Airworthiness Directives; Airbus Airplanes, 23160-23163 [2017-10138]

Download as PDF 23160 Federal Register / Vol. 82, No. 97 / Monday, May 22, 2017 / Proposed Rules (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Replacement Within 6 months after the effective date of this AD: Replace any circuit breaker having part number (P/N) MS3320–10 installed at position 2LJ (L25) and position 4LJ (L26) with a circuit breaker having P/N MS3320– 7–5, in accordance with the Accomplishment Instructions of Saab Service Bulletin 340–33– 058, Revision 01, dated October 21, 2016. (h) Parts Installation Prohibition As of the effective date of this AD, no person may install a circuit breaker P/N MS3320–10 on any passenger reading light system at position at 2LJ (L25) and position 4LJ (L26), on any airplane. (i) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Saab Service Bulletin 340–33–058, dated May 30, 2016. nlaroche on DSK30NT082PROD with PROPOSALS (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Branch, send it to the attention of the person identified in paragraph (k)(2) of this AD. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Saab AB, Saab Aeronautics’ EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2016–0234, dated November 24, 2016, 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–2017–0479. (2) For more information about this AD, contact Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM–116, VerDate Sep<11>2014 12:41 May 19, 2017 Jkt 241001 Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1112; fax 425–227–1149. (3) For service information identified in this AD, contact Saab AB, Saab Aeronautics, ¨ SE–581 88, Linkoping, Sweden; telephone +46 13 18 5591; fax +46 13 18 4874; email saab340techsupport@saabgroup.com; Internet https://www.saabgroup.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on May 12, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–10139 Filed 5–19–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0478; Directorate Identifier 2016–NM–174–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A319 series airplanes; Model A320–211, –212, –214, –231, –232, and –233, airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. This proposed AD was prompted by a report of cracks on frame forks and outer skin on the forward and aft cargo compartment doors. This proposed AD would require repetitive inspections of the frame forks, and corrective actions if necessary. This proposed AD would also include optional modifications that constitute terminating action. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by July 6, 2017. 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– SUMMARY: PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 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 service information identified in this NPRM, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: account.airworth-eas@airbus.com; Internet: https://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. 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–2017– 0478; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–227–1405; fax: 425–227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2017–0478; Directorate Identifier 2016–NM–174–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each E:\FR\FM\22MYP1.SGM 22MYP1 23161 Federal Register / Vol. 82, No. 97 / Monday, May 22, 2017 / Proposed Rules substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2016–0187, dated September 19, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A319 series airplanes; Model A320–211, –212, –214, –231, –232, and –233, airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. The MCAI states: During full scale fatigue test, cracks have been found on frame forks and outer skin on forward and aft cargo doors. To improve the fatigue behaviour of the frame forks, Airbus introduced modification (mod) 22948 in production, and issued inspection Service Bulletin (SB) A320–52– 1032 and modification SB A320–52–1042, both recommended. Since those actions were taken, further improved cargo compartment doors have been introduced in production through Airbus mod 26213, on aeroplanes having MSN 0759 and up. This modification, which is not available for in-service retrofit, also includes provisions that exclude installation of pre-mod 26213 aft and forward compartment cargo doors on an aeroplane. In the frame of the Widespread Fatigue Damage (WFD) study, it has been determined that repetitive inspections are necessary for aft and forward cargo compartment doors on aeroplanes that do not (or no longer) embody mod 22948 (or SB A320–52–1042), and those that do not embody mod 26213. Failure to detect cracks would reduce the cargo door structural integrity. This condition, if not detected and corrected, could lead to cargo door failure, possibly resulting in decompression of the aeroplane and injury to occupants. To address this unsafe condition, Airbus issued SB A320–52–1171 to provide inspection instructions. This SB was later revised to correct the list of affected cargo doors. Airbus also issued SB A320–52–1170, introducing a door modification which constitutes terminating action for the repetitive special detailed inspection (SDI). For the reason described above, this [EASA] AD requires accomplishment of repetitive SDI by rototest of all frame forks in beam 4 area to detect cracks, and, depending on findings, accomplishment of applicable corrective action(s) [repair or replacement]. This AD also provides an optional [modification that constitutes] terminating action for the repetitive SDI required by this [EASA] AD. One of the optional modifications includes related investigative and corrective actions. The related investigative action is a high frequency eddy current (HFEC) rotating probe inspection for cracks, and the corrective action is a repair. 