminated areas, and measuring latch pin hole fitting diameters near migrated bushes. This material is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with the State of Design Authority, the FAA has been notified of the unsafe condition described in the MCAI referenced above. The FAA is proposing this AD because the agency evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Proposed Requirements of This NPRM This proposed AD would require accomplishing the actions specified in EASA AD 2018–0148R1 described previously, as incorporated by reference, except for any differences identified as exceptions in the regulatory text of this AD. Explanation of Required Compliance Information In the FAA’s ongoing efforts to improve the efficiency of the AD process, the FAA worked with Airbus and EASA to develop a process to use certain EASA ADs as the primary source of information for compliance with requirements for corresponding FAA ADs. As a result, EASA AD 2018– 0148R1 will be incorporated by reference in the FAA final rule. This proposed AD would, therefore, require compliance with the provisions specified in EASA AD 2018–0148R1, through that incorporation, except for any differences identified as exceptions in the regulatory text of this proposed AD. Service information specified in EASA AD 2018–0148R1 that is required for compliance with EASA AD 2018– 0148R1 will be available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2019–0485 after the FAA final rule is published. E:\FR\FM\26JNP1.SGM 26JNP1 30054 Federal Register / Vol. 84, No. 123 / Wednesday, June 26, 2019 / Proposed Rules Costs of Compliance The FAA estimates that this proposed AD affects 51 airplanes of U.S. registry. The FAA estimates the following costs to comply with this proposed AD: ESTIMATED COSTS FOR REQUIRED ACTIONS Labor cost 1 work-hour × $85 per hour = $85 .............................................................................................. The FAA estimates the following costs to do any necessary on-condition actions that would be required based on Cost per product Parts cost the results of any required actions. The FAA has no way of determining the $0 Cost on U.S. operators $85 $4,335 number of aircraft that might need these on-condition actions: ESTIMATED COSTS OF ON-CONDITION ACTIONS * Labor cost Cost per product Parts cost 2 work-hours × $85 per hour = $170 ...................................................................................................................... $0 $170 * The table only includes the costs for on-condition inspections. The FAA has received no definitive data that would enable the agency to provide cost estimates for the on-condition corrective actions and replacement specified in this proposed AD. According to the manufacturer, some or all of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. The FAA does not control warranty coverage for affected individuals. As a result, the FAA has included all known costs in our cost estimate. jbell on DSK3GLQ082PROD with PROPOSALS 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. The FAA is 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. This proposed 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 VerDate Sep<11>2014 16:20 Jun 25, 2019 Jkt 247001 Director has delegated the authority to issue ADs applicable to transport category airplanes and associated appliances to the Director of the System Oversight Division. 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. Regulatory Findings The FAA determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Will not affect intrastate aviation in Alaska; and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus SAS: Docket No. FAA–2019–0485; Product Identifier 2019–NM–064–AD. (a) Comments Due Date The FAA must receive comments by August 12, 2019. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus SAS Model A330–243, A330–243F, A330– 341, A330–342, and A330–343 airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 78, Engine exhaust. (e) Reason This AD was prompted by reports of thrust reverser unit (TRU) beams found with evidence of thermally caused material degradation in the rearmost section of the TRU beam at certain latches. The FAA is issuing this AD to address degradation of TRU beams, which could lead to disconnection of the TRU from the engine, causing possible damage to the engine adjacent structure and controls, possible damage E:\FR\FM\26JNP1.SGM 26JNP1 Federal Register / Vol. 84, No. 123 / Wednesday, June 26, 2019 / Proposed Rules to the airplane, and possible injury to people on the ground. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Requirements Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Aviation Safety Agency (EASA) AD 2018–0148R1, dated April 5, 2019 (‘‘EASA AD 2018–0148R1’’). (h) Exceptions to EASA AD 2018– 0148R1 (1) For purposes of determining compliance with the requirements of this AD: Where EASA AD 2018–0148R1 refers to its effective date, or July 27, 2018 (the effective date of EASA AD 2018–0148, dated July 13, 2018), this AD requires using the effective date of this AD. (2) The ‘‘Remarks’’ section of EASA AD 2018–0148R1 does not apply to this AD. (i) No Reporting Requirement Although the service information referenced in EASA AD 2018–0148R1 specifies to submit certain information to the manufacturer, this AD does not include that requirement. jbell on DSK3GLQ082PROD with PROPOSALS (j) 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 (k)(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 instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, International Section, VerDate Sep<11>2014 16:20 Jun 25, 2019 Jkt 247001 Transport Standards Branch, FAA; or 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): For any service information referenced in EASA AD 2018–0148R1 that contains RC procedures and tests: Except as required by paragraph (j)(2) of this AD, RC procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (k) Related Information (1) For information about EASA AD 2018–0148R1, contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 89990 6017; email ADs@easa.europa.eu; Internet www.easa.europa.eu. You may find this EASA AD on the EASA website at https://ad.easa.europa.eu. You may view this EASA AD 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. EASA AD 2018–0148R1 may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2019– 0485. (2) For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231– 3229. Issued in Des Moines, Washington, on June 18, 2019. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–13421 Filed 6–25–19; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 30055 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0484; Product Identifier 2019–NM–065–AD] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for all Airbus SAS Model A330–200, A330– 200 Freighter, A330–300, A340–200, A340–300, A340–500, and A340–600 series airplanes. This proposed AD was prompted by a report that an airplane failed to extend its nose landing gear (NLG) using the free fall method, due to loss of the green hydraulic system. This proposed AD would require repetitive tests of affected free fall actuators (FFA), and replacement of any affected FFA that fails a test with a serviceable FFA; as specified in a European Aviation Safety Agency (EASA) AD, which will be incorporated by reference. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by August 12, 2019 ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For the material identified in this proposed AD that will be incorporated by reference (IBR), contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 89990 1000; email: ADs@ easa.europa.eu; internet: www.easa.europa.eu. You may find this IBR material on the EASA website at https://ad.easa.europa.eu. You may view this IBR material at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For SUMMARY: E:\FR\FM\26JNP1.SGM 26JNP1

