Airworthiness Directives; Airbus Airplanes, 3294-3297 [2016-01110]

Download as PDF 3294 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations jstallworth on DSK7TPTVN1PROD with RULES In an interim rule published in the Federal Register on August 19, 2015, and effective on August 20, 2015, (80 FR 50189, Doc. No. AMS–FV–15–0033, FV15–922–1 IR), § 922.235 was amended by decreasing the assessment rate for the 2015–2016 and subsequent fiscal periods from $1.50 to $0.75 per ton. The decrease in the per ton assessment rate allows the Committee to reduce its financial reserve while still providing adequate funding to meet program expenses. Final Regulatory Flexibility Analysis Pursuant to requirements set forth in the Regulatory Flexibility Act (RFA) (5 U.S.C. 601–612), the Agricultural Marketing Service (AMS) has considered the economic impact of this rule on small entities. Accordingly, AMS has prepared this final regulatory flexibility analysis. The purpose of the RFA is to fit regulatory actions to the scale of businesses subject to such actions in order that small businesses will not be unduly or disproportionately burdened. Marketing orders issued pursuant to the Act, and the rules issued thereunder, are unique in that they are brought about through group action of essentially small entities acting on their own behalf. There are approximately 100 apricot producers in the production area and approximately 17 handlers subject to regulation under the marketing order. Small agricultural producers are defined by the Small Business Administration as those having annual receipts of less than $750,000, and small agricultural service firms are defined as those having annual receipts of less than $7,000,000 (13 CFR 121.201). The National Agricultural Statistics Service reported that, in 2014, the Washington apricot total utilization of 8,500 tons (including both fresh and processed markets) sold for an average of $1,080 per ton. Consequently, the total farm-gate value in 2014 was approximately $9,180,000. Based on the number of producers in the production area (100), the 2014 average revenue from the sale of apricots is estimated at approximately $91,800 per producer. In addition, based on information from the USDA’s Market News Service, 2014 f.o.b. prices for WA No. 1 apricots ranged from $20.00 to $26.00 per 24pound loose-pack container, and from $22.00 to $30.00 for 2-layer tray-pack containers. Using average price and shipment information provided by the Committee, it is determined that each of the Washington apricot handlers currently ship less than $7,000,000 worth of apricots on an annual basis. In VerDate Sep<11>2014 15:08 Jan 20, 2016 Jkt 238001 view of the foregoing, it can be concluded that the majority of Washington apricots producers and handlers may be classified as small entities. This rule continues in effect the action that decreased the assessment rate collected from handlers for the 2015–2016 and subsequent fiscal periods from $1.50 to $0.75 per ton of apricots handled. The Committee also unanimously recommended 2015–2016 fiscal period expenditures of $7,610. With a 2015 Washington apricot crop estimate of 5,800 fresh market tons, the Committee anticipates assessment income of approximately $4,350. Income derived from handler assessments, along with funds from the Committee’s monetary reserve, will be adequate to cover budgeted expenses for the 2015–2016 fiscal period. This action will allow the Committee to reduce its financial reserve while still providing adequate funding to meet program expenses. This rule continues in effect the action that decreased the assessment obligation imposed on handlers. Assessments are applied uniformly on all handlers. However, decreasing the assessment rate reduces the burden on handlers, and may reduce the burden on producers. In addition, the Committee’s meeting was widely publicized throughout the Washington apricot industry, and all interested persons were invited to attend the meeting and participate in Committee deliberations on all issues. Like all Committee meetings, the May 12, 2015, meeting was a public meeting, and all entities, both large and small, were able to express views on this issue. In accordance with the Paperwork Reduction Act of 1995 (44 U.S.C. Chapter 35), the order’s information collection requirements have been previously approved by the Office of Management and Budget (OMB) and assigned OMB No. 0581–0189. No changes in those requirements as a result of this action are necessary. Should any changes become necessary, they would be submitted to OMB for approval. This action imposes no additional reporting or recordkeeping requirements on either small or large Washington apricot handlers. As with all Federal marketing order programs, reports and forms are periodically reviewed to reduce information requirements and duplication by industry and public sector agencies. USDA has not identified any relevant Federal rules that duplicate, overlap, or conflict with this rule. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Comments on the interim rule were required to be received on or before October 19, 2015. No comments were received. Therefore, for reasons given in the interim rule, we are adopting the interim rule as a final rule, without change. To view the interim rule, go to: http:// www.regulations.gov/ #!documentDetail;D=AMS-FV-15-00330001. This action also affirms information contained in the interim rule concerning Executive Orders 12866, 12988, 13175, and 13563; the Paperwork Reduction Act (44 U.S.C. Chapter 35); and the EGov Act (44 U.S.C. 101). After consideration of all relevant material presented, it is found that finalizing the interim rule, without change, as published in the Federal Register (80 FR 50189, August 19, 2015) will tend to effectuate the declared policy of the Act. List of Subjects in 7 CFR Part 922 Apricots, Marketing agreements, Reporting and recordkeeping requirements. Accordingly, the interim rule amending 7 CFR part 922, which was published at 80 FR 50189 on August 19, 2015, is adopted as a final rule without change. Dated: January 15, 2016. Erin Morris, Associate Administrator, Agricultural Marketing Service. [FR Doc. 2016–01137 Filed 1–20–16; 8:45 am] BILLING CODE 3410–02–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–8433; Directorate Identifier 2015–NM–194–AD; Amendment 39–18366; AD 2016–01–07] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus Model A319–113 and A319–114 airplanes; and Model A320–211 and A320–212 airplanes. This AD requires identifying affected engines, and doing a torque check of the forward engine SUMMARY: E:\FR\FM\21JAR1.SGM 21JAR1 jstallworth on DSK7TPTVN1PROD with RULES Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations bolts on affected engines. This AD would also require, for any bolt rotation that is found, torqueing the bolt and eventually replacing the forward engine mount bolts, nuts, and washers, doing a fluorescent penetrant inspection and dimensional check of the affected bolt holes for local deformation and cracks, and doing corrective actions if necessary. This AD was prompted by an incorrect torque unit for the CFM56–5A engine forward mount fasteners that was inadvertently introduced into a certain Airbus airplane maintenance manual. We are issuing this AD to prevent loose bolts, which, if combined with induced maintenance damage, could lead to forward engine mount failure. An engine mount failure can result in an engine detachment and consequent reduced control of the airplane, damage to the airplane, and injury to persons on the ground. DATES: This AD becomes effective February 5, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 5, 2016. We must receive comments on this AD by March 7, 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: 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. For service information identified in this AD, contact Airbus, Airworthiness Office—EAS, 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.airwortheas@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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–8433. VerDate Sep<11>2014 15:08 Jan 20, 2016 Jkt 238001 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–2015– 8433; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this 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: Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2015–0229, dated November 27, 2015, (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A319–113 and A319–114 airplanes; and Model A320–211 and A320–212 airplanes. The MCAI states: A review of the maintenance instructions revealed that an incorrect torque value with wrong unit for the four forward engine mount pylon bolts was included in task 71–00–00– 400–040–A01, ‘‘Installation of the power plant with Engine Positioner TWW75E’’, of the A320 family (CFMI) [CFM International] Aircraft Maintenance Manual (AMM), revision dated May 2013. It was determined that this AMM inconsistent torque unit affected the A319/A320 airplane equipped with CFM56–5A engines only. Subsequently, AMM task 71–00–00–400– 040–A01 was corrected to include the correct values in the August 2015 revision. During the period between these two AMM revisions, incorrect torque values may have been applied. This condition, if not corrected, and if combined with induced maintenance damage, could lead to forward engine mount failure, possibly resulting in engine detachment and consequent reduced control of the airplane, damage to the airplane and/ or injury to persons on the ground. To address this potential unsafe