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–2017–0478. Related Service Information Under 1 CFR Part 51 We reviewed the following Airbus service information. • Airbus Service Bulletin A320–52– 1171, Revision 01, dated September 5, 2016, describes procedures for repetitive special detailed inspections of all frame forks in the beam 4 area of any affected door, and corrective actions. • Airbus Service Bulletin A320–52– 1042, Revision 2, dated January 14, 1997, describes procedures for modification of all affected forward and aft cargo compartment doors of an airplane. • Airbus Service Bulletin A320–52– 1170, dated September 5, 2016, describes modification of all affected forward and aft cargo compartment doors of an airplane, including related investigative and corrective actions. 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. 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 our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Difference Between This Proposed AD and the MCAI or Service Information Note 2 of the MCAI specifies to refer to Airbus A318/A319/A320/A321 Airworthiness Limitations Section (ALS) Part 1—Safe Life Airworthiness Limitation Items, Section 1, Chapter 5.2 (traceability). However, that document refers to an Airbus document to which we do not have access, and therefore we have not included a reference to Airbus A318/A319/A320/A321 ALS Part 1— Safe Life Airworthiness Limitation Items, Section 1, Chapter 5.2 (traceability) in this proposed AD. Costs of Compliance We estimate that this proposed AD affects 88 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Special detailed inspection ............................. 25 work-hours × $85 per hour = $2,125 ........ Cost per product Parts cost $0 $2,125 Cost on U.S. operators $187,000 OPTIONAL ACTIONS Labor cost Parts cost Modification .................................... nlaroche on DSK30NT082PROD with PROPOSALS Action 24 work-hours × $85 per hour = $2,040. Up to $240 .................................... We have received no definitive data that would enable us to provide cost estimates for the on-condition repairs and replacements specified in this proposed AD. VerDate Sep<11>2014 12:41 May 19, 2017 Jkt 241001 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 PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 Cost per product Up to $2,280. the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. E:\FR\FM\22MYP1.SGM 22MYP1 23162 Federal Register / Vol. 82, No. 97 / Monday, May 22, 2017 / Proposed Rules We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this 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. 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. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A319– 111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–211, –212, –214, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes, certificated in any category, manufacturer serial numbers through 0758 inclusive. (d) Subject Air Transport Association (ATA) of America Code 52, Doors. (e) Reason This AD was prompted by a report of cracks on the frame forks and outer skin on the forward and aft cargo compartment doors. We are issuing this AD to detect and correct cracks on the frame forks and outer skin on the forward and aft cargo compartment doors, which could lead to reduced structural integrity and failure of the cargo compartment door, possible decompression of the airplane, and injury to occupants. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definition of Affected Door For the purpose of this AD, an ‘‘affected door’’ is a forward or aft cargo compartment door, having any part number listed in table 1 to paragraph (g) of this AD, except a cargo compartment door on which Airbus Service Bulletin A320–52–1042 or Airbus Service Bulletin A320–52–1170 is embodied. TABLE 1 TO PARAGRAPH (g) OF THIS AD—AFFECTED PART NUMBERS Forward cargo compartment door part Nos. Aft cargo compartment door part Nos. D52371000000 D52371000002 D52371000004 D52371000006 D52371000008 D52371000010 D52371000012 D52371000014 D52371000016 D52371000018 D52371000022 D52371900000 D52371900002 D52371900004 D52371900008 D52371900010 D52371900012 D52371900014 D52371900016 D52371900018 D52371900022 ............................ 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 1. The authority citation for part 39 continues to read as follows: ■ nlaroche on DSK30NT082PROD with PROPOSALS 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): ■ Airbus: Docket No. FAA–2017–0478; Directorate Identifier 2016–NM–174–AD. (a) Comments Due Date We must receive comments by July 6, 2017. VerDate Sep<11>2014 12:41 May 19, 2017 Jkt 241001 (h) Repetitive Special Detailed Inspection of Frame Forks At the latest of the compliance times listed in paragraphs (h)(1) through (h)(4) of this AD: Do a special detailed inspection of all frame forks in the beam 4 area of any affected door as defined in paragraph (g) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 52–1171, Revision 01, dated September 5, 2016 (‘‘SB A320–52–1171 R01’’), except as specified in paragraphs (k) and (l) of this AD. Repeat the inspection thereafter at intervals not to exceed 3,000 flight cycles. A review of PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 the airplane delivery or maintenance records is acceptable to identify any affected door installed on the airplane, provided that the cargo compartment door part number can be conclusively determined from that review. (1) Before exceeding 37,500 flight cycles since first installation of the door on an airplane. (2) Within 900 flight cycles after the