Agencies

[Federal Register Volume 84, Number 123 (Wednesday, June 26, 2019)]
[Proposed Rules]
[Pages 30052-30055]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-13421]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0485; Product Identifier 2019-NM-064-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for all Airbus SAS Model A330-243, A330-243F, A330-341, A330-342, and 
A330-343 airplanes. This proposed AD was prompted by reports of thrust 
reverser unit (TRU) beams found with evidence of thermally caused 
material degradation in the rearmost section of the TRU beam at certain 
latches. This proposed AD would require an inspection for heat damage 
of each left-hand and right-hand TRU beam. Depending on findings, this 
proposed AD might also require inspections of the TRU beam latches, the 
TRU beam clevises, and the thrust reverser outer fixed structure rear 
area; corrective actions; and replacement of TRU beams; as specified in 
a European Aviation Safety Agency (EASA) AD, which will be incorporated 
by reference. The FAA is proposing this AD to address the unsafe 
condition on these products.

DATES: The FAA must receive comments on this proposed AD by August 12, 
2019.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:

[[Page 30053]]

     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For the material identified in this proposed AD that will be 
incorporated by reference (IBR) contact the EASA, Konrad-Adenauer-Ufer 
3, 50668 Cologne, Germany; telephone +49 221 89990 1000; email 
[email protected]; internet www.easa.europa.eu. You may find this IBR 
material on the EASA website at https://ad.easa.europa.eu. You may view 
this IBR material 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 in the AD 
docket on the internet at https://www.regulations.gov.

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-2019-
0485; 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 NPRM, the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations is listed above. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3229.

