Airworthiness Directives; Airbus Airplanes, 59530-59532 [2016-20685]

Download as PDF 59530 Federal Register / Vol. 81, No. 168 / Tuesday, August 30, 2016 / Proposed Rules Revision 01, dated March 31, 2014: Within 6,600 flight hours after the effective date of this AD, do a general visual inspection for tube misalignment on the pitot number 1 and pitot number 2 tube assemblies; do all applicable corrective actions; and install a new tube ribbon heater on the pitot number 1 and pitot number 2 tube assemblies; in accordance with the Accomplishment Instructions of Embraer Service Bulletin 145– 30–0056, Revision 01, dated March 31, 2014. Do all applicable corrective actions before further flight. (2) For airplanes identified as Group 1 in Embraer Service Bulletin 145LEG–30–0021, dated March 31, 2014: Within 5,000 flight hours or 48 months after the effective date of this AD, whichever occurs first, do a general visual inspection for tube misalignment on the pitot number 1 and pitot number 2 tube assemblies; do all applicable corrective actions; and install a new tube ribbon heater on the pitot number 1 and pitot number 2 tube assemblies; in accordance with the Accomplishment Instructions of Embraer Service Bulletin 145LEG–30–0021, dated March 31, 2014. Do all applicable corrective actions before further flight. mstockstill on DSK3G9T082PROD with PROPOSALS (h) Inspection, Corrective Action, and Replacement (1) For airplanes identified as Group 2 in Embraer Service Bulletin 145–30–0056, Revision 01, dated March 31, 2014: Within 6,600 flight hours after the effective date of this AD, do a general visual inspection for tube misalignment on the pitot number 1 and pitot number 2 tube assemblies; do all applicable corrective actions; and replace the tube ribbon heater with a new tube ribbon heater on the pitot number 1 and pitot number 2 tube assemblies; in accordance with the Accomplishment Instructions of Embraer Service Bulletin 145–30–0056, Revision 01, dated March 31, 2014. Do all applicable corrective actions before further flight. (2) For airplanes identified as Group 2 in Embraer Service Bulletin 145LEG–30–0021, dated March 31, 2014: Within 5,000 flight hours or 48 months after the effective date of this AD, whichever occurs first, do a general visual inspection for tube misalignment on the pitot number 1 and pitot number 2 tube assemblies; do all applicable corrective actions; and replace the tube ribbon heater with a new tube ribbon heater on the pitot number 1 and pitot number 2 tube assemblies; in accordance with the Accomplishment Instructions of Embraer Service Bulletin 145LEG–30–0021, dated March 31, 2014. Do all applicable corrective actions before further flight. (i) Airplane Flight Manual (AFM) Revision (1) For airplanes identified in paragraphs (c)(1) and (c)(3) of this AD: Within 60 days after the effective date of this AD, revise the AFM to include the information in the ‘‘Unreliable Airspeed Procedure’’ in the Emergency/Abnormal Procedures section and the ‘‘Unreliable Airspeed Tables’’ (corresponding to the airplane configuration) in the Performance section, as specified in Embraer Temporary Revision (TR) 40.2, dated April 4, 2014, to Volume 1, of the VerDate Sep<11>2014 17:56 Aug 29, 2016 Jkt 238001 Embraer EMB–145 Aircraft Operations Manual (AOM) AOM–145/1114 (‘‘Embraer TR 40.2’’). (2) For airplanes identified in paragraphs (c)(2) and (c)(4) of this AD: Within 60 days after the effective date of this AD, revise the AFM to include the information in the ‘‘Unreliable Airspeed Procedure’’ in the Emergency/Abnormal Procedures section and the ‘‘Unreliable Airspeed Tables’’ (corresponding to the airplane configuration) in the Performance section, as specified in Embraer TR 19.1, dated April 22, 2014, to Volume 1 of the Embraer EMB–145 AOM AOM–2014135/1542 (‘‘Embraer TR 19.1’’). (j) AFM Revision Method of Compliance The AFM revisions required by paragraphs (i)(1) and (i)(2) of this AD may be done by inserting Embraer AOM TR 40.2 or Embraer AOM TR 19.1, as applicable, into the AFM. When the applicable Embraer AOM TR has been included in general revisions of the AFM, the general revisions may be inserted in the AFM, provided the relevant information in the general revision is identical to that in Embraer AOM TR 40.2 or Embraer AOM TR 19.1, as applicable, and the applicable Embraer AOM TR may be removed from the AFM. (k) Credit for Previous Actions This paragraph provides credit for the actions required by paragraphs (g)(1) and (h)(1) of this AD, if those actions were performed before the effective date of this AD using Embraer Service Bulletin 145–30–0056, dated December 19, 2013. (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1175; fax 425–227–1149. 