Airworthiness Directives; Airbus Airplanes, 51818-51821 [2016-18486]

Download as PDF 51818 Federal Register / Vol. 81, No. 151 / Friday, August 5, 2016 / Proposed Rules certificated in any category, as identified in Embraer Service Bulletin 145LEG–28–0032, Revision 01, dated November 20, 2012. (d) Subject Air Transport Association (ATA) of America Code 28, Fuel. (e) Reason This AD was prompted by a report of chafing found between the fuel pump electrical harness and the fuel pump tubing during scheduled maintenance. We are issuing this AD to detect and correct chafing of the fuel pump harnesses with other parts inside the fuel tank, which could present a potential ignition source that could result in a fire or fuel tank explosion. (f) Compliance Comply with this AD within the compliance times specified, unless already done. mstockstill on DSK3G9T082PROD with PROPOSALS (g) Detailed Inspection and Corrective Action Do the actions specified in paragraphs (g)(1) and (g)(2) of this AD at the applicable times specified in paragraph (h)(1) or (h)(2) of this AD. (1) Do a detailed inspection for chafing on the electrical harness of each electrical fuel pump in the fuel tanks, in accordance with the Accomplishment Instructions of Embraer Service Bulletin 145–28–0030, Revision 01, dated October 22, 2010 (for Model EMB– 135ER, –135KE, –135KL, and –135LR airplanes; and Model EMB–145, –145ER, –145MR, –145LR, –145MP, –145EP, and –145XR airplanes); or Embraer Service Bulletin 145LEG–28–0032, Revision 01, dated November 20, 2012 (for Model EMB– 135BJ airplanes). If any chafing is found, before further flight, replace the affected electrical fuel pump with a new or serviceable pump having the same part number, in accordance with the Accomplishment Instructions of Embraer Service Bulletin 145–28–0030, Revision 01, dated October 22, 2010; or Embraer Service Bulletin 145LEG–28–0032, Revision 01, dated November 20, 2012; as applicable. (2) Install clamps on the fuel pump electrical harnesses, in accordance with the Accomplishment Instructions of Embraer Service Bulletin 145–28–0030, Revision 01, dated October 22, 2010 (for Model EMB– 135ER, –135KE, –135KL, and –135LR airplanes; and Model EMB–145, –145ER, –145MR, –145LR, –145MP, –145EP, and –145XR airplanes); or Embraer Service Bulletin 145LEG–28–0032, Revision 01, dated November 20, 2012 (for Model EMB– 135BJ airplanes). (h) Compliance Times (1) For Model EMB–135ER, –135KE, –135KL, and –135LR airplanes; and Model EMB–145, –145ER, –145MR, –145LR, –145MP, –145EP, and –145XR airplanes: Do the actions specified in paragraph (g) of this AD within 5,000 flight hours or 24 months after the effective date of this AD, whichever occurs first. (2) For Model EMB–135BJ airplanes: Do the actions specified in paragraph (g) of this AD within 4,800 flight hours or 48 months VerDate Sep<11>2014 16:15 Aug 04, 2016 Jkt 238001 after the effective date of this AD, whichever occurs first. (i) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Embraer Service Bulletin 145–28–0030, dated September 1, 2010 (for Model EMB–135ER, –135KE, –135KL, and –135LR airplanes; and Model EMB–145, –145ER, –145MR, –145LR, –145MP, –145EP, and –145XR airplanes); or Embraer Service Bulletin 145LEG–28–0032, dated September 15, 2011 (for Model EMB– 135BJ airplanes), as applicable. This service information is not incorporated by reference in this AD. (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 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. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Brazilian Airworthiness Directive 2015–03–01, effective March 23, 2015, for related information. This MCAI may be found in the AD docket on the Internet by searching for and locating Docket No. FAA–2015–3143. (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 PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 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 July 25, 2016. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–18500 Filed 8–4–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–8184; Directorate Identifier 2016–NM–036–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 series airplanes; and Airbus Model A300 B4–600, B4– 600R, and F4–600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes). This proposed AD was prompted by reports of cracks in certain pins in the main landing gear (MLG). This proposed AD would require repetitive detailed visual inspections of the pins for cracks, and replacing the MLG leg if necessary. We are proposing this AD to detect and correct cracking of certain pins in the MLG, which could result in a MLG collapse, and consequent damage to the airplane and injury to the airplane occupants. SUMMARY: We must receive comments on this proposed AD by September 19, 2016. DATES: 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 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 ADDRESSES: E:\FR\FM\05AUP1.SGM 05AUP1 51819 Federal Register / Vol. 81, No. 151 / Friday, August 5, 2016 / Proposed Rules 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 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– 8184; 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. 