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2019-0485; 
Product Identifier 2019-NM-064-AD'' at the beginning of your comments. 
The FAA specifically invites comments on the overall regulatory, 
economic, environmental, and energy aspects of this NPRM. The FAA will 
consider all comments received by the closing date and may amend this 
NPRM based on those comments.
    The FAA will post all comments, without change, to https://www.regulations.gov, including any personal information you provide. 
The FAA will also post a report summarizing each substantive verbal 
contact the agency receives about this NPRM.

Discussion

    The EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2018-0148R1, dated April 5, 2019 
(``EASA AD 2018-0148R1'') (also referred to as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for all Airbus SAS Model A330-243, A330-243F, A330-341, A330-
342, and A330-343 airplanes. The MCAI states:

    Occurrences have been reported on A330 aeroplanes fitted with 
Trent 700 engines where a TRU beam was found with evidence of 
thermally caused material degradation in the rearmost section of the 
TRU beam at latches 5, 6 and 7 areas. Subsequent fatigue analysis 
determined that the static strength margins of the material of the 
TRU beam could be reduced, with detrimental effect on the 
operational fatigue life of the beam.
    This condition, if not detected and corrected, could lead to 
disconnection of the TRU from the engine, with possible damage to 
the engine adjacent structure and controls, and/or damage to the 
aeroplane, and injury to persons on the ground.
    To address this potential unsafe condition, Airbus issued the SB 
[service bulletin], which includes reference to the instructions of 
the NMSB [non-modification service bulletin], providing instructions 
to inspect each TRU beam.
    For the reasons described above, EASA issued AD 2018-0148 to 
require repetitive special detailed inspections (SDI) of the TRU 
beams and, depending on findings, accomplishment of applicable 
corrective action(s).
    Since that [EASA] AD was issued, it was found that there may be 
cases where the flight cycles (FC) accumulated by a TRU beam are 
unknown (at that time, not a tracked part). This [EASA] AD is 
revised to clarify that the FC accumulated by the TRU assembly can 
be used to determine the first inspection. This revised [EASA] AD 
also introduces a new Table 1 (previous Table 1 becomes Table 2) to 
improve understanding of the initial compliance time and clarifies 
the area to be inspected, as specified in Table 2 of this revised 
AD.

Related IBR Material Under 1 CFR part 51

    EASA AD 2018-0148R1 describes procedures for a special detailed 
inspection for heat damage of each left-hand and right-hand TRU beam, 
detailed inspections of the TRU beam latches for bush migration and 
cracks or deformation, detailed inspections of the TRU beam clevises 
for cracks and deformation, ultrasonic inspections of the thrust 
reverser outer fixed structure rear area for delamination, replacement 
of TRU beams, and corrective actions. Corrective actions include 
restoring paint, repairing delaminated areas, and measuring latch pin 
hole fitting diameters near migrated bushes. This material is 
reasonably available because the interested parties have access to it 
through their normal course of business or by the means identified in 
the ADDRESSES section.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to the FAA's bilateral agreement with the State of Design Authority, 
the FAA has been notified of the unsafe condition described in the MCAI 
referenced above. The FAA is proposing this AD because the agency 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Proposed Requirements of This NPRM

    This proposed AD would require accomplishing the actions specified 
in EASA AD 2018-0148R1 described previously, as incorporated by 
reference, except for any differences identified as exceptions in the 
regulatory text of this AD.

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD 
process, the FAA worked with Airbus and EASA to develop a process to 
use certain EASA ADs as the primary source of information for 
compliance with requirements for corresponding FAA ADs. As a result, 
EASA AD 2018-0148R1 will be incorporated by reference in the FAA final 
rule. This proposed AD would, therefore, require compliance with the 
provisions specified in EASA AD 2018-0148R1, through that 
incorporation, except for any differences identified as exceptions in 
the regulatory text of this proposed AD. Service information specified 
in EASA AD 2018-0148R1 that is required for compliance with EASA AD 
2018-0148R1 will be available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0485 after the FAA final rule is published.