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. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or ˆ the Agencia Nacional de Aviacao Civil ¸˜ (ANAC); or ANAC’s authorized Designee. If approved by the ANAC Designee, the approval must include the Designee’s authorized signature. PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Brazilian Airworthiness Directive 2016–03–01, effective March 11, 2016, for related information. This MCAI may be found in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016–9049. (2) For service information identified in this AD, contact Empresa Brasileira de Aeronautica S.A. (Embraer), Technical Publications Section (PC 060), Av. Brigadeiro ˜ Faria Lima, 2170—Putim—12227–901 Sao Jose dos Campos—SP—Brasil; telephone +55 12 3927–5852 or +55 12 3309–0732; fax +55 12 3927–7546; email distrib@embraer.com.br; Internet http://www.flyembraer.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 August 18, 2016. Dorr M. Anderson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–20684 Filed 8–29–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9051; Directorate Identifier 2016–NM–035–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 all Airbus Model A300 B4–603, B4–620, and B4–622 airplanes; Model A300 B4– 605R and A300 B4–622R airplanes; and Model A300 C4–605R Variant F airplanes. This proposed AD was prompted by an in-service detection of cracks in the fuselage skin lap joints. This proposed AD would require an ultrasonic inspection of certain skin lap joints, and repair if necessary. We are proposing this AD to detect and correct cracks in certain skin lap joints. Such cracking could result in reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by October 14, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR SUMMARY: E:\FR\FM\30AUP1.SGM 30AUP1 Federal Register / Vol. 81, No. 168 / Tuesday, August 30, 2016 / Proposed Rules 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://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 SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9051; 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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149; email dan.rodina@ faa.gov. 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–2016–9051; Directorate Identifier 2016–NM–035–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 http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each 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 Airworthiness Directive 2016–0557, dated March 18, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A300 B4–603, B4–620, and B4– 622 airplanes; Model A300 B4–605R and A300 B4–622R airplanes; and Model A300 C4–605R Variant F airplanes. The MCAI states: Prompted by in-service detection on Airbus A300–600 aeroplanes of cracks in certain fuselage skin lap joints, several studies were launched to understand the phenomenon and provide the corrective actions. More recently, new analyses were performed and the results identified that a new area has to be inspected at the skin lap joint below Stringer (STR) 28 at Frame (FR) 72 to FR 76. This condition, if not detected and corrected, could result in reduced structure integrity of the aeroplane. 59531 To address this unsafe condition, Airbus published Service Bulletin (SB) A300–53– 6184 [dated November 12, 2015] to introduce inspections and applicable corrective actions for the affected areas. For the reason described above, this [EASA] AD requires repetitive Special Detail Inspections (SDI) of the affected skin lap joint and, depending on findings, accomplishment of applicable corrective action(s) [repairs]. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9051. Related Service Information Under 1 CFR Part 51 We reviewed Airbus Service Bulletin A300–53–6184, November 12, 2015. The service information describes procedures for an ultrasonic inspection of the skin lap joint below stringer 28 at FR 72 to FR 76, and repair if necessary. 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. Costs of Compliance We estimate that this proposed AD affects 29 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Labor cost Cost per product Ultrasonic inspection ...................... mstockstill on DSK3G9T082PROD with PROPOSALS Action 6 work-hours × $85 per hour = $510 per inspection cycle. $510 per inspection cycle ............. We have no way to determine the costs to do any necessary repairs that would be required based on the results of the proposed inspection. We have no way of determining the number of airplanes that might need these repairs. VerDate Sep<11>2014 17:56 Aug 29, 2016 Jkt 238001 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 00014 Fmt 4702 Sfmt 4702 Cost on U.S. operators $14,790 per inspection cycle. the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, E:\FR\FM\30AUP1.SGM 30AUP1 59532 Federal Register / Vol. 81, No. 168 / Tuesday, August 30, 2016 / Proposed Rules 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. mstockstill on DSK3G9T082PROD with PROPOSALS § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2016–9051; Directorate Identifier 2016–NM–035–AD. (a) Comments Due Date We must receive comments by October 14, 2016. VerDate Sep<11>2014 17:56 Aug 29, 2016 Jkt 238001 (b) Affected ADs None. (c) Applicability This AD applies to all Airbus Model A300 B4–603, B4–620, and B4–622 airplanes; Model A300 B4–605R and A300 B4–622R airplanes; and Model A300 C4–605R Variant F airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by an in-service detection of cracks in the fuselage skin lap joints. We are issuing this AD to detect and correct cracks in the skin lap joint below stringer 28 at frame (FR) 72 to FR 76. Such cracking could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections Before 29,500 flight cycles since the first flight of the airplane or within 2,000 flight cycles after the effective date of this AD, whichever occurs later, do an ultrasonic inspection for cracks of the skin lap joint below stringer 28 at FR 72 to FR 76 and do all applicable repairs before further flight, in accordance with the Accomplishment Instruction of Airbus Service Bulletin A300– 53–6184, November 12, 2015, except as required by paragraph (h) of this AD. Repeat the ultrasonic inspection thereafter at intervals not to exceed 5,400 flight cycles. (h) Exceptions to Service Information Specified Paragraph (g) of This AD Where Airbus Service Bulletin A300–53– 6184, November 12, 2015, specifies to contact Airbus for repair instructions, and specifies that action as ‘‘RC’’ (Required for Compliance), this AD requires repair before further flight using a method approved in accordance with the procedures specified in paragraph (i) of this AD. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Brach, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149; email dan.rodina@faa.gov. 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 PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (h) 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. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016–0557, dated March 18, 2016, for related information. This MCAI may be found in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016–9051. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http://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 August 19, 2016. Dorr M. Anderson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–20685 Filed 8–29–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9050; Directorate Identifier 2016–NM–086–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: E:\FR\FM\30AUP1.SGM 30AUP1