effective date of this AD, without exceeding 41,950 flight cycles since first installation of the door on an airplane. (3) Within 50 flight cycles after the effective date of this AD, for a door having reached or exceeded 41,900 flight cycles since first installation on an airplane. (4) Within 3,000 flight cycles since the last inspection of the door as specified in Airbus Service Bulletin A320–52–1032. (i) Corrective Actions If any crack is found during any inspection required by paragraph (h) of this AD, before further flight, do all applicable corrective actions in accordance with the Accomplishment Instructions of SB A320– 52–1171 R01, except as specified in paragraphs (k) and (l) of this AD. Accomplishment of applicable corrective actions does not constitute terminating action for the repetitive inspections. (j) Optional Terminating Action (1) Modification of all affected doors of an airplane in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–52–1042, Revision 2, dated January 14, 1997, constitutes terminating action for the repetitive inspections specified in paragraph (h) of this AD for that airplane, provided that, after modification, no affected door is re-installed on that airplane. (2) Modification of all affected doors of an airplane including accomplishment of all applicable related investigative and corrective actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–52–1170, dated September 5, 2016, except as specified in paragraphs (k) and (l) of this AD, constitutes terminating action for the repetitive inspections specified in paragraph (h) of this AD for that airplane, provided that, after modification, no affected door is re-installed on that airplane. (3) Modification of all affected doors on an airplane, in case of finding damaged frame forks, as specified in an Airbus Repair Design Approval Sheet (RDAS), and done in accordance with a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA); constitutes terminating action for the repetitive inspection specified in paragraph (h) of this AD for that airplane, provided that, after modification, no affected door is re-installed on that airplane. (k) Exception to Service Information Where SB A320–52–1171 R01 specifies to contact Airbus for appropriate action, and specifies that action as ‘‘RC’’ (Required for Compliance): Before further flight, accomplish corrective actions in accordance E:\FR\FM\22MYP1.SGM 22MYP1 Federal Register / Vol. 82, No. 97 / Monday, May 22, 2017 / Proposed Rules with the procedures specified in paragraph (o)(2) of this AD. (l) No Reporting Requirement Although SB A320–52–1171 R01 specifies to submit certain information to the manufacturer, and specifies that action as ‘‘RC’’ (Required for Compliance), this AD does not include that requirement. (m) Credit for Previous Actions This paragraph provides credit for the actions required by paragraphs (h) and (i) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–52–1171, dated October 29, 2015, provided that it can be conclusively determined that any part number D52371000018 was also inspected as specified in paragraph (h) of this AD. nlaroche on DSK30NT082PROD with PROPOSALS (n) Parts Installation Limitation As of the effective date of this AD, no person may install, on any airplane, an affected door specified in paragraph (g) of this AD, unless it has been inspected in accordance with the requirements of paragraph (h) of this AD and all applicable corrective actions have been done in accordance with paragraph (i) of this AD. (o) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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 manager of the International Branch, send it to the attention of the person identified in paragraph (p)(2) of this AD. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as specified in paragraphs (k) and (l) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an VerDate Sep<11>2014 12:41 May 19, 2017 Jkt 241001 airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016–0187, dated September 19, 2016, 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–2017–0478. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–227–1405; fax: 425–227– 1149. (3) For service information identified in this AD, contact Airbus, Airworthiness— EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on May 12, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–10138 Filed 5–19–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0475; Directorate Identifier 2016–NM–142–AD] RIN 2120–AA64 Airworthiness Directives; Dassault Aviation Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 2000 and FALCON 2000EX airplanes. This proposed AD was prompted by reports of ice accretion on the airplane wing due to the failure of certain anti-ice piccolo tubes in the wing outboard slats. This proposed AD would require repetitive inspections of each anti-ice piccolo tube and corrective action if necessary. This proposed AD also provides an optional terminating action for the repetitive inspections. We are SUMMARY: PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 23163 proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by July 6, 2017. 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 service information identified in this NPRM, contact Dassault Falcon Jet Corporation, Teterboro Airport, P.O. Box 2000, South Hackensack, NJ 07606; telephone 201–440–6700; Internet https://www.dassaultfalcon.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. 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–2017– 0475; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1137; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2017–0475; Directorate Identifier 2016–NM–142–AD’’ at the beginning of E:\FR\FM\22MYP1.SGM 22MYP1