condition, Airbus issued Alert Operators Transmission (AOT) A71N010–15 * * *, to provide instructions to check the torque values of the forward engine mount bolts. For the reasons described above, this [EASA] AD requires identification of CFM56–5A engines that were installed by using the incorrect torque data, verifying the proper torque value of the all four forward PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 3295 engine mount pylon bolts and, depending on findings, accomplishment of corrective action(s) [i.e., tightening the under-torqued bolts and replacement of bolts at the next engine change. The replacement includes a fluorescent penetrant inspection and dimensional check of the pylon bolt holes of the affected forward engine mount platform for local deformation and cracks and corrective actions, i.e., replacing the forward platform]. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–8433. Related Service Information Under 1 CFR Part 51 Airbus has issued Alert Operators Transmission (AOT) A71N010–15, dated September 30, 2015. The service information describes procedures for checking the current torque value for the forward engine bolts; torqueing the bolt; replacing the forward engine mount bolts, nuts, and washers; doing a fluorescent penetrant inspection and dimensional check of the pylon bolt holes of the affected forward engine mount platform for local deformation and cracks; and doing 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 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 issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of these same type designs. FAA’s Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because this condition, if not corrected, and if combined with induced maintenance damage, could lead to forward engine mount failure. A failed engine mount can result in engine detachment and consequent reduced control of the airplane, damage to the airplane, and injury to persons on the E:\FR\FM\21JAR1.SGM 21JAR1 3296 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations ground. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2015–8433; Directorate Identifier 2015–NM–194– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this 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 AD. jstallworth on DSK7TPTVN1PROD with RULES Costs of Compliance We estimate that this AD affects 126 airplanes of U.S. registry. We also estimate that it will take about 5 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $53,550, or $425 per product. In addition, we estimate that any necessary follow-on actions will take about 1 work-hour for a cost of $85 per product. We have no definitive costs for the engine mounting bolts, nuts, and washers, and no way of determining the number of aircraft that might need this action. 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 VerDate Sep<11>2014 15:08 Jan 20, 2016 Jkt 238001 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 AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2016–01–07 Airbus: Amendment 39–18366. Docket No. FAA–2015–8433; Directorate Identifier 2015–NM–194–AD. (a) Effective Date This AD becomes effective February 5, 2016. (b) Affected ADs None. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category. (1) Airbus Model A319–113 and A319–114 airplanes, all manufacturer serial numbers. (2) Airbus Model A320–211 and A320–212 airplanes, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 71, Power Plant. (e) Reason This AD was prompted by an incorrect torque unit for the CFM56–5A engine forward mount fasteners that was inadvertently introduced into a certain Airbus airplane maintenance manual. We are issuing this AD to prevent loose bolts, which if combined with induced maintenance damage, could lead to forward engine mount failure. An engine mount failure can result in an engine detachment and consequent reduced control of the airplane, damage to the airplane, and injury to persons on the ground. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Identification of Affected Engines and Torque Check Within 2 months after the effective date of this AD, accomplish the actions required by paragraphs (g)(1) and (g)(2) of this AD, as applicable. (1) Identify each CFM56–5A engine that has been installed on the airplane as specified in A318/A319/A320/A321 Airplane Maintenance Manual (AMM) Task 71–00– 00–400–040–A01, ‘‘Installation of the Power Plant with Engine Positioner TWW–75E,’’ of an AMM having a revision date between May 2013 and July 2015 (inclusive). A review of airplane maintenance records is acceptable in lieu of this determination if the date of the AMM revision used for the engine installation can be conclusively determined from that review. (2) For each engine installation determined to be affected as required by