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–2016–8184; Directorate Identifier 2016–NM–036–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 AD 2016–0058, dated March 21, 2016, (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A300 series airplanes; and Airbus Model A300 B4–600, B4–600R, and F4–600R series airplanes, and Model A300 C4– 605R Variant F airplanes (collectively called Model A300–600 series airplanes). The MCAI states: Two cases were reported of finding a cracked main landing gear (MLG) hinge arm/ barrel pin, one was discovered in service during a maintenance task and the other one was identified during MLG overhaul. This condition, if not detected and corrected, could lead to MLG collapse, resulting in damage to the aeroplane and potential injury to occupants. To address this potential unsafe condition, and awaiting a final fix establishment, Airbus issued Alert Operators Transmission (AOT) 32W008–16 to provide instructions for detailed visual inspections (DET) to detect through cracks. For the reasons described above, this [EASA] AD requires repetitive DET of the MLG hinge arm/barrel pin and, depending on findings, replacement of the affected MLG leg. 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– 8184. Related Service Information Under 1 CFR Part 51 We reviewed Airbus Alert Operators Transmission (AOT) 32W008–16, dated February 25, 2016. This service information describes detailed visual inspection and replacement procedures for the MLG hinge arm and barrel pin. 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 128 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Detailed Visual Inspection Reporting ........................... 1 work-hour × $85 per hour = $85 per inspection cycle ..... 1 work-hour × $85 per hour ................................................. mstockstill on DSK3G9T082PROD with PROPOSALS We estimate the following costs to do any necessary replacement that would Parts cost be required based on the results of the proposed inspection. We have no way of 0 0 Cost per product $85 85 Cost on U.S. operators $10,880 per inspection cycle. $10,880. determining the number of airplanes that might need this replacement. ON-CONDITION COSTS Action Labor cost Parts cost Cost per product Remove and Replace MLG Leg ................................... 20 work-hours × $85 per hour = $1,700 ...................... $3,400,000 $3,401,700 VerDate Sep<11>2014 16:15 Aug 04, 2016 Jkt 238001 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 E:\FR\FM\05AUP1.SGM 05AUP1 51820 Federal Register / Vol. 81, No. 151 / Friday, August 5, 2016 / Proposed Rules Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this proposed AD is 2120– 0056. The paperwork cost associated with this proposed AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this proposed AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES–200. 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. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. mstockstill on DSK3G9T082PROD with PROPOSALS 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; VerDate Sep<11>2014 16:15 Aug 04, 2016 Jkt 238001 § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2016–8184; Directorate Identifier 2016–NM–036–AD. (a) Comments Due Date We must receive comments by September 9, 2016. (b) Affected ADs None. (c) Applicability This AD applies to Airbus airplanes identified in paragraphs (c)(1) through (c)(5) of this AD, certificated in any category, all manufacturer serial numbers. (1) Model A300 B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes. (2) Model A300 B4–601, B4–603, B4–620, and B4–622 airplanes. (3) Model A300 B4–605R and B4–622R airplanes. (4) Model A300 F4–605R and F4–622R airplanes. (5) Model A300 C4–605R Variant F airplanes. (d) Subject Air Transport Association (ATA) of America Code 32, Landing Gear. (e) Reason This AD was prompted by reports of cracks in certain pins in the main landing gear (MLG). We are issuing this AD to detect and correct cracking of certain pins in the MLG, which could result in a MLG collapse, and consequent damage to the airplane and injury to the airplane occupants. PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Detailed