Agencies

[Federal Register Volume 82, Number 97 (Monday, May 22, 2017)]
[Proposed Rules]
[Pages 23160-23163]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10138]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0478; Directorate Identifier 2016-NM-174-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Airbus Model A319 series airplanes; Model A320-211, -212, -214, 
-231, -232, and -233, airplanes; and Model A321-111, -112, -131, -211, 
-212, -213, -231, and -232 airplanes. This proposed AD was prompted by 
a report of cracks on frame forks and outer skin on the forward and aft 
cargo compartment doors. This proposed AD would require repetitive 
inspections of the frame forks, and corrective actions if necessary. 
This proposed AD would also include optional modifications that 
constitute terminating action. We are proposing this AD to address the 
unsafe condition on these products.

DATES: We must receive comments on this proposed AD by July 6, 2017.

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 service information identified in this NPRM, contact Airbus, 
Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 
44 51; email: account.airworth-eas@airbus.com; Internet: https://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

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-2017-
0478; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

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

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0478; 
Directorate Identifier 2016-NM-174-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each

[[Page 23161]]

substantive verbal contact we receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2016-0187, dated September 19, 2016 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Airbus Model A319 series 
airplanes; Model A320-211, -212, -214, -231, -232, and -233, airplanes; 
and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes. The MCAI states:

    During full scale fatigue test, cracks have been found on frame 
forks and outer skin on forward and aft cargo doors.
    To improve the fatigue behaviour of the frame forks, Airbus 
introduced modification (mod) 22948 in production, and issued 
inspection Service Bulletin (SB) A320-52-1032 and modification SB 
A320-52-1042, both recommended.
    Since those actions were taken, further improved cargo 
compartment doors have been introduced in production through Airbus 
mod 26213, on aeroplanes having MSN 0759 and up. This modification, 
which is not available for in-service retrofit, also includes 
provisions that exclude installation of pre-mod 26213 aft and 
forward compartment cargo doors on an aeroplane.
    In the frame of the Widespread Fatigue Damage (WFD) study, it 
has been determined that repetitive inspections are necessary for 
aft and forward cargo compartment doors on aeroplanes that do not 
(or no longer) embody mod 22948 (or SB A320-52-1042), and those that 
do not embody mod 26213. Failure to detect cracks would reduce the 
cargo door structural integrity.
    This condition, if not detected and corrected, could lead to 
cargo door failure, possibly resulting in decompression of the 
aeroplane and injury to occupants.
    To address this unsafe condition, Airbus issued SB A320-52-1171 
to provide inspection instructions. This SB was later revised to 
correct the list of affected cargo doors. Airbus also issued SB 
A320-52-1170, introducing a door modification which constitutes 
terminating action for the repetitive special detailed inspection 
(SDI).
    For the reason described above, this [EASA] AD requires 
accomplishment of repetitive SDI by rototest of all frame forks in 
beam 4 area to detect cracks, and, depending on findings, 
accomplishment of applicable corrective action(s) [repair or 
replacement]. This AD also provides an optional [modification that 
constitutes] terminating action for the repetitive SDI required by 
this [EASA] AD.