paragraph (g)(1) of this AD, check the torque values applied on the forward engine mount bolts, in accordance with the instructions of paragraph 4.2.2 of Airbus Alert Operators Transmission (AOT) A71N010–15, dated September 30, 2015. (h) On-Condition Actions If, during the torque check required by paragraph (g)(2) of this AD, any bolt rotation is detected, accomplish the actions required by paragraphs (h)(1) and (h)(2) of this AD. (1) Before further flight, torque the affected bolt, in accordance with the instructions of paragraph 4.2.3.1 of Airbus AOT A71N010– 15, dated September 30, 2015. (2) During the next engine removal, replace the forward engine mount bolts, nuts, and washers; accomplish a fluorescent penetrant inspection and dimensional check of the pylon bolt holes of the affected forward engine mount platform for local deformation E:\FR\FM\21JAR1.SGM 21JAR1 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations and cracks; and do all applicable corrective actions; in accordance with the instructions of paragraph 4.2.3.2 of Airbus AOT A71N010–15, dated September 30, 2015. Do all applicable corrective actions before further flight. (i) Parts Installation Limitation As of the effective date of this AD, installation of a CFM56–5A engine on an airplane is permitted, provided that the installation is accomplished using the torque values for forward engine mount bolts specified in paragraph 4.2.3.1 of Airbus AOT A71N010–15, dated September 30, 2015. Note 1 to paragraph (i) of this AD: Additional guidance for the re-torque can be found in Airbus A318/A319/A320/A321 AMM, Task 71–00–00–400–040–A01, ‘‘Installation of the Power Plant with Engine Positioner TWW 75E,’’ dated August 2015. (j) Special Flight Permits Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed. (k) Other FAA AD Provisions jstallworth on DSK7TPTVN1PROD with RULES 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: 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. 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 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. (l) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2015–0229, dated November 27, 2015, for related information. You may examine the MCAI on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015–8433. VerDate Sep<11>2014 15:08 Jan 20, 2016 Jkt 238001 (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Alert Operators Transmission (AOT) A71N010–15, dated September 30, 2015. (ii) Reserved. (3) For service information identified in this AD, 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 http://www.airbus.com. (4) 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on December 28, 2015. Phil Forde, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–01110 Filed 1–20–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–1987; Directorate Identifier 2014–NM–240–AD; Amendment 39–18377; AD 2016–01–17] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL–600–2C10 (Regional Jet Series 700, 701, & 702) airplanes. This AD was prompted by reports of cracked forward door members of the inboard main landing gear (MLG) doors. This AD requires repetitive inspections of the inboard MLG doors, repairs if necessary, and replacement of the inboard MLG doors. SUMMARY: PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 3297 This AD also provides optional terminating action for the door replacement. We are issuing this AD to prevent loss of an MLG door during flight, which could result in damage to the airplane. DATES: This AD becomes effective February 25, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 25, 2016. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2015-1987; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this AD, contact Bombardier, Inc., 400 ˆ ´ Cote-Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; telephone 514–855– 5000; fax 514–855–7401; email thd.crj@ aero.bombardier.com; Internet http:// www.bombardier.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. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 1987. FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone 516–228– 7329; fax 516–794–5531. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Bombardier, Inc. Model CL–600–2C10 (Regional Jet Series 700, 701, & 702) airplanes. The NPRM published in the Federal Register on June 30, 2015 (80 FR 37200). The NPRM was prompted by reports of cracked forward door members of the inboard MLG doors. The NPRM proposed to require repetitive inspections of the inboard MLG doors, repairs if necessary, and replacement of the inboard MLG doors. The NPRM also proposed optional terminating action for the door replacement. We are issuing this AD to prevent loss of an MLG door during flight, which could result in damage to the airplane. E:\FR\FM\21JAR1.SGM 21JAR1