Visual Inspections Within the compliance time specified in paragraphs (g)(1) and (g)(2) of this AD, whichever occurs later, and thereafter at intervals not to exceed 100 flight cycles, accomplish a detailed visual inspection of the internal diameter of each affected MLG hinge arm/barrel pin, in accordance with the instructions of Airbus Alert Operators Transmission (AOT) A32W008–16, dated February 25, 2016. The affected MLG hinge arm/barrel pins are those with part number C66441–(x) and part number C65543–(x), where the x represents a variable number. (1) Within 30 months since the pin’s first flight on an airplane, or since the pin’s first flight on an airplane after overhaul, as applicable. (2) Within 30 days after the effective date of this AD. (h) Corrective Action for Detailed Visual Inspection If any crack is found during any inspection required by paragraph (g) of this AD, before further flight, replace the MLG leg with a serviceable unit, in accordance with the instructions of Airbus AOT A32W008–16, dated February 25, 2016. Replacement of a MLG leg does not constitute terminating action for the repetitive inspections required by paragraph (g) of this AD. (i) Reporting Requirement At the applicable time specified in paragraph (i)(1) or (i)(2) of this AD, report the results of the inspections required by paragraph (g) of this AD to Airbus in accordance with the instructions of Airbus AOT A32W008–16, dated February 25, 2016. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (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 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. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or E:\FR\FM\05AUP1.SGM 05AUP1 Federal Register / Vol. 81, No. 151 / Friday, August 5, 2016 / Proposed Rules 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 European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. (k) Related Information mstockstill on DSK3G9T082PROD with PROPOSALS (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2016–0058, dated March 21, 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– 2016–8184. (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 July 26, 2016. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–18486 Filed 8–4–16; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 16:15 Aug 04, 2016 Jkt 238001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–8183; Directorate Identifier 2015–NM–083–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2012–08– 11 for certain Bombardier, Inc. Model DHC–8–400 series airplanes. AD 2012– 08–11 currently requires repetitive detailed inspections for defects and damage of the retract port flexible hoses on the left and right Main Landing Gear (MLG) retraction actuator, and replacement of the flexible hoses if necessary. Since we issued AD 2012– 08–11, we determined that the orientation of the retraction actuator ports must be revised to address the identified unsafe condition. This proposed AD would continue to require the actions required by AD 2012–08–11, and would require reorientation of the retraction actuator of the MLG, which would terminate the repetitive inspections. This proposed AD would also remove airplanes from the applicability. We are proposing this AD to prevent hydraulic fluid leakage in the event of a damaged retract port flexible hose failure; this condition could lead to an undamped extension of the MLG and could result in MLG structural failure, leading to an unsafe, asymmetric landing configuration. DATES: We must receive comments on this proposed AD by September 19, 2016. SUMMARY: You may send comments 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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. ADDRESSES: PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 51821 • For Bombardier service information identified in this NPRM, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375– 4539; email thd.qseries@ aero.bombardier.com; Internet http:// www.bombardier.com. For Goodrich service information identified in this NPRM, contact Goodrich Corporation, Landing Gear, 1400 South Service Road, West Oakville, ON, Canada L6L 5Y7; telephone +1–877–808–7575; fax: +1– 860–660–0372; Internet: https:// techpubs.goodrich.com/ContactUs. 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– 8183; 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: Cesar Gomez, Mechanical Systems Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516– 228–7318; fax 516–794–5531. 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–2016–8183; Directorate Identifier 2015–NM–083–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 E:\FR\FM\05AUP1.SGM 05AUP1