    One of the optional modifications includes related investigative 
and corrective actions. The related investigative action is a high 
frequency eddy current (HFEC) rotating probe inspection for cracks, and 
the corrective action is a repair. 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-2017-0478.

Related Service Information Under 1 CFR Part 51

    We reviewed the following Airbus service information.
     Airbus Service Bulletin A320-52-1171, Revision 01, dated 
September 5, 2016, describes procedures for repetitive special detailed 
inspections of all frame forks in the beam 4 area of any affected door, 
and corrective actions.
     Airbus Service Bulletin A320-52-1042, Revision 2, dated 
January 14, 1997, describes procedures for modification of all affected 
forward and aft cargo compartment doors of an airplane.
     Airbus Service Bulletin A320-52-1170, dated September 5, 
2016, describes modification of all affected forward and aft cargo 
compartment doors of an airplane, including related investigative and 
corrective actions.
    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.

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 our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Difference Between This Proposed AD and the MCAI or Service Information

    Note 2 of the MCAI specifies to refer to Airbus A318/A319/A320/A321 
Airworthiness Limitations Section (ALS) Part 1--Safe Life Airworthiness 
Limitation Items, Section 1, Chapter 5.2 (traceability). However, that 
document refers to an Airbus document to which we do not have access, 
and therefore we have not included a reference to Airbus A318/A319/
A320/A321 ALS Part 1--Safe Life Airworthiness Limitation Items, Section 
1, Chapter 5.2 (traceability) in this proposed AD.

Costs of Compliance

    We estimate that this proposed AD affects 88 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Special detailed inspection...........  25 work-hours x $85 per               $0          $2,125        $187,000
                                         hour = $2,125.
----------------------------------------------------------------------------------------------------------------


                                                Optional Actions
----------------------------------------------------------------------------------------------------------------
                Action                        Labor cost               Parts cost            Cost per product
----------------------------------------------------------------------------------------------------------------
Modification.........................  24 work-hours x $85 per  Up to $240.............  Up to $2,280.
                                        hour = $2,040.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition repairs and replacements specified 
in this proposed AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.

[[Page 23162]]

    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this 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. 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.

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: Docket No. FAA-2017-0478; Directorate Identifier 2016-NM-
174-AD.

(a) Comments Due Date

    We must receive comments by July 6, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A319-111, -112, -113, -114, -
115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -
231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, 
-212, -213, -231, and -232 airplanes, certificated in any category, 
manufacturer serial numbers through 0758 inclusive.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of cracks on the frame forks 
and outer skin on the forward and aft cargo compartment doors. We 
are issuing this AD to detect and correct cracks on the frame forks 
and outer skin on the forward and aft cargo compartment doors, which 
could lead to reduced structural integrity and failure of the cargo 
compartment door, possible decompression of the airplane, and injury 
to occupants.

(f) Compliance

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

(g) Definition of Affected Door

    For the purpose of this AD, an ``affected door'' is a forward or 
aft cargo compartment door, having any part number listed in table 1 
to paragraph (g) of this AD, except a cargo compartment door on 
which Airbus Service Bulletin A320-52-1042 or Airbus Service 
Bulletin A320-52-1170 is embodied.

       Table 1 to Paragraph (g) of This AD--Affected Part Numbers
------------------------------------------------------------------------
                                                           Aft cargo
       Forward cargo compartment door part Nos.         compartment door
                                                           part Nos.
------------------------------------------------------------------------
D52371000000.........................................      D52371900000
D52371000002.........................................      D52371900002
D52371000004.........................................      D52371900004
D52371000006.........................................      D52371900008
D52371000008.........................................      D52371900010
D52371000010.........................................      D52371900012
D52371000012.........................................      D52371900014
D52371000014.........................................      D52371900016
D52371000016.........................................      D52371900018
D52371000018.........................................      D52371900022
D52371000022.........................................  .................
------------------------------------------------------------------------