Agencies

[Federal Register Volume 81, Number 13 (Thursday, January 21, 2016)]
[Rules and Regulations]
[Pages 3294-3297]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-01110]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-8433; Directorate Identifier 2015-NM-194-AD; 
Amendment 39-18366; AD 2016-01-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A319-113 and A319-114 airplanes; and Model A320-211 and 
A320-212 airplanes. This AD requires identifying affected engines, and 
doing a torque check of the forward engine

[[Page 3295]]

bolts on affected engines. This AD would also require, for any bolt 
rotation that is found, torqueing the bolt and eventually replacing the 
forward engine mount bolts, nuts, and washers, doing a fluorescent 
penetrant inspection and dimensional check of the affected bolt holes 
for local deformation and cracks, and doing corrective actions if 
necessary. This AD was prompted by an incorrect torque unit for the 
CFM56-5A engine forward mount fasteners that was inadvertently 
introduced into a certain Airbus airplane maintenance manual. We are 
issuing this AD to prevent loose bolts, which, if combined with induced 
maintenance damage, could lead to forward engine mount failure. An 
engine mount failure can result in an engine detachment and consequent 
reduced control of the airplane, damage to the airplane, and injury to 
persons on the ground.

DATES: This AD becomes effective February 5, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of February 5, 
2016.
    We must receive comments on this AD by March 7, 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: 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.
    For service information identified in this AD, contact Airbus, 
Airworthiness Office--EAS, 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. It 
is also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2015-8433.

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-2015-
8433; or in person at the Docket Operations office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this 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:

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2015-0229, dated November 27, 2015, (referred to after this as ``the 
MCAI''), to correct an unsafe condition for all Airbus Model A319-113 
and A319-114 airplanes; and Model A320-211 and A320-212 airplanes. The 
MCAI states:

    A review of the maintenance instructions revealed that an 
incorrect torque value with wrong unit for the four forward engine 
mount pylon bolts was included in task 71-00-00-400-040-A01, 
``Installation of the power plant with Engine Positioner TWW75E'', 
of the A320 family (CFMI) [CFM International] Aircraft Maintenance 
Manual (AMM), revision dated May 2013. It was determined that this 
AMM inconsistent torque unit affected the A319/A320 airplane 
equipped with CFM56-5A engines only.
    Subsequently, AMM task 71-00-00-400-040-A01 was corrected to 
include the correct values in the August 2015 revision. During the 
period between these two AMM revisions, incorrect torque values may 
have been applied.
    This condition, if not corrected, and if combined with induced 
maintenance damage, could lead to forward engine mount failure, 
possibly resulting in engine detachment and consequent reduced 
control of the airplane, damage to the airplane and/or injury to 
persons on the ground.
    To address this potential unsafe condition, Airbus issued Alert 
Operators Transmission (AOT) A71N010-15 * * *, to provide 
instructions to check the torque values of the forward engine mount 
bolts.
    For the reasons described above, this [EASA] AD requires 
identification of CFM56-5A engines that were installed by using the 
incorrect torque data, verifying the proper torque value of the all 
four forward engine mount pylon bolts and, depending on findings, 
accomplishment of corrective action(s) [i.e., tightening the under-
torqued bolts and replacement of bolts at the next engine change. 
The replacement includes a fluorescent penetrant inspection and 
dimensional check of the pylon bolt holes of the affected forward 
engine mount platform for local deformation and cracks and 
corrective actions, i.e., replacing the forward platform].

    You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
8433.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Alert Operators Transmission (AOT) A71N010-15, 
dated September 30, 2015. The service information describes procedures 
for checking the current torque value for the forward engine bolts; 
torqueing the bolt; replacing the forward engine mount bolts, nuts, and 
washers; doing a fluorescent penetrant inspection and dimensional check 
of the pylon bolt holes of the affected forward engine mount platform 
for local deformation and cracks; and doing 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 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 issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because this 
condition, if not corrected, and if combined with induced maintenance 
damage, could lead to forward engine mount failure. A failed engine 
mount can result in engine detachment and consequent reduced control of 
the airplane, damage to the airplane, and injury to persons on the

[[Page 3296]]

ground. Therefore, we determined that notice and opportunity for public 
comment before issuing this AD are impracticable and that good cause 
exists for making this amendment effective in fewer than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2015-8433; Directorate 
Identifier 2015-NM-194-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this 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 AD.

Costs of Compliance

    We estimate that this AD affects 126 airplanes of U.S. registry.
    We also estimate that it will take about 5 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $53,550, or $425 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 1 work-hour for a cost of $85 per product. We have no 
definitive costs for the engine mounting bolts, nuts, and washers, and 
no way of determining the number of aircraft that might need this 
action.