Agencies

[Federal Register Volume 81, Number 151 (Friday, August 5, 2016)]
[Proposed Rules]
[Pages 51818-51821]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-18486]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-8184; Directorate Identifier 2016-NM-036-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 series airplanes; and Airbus Model A300 B4-600, B4-
600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F 
airplanes (collectively called Model A300-600 series airplanes). This 
proposed AD was prompted by reports of cracks in certain pins in the 
main landing gear (MLG). This proposed AD would require repetitive 
detailed visual inspections of the pins for cracks, and replacing the 
MLG leg if necessary. We are proposing this AD to detect and correct 
cracking of certain pins in the MLG, which could result in a MLG 
collapse, and consequent damage to the airplane and injury to the 
airplane occupants.

DATES: We must receive comments on this proposed AD by September 19, 
2016.

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 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

[[Page 51819]]

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 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-
8184; 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.

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-2016-8184; 
Directorate Identifier 2016-NM-036-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 AD 
2016-0058, dated March 21, 2016, (referred to after this as ``the 
MCAI''), to correct an unsafe condition for all Airbus Model A300 
series airplanes; and Airbus Model A300 B4-600, B4-600R, and F4-600R 
series airplanes, and Model A300 C4-605R Variant F airplanes 
(collectively called Model A300-600 series airplanes). The MCAI states:

    Two cases were reported of finding a cracked main landing gear 
(MLG) hinge arm/barrel pin, one was discovered in service during a 
maintenance task and the other one was identified during MLG 
overhaul.
    This condition, if not detected and corrected, could lead to MLG 
collapse, resulting in damage to the aeroplane and potential injury 
to occupants.
    To address this potential unsafe condition, and awaiting a final 
fix establishment, Airbus issued Alert Operators Transmission (AOT) 
32W008-16 to provide instructions for detailed visual inspections 
(DET) to detect through cracks.
    For the reasons described above, this [EASA] AD requires 
repetitive DET of the MLG hinge arm/barrel pin and, depending on 
findings, replacement of the affected MLG leg.

    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-
8184.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Alert Operators Transmission (AOT) 32W008-16, 
dated February 25, 2016. This service information describes detailed 
visual inspection and replacement procedures for the MLG hinge arm and 
barrel pin. 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 128 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                      Parts     Cost per
               Action                          Labor cost              cost     product   Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Detailed Visual Inspection.........  1 work-hour x $85 per hour =           0        $85  $10,880 per inspection
                                      $85 per inspection cycle.                            cycle.
Reporting..........................  1 work-hour x $85 per hour...          0         85  $10,880.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacement 
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 
this replacement.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Remove and Replace MLG Leg...................  20 work-hours x $85 per hour =       $3,400,000       $3,401,700
                                                $1,700.
----------------------------------------------------------------------------------------------------------------


[[Page 51820]]

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this proposed AD 
is 2120-0056. The paperwork cost associated with this proposed AD has 
been detailed in the Costs of Compliance section of this document and 
includes time for reviewing instructions, as well as completing and 
reviewing the collection of information. Therefore, all reporting 
associated with this proposed AD is mandatory. Comments concerning the 
accuracy of this burden and suggestions for reducing the burden should 
be directed to the FAA at 800 Independence Ave. SW., Washington, DC 
20591, ATTN: Information Collection Clearance Officer, AES-200.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this 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-2016-8184; Directorate Identifier 2016-NM-
036-AD.

(a) Comments Due Date

    We must receive comments by September 9, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus airplanes identified in paragraphs 
(c)(1) through (c)(5) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and 
B4-203 airplanes.
    (2) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
    (3) Model A300 B4-605R and B4-622R airplanes.
    (4) Model A300 F4-605R and F4-622R airplanes.
    (5) Model A300 C4-605R Variant F airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
Gear.

(e) Reason

    This AD was prompted by reports of cracks in certain pins in the 
main landing gear (MLG). We are issuing this AD to detect and 
correct cracking of certain pins in the MLG, which could result in a 
MLG collapse, and consequent damage to the airplane and injury to 
the airplane occupants.

(f) Compliance

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

(g) Repetitive Detailed Visual Inspections

    Within the compliance time specified in paragraphs (g)(1) and 
(g)(2) of this AD, whichever occurs later, and thereafter at 
intervals not to exceed 100 flight cycles, accomplish a detailed 
visual inspection of the internal diameter of each affected MLG 
hinge arm/barrel pin, in accordance with the instructions of Airbus 
Alert Operators Transmission (AOT) A32W008-16, dated February 25, 
2016. The affected MLG hinge arm/barrel pins are those with part 
number C66441-(x) and part number C65543-(x), where the x represents 
a variable number.
    (1) Within 30 months since the pin's first flight on an 
airplane, or since the pin's first flight on an airplane after 
overhaul, as applicable.
    (2) Within 30 days after the effective date of this AD.

(h) Corrective Action for Detailed Visual Inspection

    If any crack is found during any inspection required by 
paragraph (g) of this AD, before further flight, replace the MLG leg 
with a serviceable unit, in accordance with the instructions of 
Airbus AOT A32W008-16, dated February 25, 2016. Replacement of a MLG 
leg does not constitute terminating action for the repetitive 
inspections required by paragraph (g) of this AD.

(i) Reporting Requirement

    At the applicable time specified in paragraph (i)(1) or (i)(2) 
of this AD, report the results of the inspections required by 
paragraph (g) of this AD to Airbus in accordance with the 
instructions of Airbus AOT A32W008-16, dated February 25, 2016.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

(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 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. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or

[[Page 51821]]

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 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2016-0058, dated March 21, 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-2016-8184.
    (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 July 26, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-18486 Filed 8-4-16; 8:45 am]
BILLING CODE 4910-13-P