(h) Repetitive Special Detailed Inspection of Frame Forks

    At the latest of the compliance times listed in paragraphs 
(h)(1) through (h)(4) of this AD: Do a special detailed inspection 
of all frame forks in the beam 4 area of any affected door as 
defined in paragraph (g) of this AD, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-52-1171, 
Revision 01, dated September 5, 2016 (``SB A320-52-1171 R01''), 
except as specified in paragraphs (k) and (l) of this AD. Repeat the 
inspection thereafter at intervals not to exceed 3,000 flight 
cycles. A review of the airplane delivery or maintenance records is 
acceptable to identify any affected door installed on the airplane, 
provided that the cargo compartment door part number can be 
conclusively determined from that review.
    (1) Before exceeding 37,500 flight cycles since first 
installation of the door on an airplane.
    (2) Within 900 flight cycles after the effective date of this 
AD, without exceeding 41,950 flight cycles since first installation 
of the door on an airplane.
    (3) Within 50 flight cycles after the effective date of this AD, 
for a door having reached or exceeded 41,900 flight cycles since 
first installation on an airplane.
    (4) Within 3,000 flight cycles since the last inspection of the 
door as specified in Airbus Service Bulletin A320-52-1032.

(i) Corrective Actions

    If any crack is found during any inspection required by 
paragraph (h) of this AD, before further flight, do all applicable 
corrective actions in accordance with the Accomplishment 
Instructions of SB A320-52-1171 R01, except as specified in 
paragraphs (k) and (l) of this AD. Accomplishment of applicable 
corrective actions does not constitute terminating action for the 
repetitive inspections.

(j) Optional Terminating Action

    (1) Modification of all affected doors of an airplane in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-52-1042, Revision 2, dated January 14, 1997, 
constitutes terminating action for the repetitive inspections 
specified in paragraph (h) of this AD for that airplane, provided 
that, after modification, no affected door is re-installed on that 
airplane.
    (2) Modification of all affected doors of an airplane including 
accomplishment of all applicable related investigative and 
corrective actions in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-52-1170, dated 
September 5, 2016, except as specified in paragraphs (k) and (l) of 
this AD, constitutes terminating action for the repetitive 
inspections specified in paragraph (h) of this AD for that airplane, 
provided that, after modification, no affected door is re-installed 
on that airplane.
    (3) Modification of all affected doors on an airplane, in case 
of finding damaged frame forks, as specified in an Airbus Repair 
Design Approval Sheet (RDAS), and done in accordance with a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the European Aviation Safety Agency 
(EASA); or Airbus's EASA Design Organization Approval (DOA); 
constitutes terminating action for the repetitive inspection 
specified in paragraph (h) of this AD for that airplane, provided 
that, after modification, no affected door is re-installed on that 
airplane.

(k) Exception to Service Information

    Where SB A320-52-1171 R01 specifies to contact Airbus for 
appropriate action, and specifies that action as ``RC'' (Required 
for Compliance): Before further flight, accomplish corrective 
actions in accordance

[[Page 23163]]

with the procedures specified in paragraph (o)(2) of this AD.

(l) No Reporting Requirement

    Although SB A320-52-1171 R01 specifies to submit certain 
information to the manufacturer, and specifies that action as ``RC'' 
(Required for Compliance), this AD does not include that 
requirement.

(m) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraphs (h) and (i) of this AD, if those actions were performed 
before the effective date of this AD using Airbus Service Bulletin 
A320-52-1171, dated October 29, 2015, provided that it can be 
conclusively determined that any part number D52371000018 was also 
inspected as specified in paragraph (h) of this AD.

(n) Parts Installation Limitation

    As of the effective date of this AD, no person may install, on 
any airplane, an affected door specified in paragraph (g) of this 
AD, unless it has been inspected in accordance with the requirements 
of paragraph (h) of this AD and all applicable corrective actions 
have been done in accordance with paragraph (i) of this AD.

(o) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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 manager of the 
International Branch, send it to the attention of the person 
identified in paragraph (p)(2) of this AD. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or 
Airbus's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as specified in 
paragraphs (k) and (l) of this AD: If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0187, dated September 19, 2016, 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-2017-0478.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone: 425-227-1405; fax: 425-227-1149.
    (3) For service information identified in this AD, contact 
Airbus, Airworthiness--EIAS, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 
44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.

    Issued in Renton, Washington, on May 12, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-10138 Filed 5-19-17; 8:45 am]
BILLING CODE 4910-13-P
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