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 AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

2016-01-07 Airbus: Amendment 39-18366. Docket No. FAA-2015-8433; 
Directorate Identifier 2015-NM-194-AD.

(a) Effective Date

    This AD becomes effective February 5, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category.
    (1) Airbus Model A319-113 and A319-114 airplanes, all 
manufacturer serial numbers.
    (2) Airbus Model A320-211 and A320-212 airplanes, all 
manufacturer serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Power Plant.

(e) Reason

    This AD was prompted by an incorrect torque unit for the CFM56-
5A engine forward mount fasteners that was inadvertently introduced 
into a certain Airbus airplane maintenance manual. We are issuing 
this AD to prevent loose bolts, which if combined with induced 
maintenance damage, could lead to forward engine mount failure. An 
engine mount failure can result in an engine detachment and 
consequent reduced control of the airplane, damage to the airplane, 
and injury to persons on the ground.

(f) Compliance

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

(g) Identification of Affected Engines and Torque Check

    Within 2 months after the effective date of this AD, accomplish 
the actions required by paragraphs (g)(1) and (g)(2) of this AD, as 
applicable.
    (1) Identify each CFM56-5A engine that has been installed on the 
airplane as specified in A318/A319/A320/A321 Airplane Maintenance 
Manual (AMM) Task 71-00-00-400-040-A01, ``Installation of the Power 
Plant with Engine Positioner TWW-75E,'' of an AMM having a revision 
date between May 2013 and July 2015 (inclusive). A review of 
airplane maintenance records is acceptable in lieu of this 
determination if the date of the AMM revision used for the engine 
installation can be conclusively determined from that review.
    (2) For each engine installation determined to be affected as 
required by paragraph (g)(1) of this AD, check the torque values 
applied on the forward engine mount bolts, in accordance with the 
instructions of paragraph 4.2.2 of Airbus Alert Operators 
Transmission (AOT) A71N010-15, dated September 30, 2015.

(h) On-Condition Actions

    If, during the torque check required by paragraph (g)(2) of this 
AD, any bolt rotation is detected, accomplish the actions required 
by paragraphs (h)(1) and (h)(2) of this AD.
    (1) Before further flight, torque the affected bolt, in 
accordance with the instructions of paragraph 4.2.3.1 of Airbus AOT 
A71N010-15, dated September 30, 2015.
    (2) During the next engine removal, replace the forward engine 
mount bolts, nuts, and washers; accomplish a fluorescent penetrant 
inspection and dimensional check of the pylon bolt holes of the 
affected forward engine mount platform for local deformation

[[Page 3297]]

and cracks; and do all applicable corrective actions; in accordance 
with the instructions of paragraph 4.2.3.2 of Airbus AOT A71N010-15, 
dated September 30, 2015. Do all applicable corrective actions 
before further flight.

(i) Parts Installation Limitation

    As of the effective date of this AD, installation of a CFM56-5A 
engine on an airplane is permitted, provided that the installation 
is accomplished using the torque values for forward engine mount 
bolts specified in paragraph 4.2.3.1 of Airbus AOT A71N010-15, dated 
September 30, 2015.

    Note 1 to paragraph (i) of this AD: Additional guidance for the 
re-torque can be found in Airbus A318/A319/A320/A321 AMM, Task 71-
00-00-400-040-A01, ``Installation of the Power Plant with Engine 
Positioner TWW 75E,'' dated August 2015.

(j) Special Flight Permits

    Special flight permits, as described in Section 21.197 and 
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199), are not allowed.

(k) 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: 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. 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 
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.

(l) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA AD 2015-0229, dated November 27, 2015, for related information. 
You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-
2015-8433.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Alert Operators Transmission (AOT) A71N010-15, dated 
September 30, 2015.
    (ii) Reserved.
    (3) For service information identified in this AD, 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 http://www.airbus.com.
    (4) 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on December 28, 2015.
Phil Forde,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-01110 Filed 1-20-16; 8:45 am]
BILLING CODE 4910-13-P