Agencies

[Federal Register Volume 81, Number 168 (Tuesday, August 30, 2016)]
[Proposed Rules]
[Pages 59530-59532]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-20685]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9051; Directorate Identifier 2016-NM-035-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 all 
Airbus Model A300 B4-603, B4-620, and B4-622 airplanes; Model A300 B4-
605R and A300 B4-622R airplanes; and Model A300 C4-605R Variant F 
airplanes. This proposed AD was prompted by an in-service detection of 
cracks in the fuselage skin lap joints. This proposed AD would require 
an ultrasonic inspection of certain skin lap joints, and repair if 
necessary. We are proposing this AD to detect and correct cracks in 
certain skin lap joints. Such cracking could result in reduced 
structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by October 14, 
2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR

[[Page 59531]]

11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://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 
SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 
51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9051; 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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
fax 425-227-1149; email dan.rodina@faa.gov.

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-2016-9051; 
Directorate Identifier 2016-NM-035-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 http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each 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 
Airworthiness Directive 2016-0557, dated March 18, 2016 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model A300 
B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and A300 B4-
622R airplanes; and Model A300 C4-605R Variant F airplanes. The MCAI 
states:

    Prompted by in-service detection on Airbus A300-600 aeroplanes 
of cracks in certain fuselage skin lap joints, several studies were 
launched to understand the phenomenon and provide the corrective 
actions. More recently, new analyses were performed and the results 
identified that a new area has to be inspected at the skin lap joint 
below Stringer (STR) 28 at Frame (FR) 72 to FR 76.
    This condition, if not detected and corrected, could result in 
reduced structure integrity of the aeroplane.
    To address this unsafe condition, Airbus published Service 
Bulletin (SB) A300-53-6184 [dated November 12, 2015] to introduce 
inspections and applicable corrective actions for the affected 
areas.
    For the reason described above, this [EASA] AD requires 
repetitive Special Detail Inspections (SDI) of the affected skin lap 
joint and, depending on findings, accomplishment of applicable 
corrective action(s) [repairs].

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9051.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Service Bulletin A300-53-6184, November 12, 
2015. The service information describes procedures for an ultrasonic 
inspection of the skin lap joint below stringer 28 at FR 72 to FR 76, 
and repair if necessary. 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.

Costs of Compliance

    We estimate that this proposed AD affects 29 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                Action                        Labor cost            Cost per product      Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Ultrasonic inspection................  6 work-hours x $85 per   $510 per inspection      $14,790 per inspection
                                        hour = $510 per          cycle.                   cycle.
                                        inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have no way to determine the costs to do any necessary repairs 
that would be required based on the results of the proposed inspection. 
We have no way of determining the number of airplanes that might need 
these repairs.

Authority for This Rulemaking

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

[[Page 59532]]

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-2016-9051; Directorate Identifier 2016-NM-
035-AD.

(a) Comments Due Date

    We must receive comments by October 14, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus Model A300 B4-603, B4-620, and B4-
622 airplanes; Model A300 B4-605R and A300 B4-622R airplanes; and 
Model A300 C4-605R Variant F airplanes, certificated in any 
category.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by an in-service detection of cracks in the 
fuselage skin lap joints. We are issuing this AD to detect and 
correct cracks in the skin lap joint below stringer 28 at frame (FR) 
72 to FR 76. Such cracking could result in reduced structural 
integrity of the airplane.

(f) Compliance

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

(g) Repetitive Inspections

    Before 29,500 flight cycles since the first flight of the 
airplane or within 2,000 flight cycles after the effective date of 
this AD, whichever occurs later, do an ultrasonic inspection for 
cracks of the skin lap joint below stringer 28 at FR 72 to FR 76 and 
do all applicable repairs before further flight, in accordance with 
the Accomplishment Instruction of Airbus Service Bulletin A300-53-
6184, November 12, 2015, except as required by paragraph (h) of this 
AD. Repeat the ultrasonic inspection thereafter at intervals not to 
exceed 5,400 flight cycles.

(h) Exceptions to Service Information Specified Paragraph (g) of This 
AD

    Where Airbus Service Bulletin A300-53-6184, November 12, 2015, 
specifies to contact Airbus for repair instructions, and specifies 
that action as ``RC'' (Required for Compliance), this AD requires 
repair before further flight using a method approved in accordance 
with the procedures specified in paragraph (i) of this AD.

(i) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Brach, FAA, has the authority to approve AMOCs for 
this AD, if requested using the procedures found in 14 CFR 39.19. In 
accordance with 14 CFR 39.19, send your request to your principal 
inspector or local Flight Standards District Office, as appropriate. 
If sending information directly to the International Branch, send it 
to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM-
116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., 
Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149; 
email dan.rodina@faa.gov. 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. The AMOC approval letter must 
specifically reference this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; 
or Airbus's EASA Design Organization Approval (DOA). If approved by 
the DOA, the approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraph (h) 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.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0557, dated March 18, 2016, for related 
information. This MCAI may be found in the AD docket on the Internet 
at http://www.regulations.gov by searching for and locating Docket 
No. FAA-2016-9051.
    (2) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
Internet http://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 August 19, 2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-20685 Filed 8-29-16; 8:45 am]
 BILLING CODE 4910-13-P