[[Page 30054]]

Costs of Compliance

    The FAA estimates that this proposed AD affects 51 airplanes of 
U.S. registry. The FAA estimates the following costs to comply with 
this proposed AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                           Labor cost                               Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
1 work-hour x $85 per hour = $85................................              $0             $85          $4,335
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary on-
condition actions that would be required based on the results of any 
required actions. The FAA has no way of determining the number of 
aircraft that might need these on-condition actions:

                Estimated Costs of On-Condition Actions *
------------------------------------------------------------------------
                                                             Cost per
               Labor cost                   Parts cost        product
------------------------------------------------------------------------
2 work-hours x $85 per hour = $170......              $0            $170
------------------------------------------------------------------------
* The table only includes the costs for on-condition inspections. The
  FAA has received no definitive data that would enable the agency to
  provide cost estimates for the on-condition corrective actions and
  replacement specified in this proposed AD.

    According to the manufacturer, some or all of the costs of this 
proposed AD may be covered under warranty, thereby reducing the cost 
impact on affected individuals. The FAA does not control warranty 
coverage for affected individuals. As a result, the FAA has 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.
    The FAA is 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.
    This proposed 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

    The FAA determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Will not affect intrastate aviation in Alaska; and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Airbus SAS: Docket No. FAA-2019-0485; Product Identifier 2019-NM-
064-AD.

(a) Comments Due Date

    The FAA must receive comments by August 12, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus SAS Model A330-243, A330-243F, A330-
341, A330-342, and A330-343 airplanes, certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 78, Engine exhaust.

(e) Reason

    This AD was prompted by reports of thrust reverser unit (TRU) beams 
found with evidence of thermally caused material degradation in the 
rearmost section of the TRU beam at certain latches. The FAA is issuing 
this AD to address degradation of TRU beams, which could lead to 
disconnection of the TRU from the engine, causing possible damage to 
the engine adjacent structure and controls, possible damage

[[Page 30055]]

to the airplane, and possible injury to people on the ground.

(f) Compliance

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

(g) Requirements

    Except as specified in paragraph (h) of this AD: Comply with all 
required actions and compliance times specified in, and in accordance 
with, European Aviation Safety Agency (EASA) AD 2018-0148R1, dated 
April 5, 2019 (``EASA AD 2018-0148R1'').

(h) Exceptions to EASA AD 2018-0148R1

    (1) For purposes of determining compliance with the requirements of 
this AD: Where EASA AD 2018-0148R1 refers to its effective date, or 
July 27, 2018 (the effective date of EASA AD 2018-0148, dated July 13, 
2018), this AD requires using the effective date of this AD.
    (2) The ``Remarks'' section of EASA AD 2018-0148R1 does not apply 
to this AD.

(i) No Reporting Requirement

    Although the service information referenced in EASA AD 2018-0148R1 
specifies to submit certain information to the manufacturer, this AD 
does not include that requirement.

(j) 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 (k)(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 instructions from a manufacturer, the instructions must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or 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): For any service information 
referenced in EASA AD 2018-0148R1 that contains RC procedures and 
tests: Except as required by paragraph (j)(2) of this AD, RC procedures 
and tests must be done to comply with this AD; any procedures or tests 
that are not identified as RC are recommended. Those procedures and 
tests that are not identified as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the procedures 
and tests identified as RC can be done and the airplane can be put back 
in an airworthy condition. Any substitutions or changes to procedures 
or tests identified as RC require approval of an AMOC.

(k) Related Information

    (1) For information about EASA AD 2018-0148R1, contact the EASA, 
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 89990 
6017; email [email protected]; Internet www.easa.europa.eu. You may 
find this EASA AD on the EASA website at https://ad.easa.europa.eu. You 
may view this EASA AD 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. EASA AD 2018-0148R1 may be 
found in the AD docket on the internet at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2019-0485.
    (2) For more information about this AD, contact Vladimir Ulyanov, 
Aerospace Engineer, International Section, Transport Standards Branch, 
FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-
231-3229.

    Issued in Des Moines, Washington, on June 18, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-13421 Filed 6-25-19; 8:45 am]
 BILLING CODE 4910-13-P
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