Airworthiness Directives; Airbus Airplanes, 74723-74726 [2015-30216]

Download as PDF Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules a proposed AD (80 FR 32315, June 8, 2015). The proposed AD had applied to Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 650–15 and Tay 651–54 turbofan engines. The NPRM proposed to reduce the cyclic life limits for certain HPT disks. The proposed action was prompted by an analysis that showed the need to reduce the cyclic life limits for certain HPT disks. The proposed actions intended to prevent failure of the HPT disk, which could result in uncontained disk release, damage to the engine, and damage to the airplane. Since we issued the NPRM (80 FR 32315, June 8, 2015), additional information became available after the public comment period closed on August 7, 2015. Upon further consideration, we hereby withdraw the proposed rule because we will propose to supersede AD 2006–18–14 (71 FR 52988, September 8, 2006). Withdrawal of the NPRM (80 FR 32315, June 8, 2015) constitutes only such action, and does not preclude the agency from issuing another notice in the future, nor does it commit the agency to any course of action in the future. Since this action only withdraws a notice of proposed rulemaking, it is neither a proposed nor a final rule. Therefore, Executive Order 12866, the Regulatory Flexibility Act, or DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979) do not cover this withdrawal. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Withdrawal jstallworth on DSK7TPTVN1PROD with PROPOSALS Accordingly, the notice of proposed rulemaking, Docket No. FAA–2015– 1014; Directorate Identifier 2015–NE– 14–AD, published in the Federal Register on June 8, 2015 (80 FR 32315), is withdrawn. Issued in Burlington, Massachusetts, on November 20, 2015. Colleen M. D’Alessandro, Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2015–30010 Filed 11–27–15; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 15:18 Nov 27, 2015 Jkt 238001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–6539; Directorate Identifier 2015–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 A318–111 and –112 airplanes; Model A319–111, –112, –113, –114, and –115 airplanes; Model A320– 211, –212, and –214 airplanes; and Model A321–111, –112, –211, –212, and –213 airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the forward engine mounts are subject to widespread fatigue damage (WFD). This proposed AD would require repetitive detailed inspections of the right and left forward engine mounts, and corrective action if necessary. These inspections are required by AD 2015–05–02. This proposed AD would reduce the compliance times for those inspections. We are proposing this AD to detect and correct fatigue cracking in the forward engine mounts, which could result in reduced structural integrity of the airplane and could lead to in-flight loss of an engine, possibly resulting in reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by January 14, 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 proposed AD, contact Airbus, SUMMARY: PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 74723 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. 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–2015– 6539; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2015–6539; Directorate Identifier 2015–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 Structural fatigue damage is progressive. It begins as minute cracks, and those cracks grow under the action of repeated stresses. This can happen because of normal operational conditions and design attributes, or E:\FR\FM\30NOP1.SGM 30NOP1 jstallworth on DSK7TPTVN1PROD with PROPOSALS 74724 Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules because of isolated situations or incidents such as material defects, poor fabrication quality, or corrosion pits, dings, or scratches. Fatigue damage can occur locally, in small areas or structural design details, or globally. Global fatigue damage is general degradation of large areas of structure with similar structural details and stress levels. Multiple-site damage is global damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Global damage can also occur in multiple elements such as adjacent frames or stringers. Multiple–sitedamage and multiple-element-damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane, in a condition known as widespread fatigue damage (WFD). As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA’s WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), VerDate Sep<11>2014 15:18 Nov 27, 2015 Jkt 238001 while providing operators with certainty regarding the LOV applicable to their airplanes. Failure of a forward engine mount could lead to in-flight loss of an engine, possibly resulting in reduced controllability of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015–0038, dated March 4, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A318–111 and –112 airplanes; Model A319–111, –112, –113, –114, and –115 airplanes; Model A320–211, –212, and –214 airplanes; and Model A321– 111, –112, –211, –212, and –213 airplanes. The MCAI states: During a A320 Extended Service Goal (ESG) residual fatigue test, in which new loads were used, taking into account the results of the 2006 fleet survey, the CFM56– 5A/5B forward engine mount experienced a failure before reaching the threshold/interval for the detailed inspection of that forward engine mount, as identified in Airbus A318/ A319/A320/A321 Airworthiness Limitations Section (ALS) Part 2 (hereafter referred to in this [EASA] AD as ‘the ALS’) task 712111– 01. In case of total loss of the primary load path, the current maintenance requirements do not ensure the design integrity of the remaining structure. This condition, if not corrected, could lead to in-flight loss of an engine, possibly resulting in reduced control of the aeroplane and injury to persons on the ground. For the reasons described above, this [EASA] AD requires implementation of a reduced threshold and interval for the detailed inspections (DET) of the forward engine mount on both right hand (RH) and left hand (LH) sides, as specified in the ALS, task 712111–01. Once further investigations and test are completed, the threshold and interval of the ALS task 712111–01 will likely be modified accordingly. Required actions include repair of discrepancies (cracks) found during the inspection. 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–2015– 6539. Related AD AD 2015–05–02, Amendment 39– 18112 (80 FR 15152, March 23, 2015), which is applicable to all Airbus Model A318, A319, A320, and A321 series airplanes, requires revising the maintenance or inspection program, as applicable, to incorporate certain Airworthiness Limitation Items. Paragraph (n)(2) of AD 2015–05–02 requires incorporating Part 2-Damage– PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 Tolerant Airworthiness Limitation Items (DT ALI), of the Airbus A318/A319/ A320/A321 ALS, Revision 02, dated May 28, 2013. AD 2015–05–02 corresponds to EASA AD 2013–0147, dated July 16, 2013. We considered the fleet size that would be affected by superseding AD 2015–05–02, and the consequent workload associated with revising maintenance record entries, and determined that this proposed AD should not supersede AD 2015–05–02. Although this proposed AD would not supersede AD 2015–05–02, paragraph (g) of this proposed AD would terminate the initial and repetitive inspections for the corresponding inspections in paragraph (n)(2) of AD 2015–05–02, Amendment 39–18112 (80 FR 15152, March 23, 2015), for Airbus Airworthiness Limitation Tasks 712111–01–1, 712111–01–2, 712111– 01–3, and 71211–01–4, ‘‘Detailed Inspection of Forward Engine Mount Installation.’’ 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. Interim Action We consider this proposed AD interim action. Once further investigations and tests are completed, the initial compliance time and repetitive intervals for Airbus Airworthiness Limitation Tasks 712111–01–1, 712111–01–2, 712111– 01–3, and 712111–01–4, ‘‘Detailed Inspection of Forward Engine Mount Installation,’’ could be revised and we might consider further rulemaking at that time. Costs of Compliance We estimate that this proposed AD affects 940 airplanes of U.S. registry. We also estimate that it would take about 1 work-hour per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $79,900, or $85 per product. E:\FR\FM\30NOP1.SGM 30NOP1 Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules We have received no definitive data that would enable us to provide cost estimates for the on-condition parts cost specified in this AD. Authority for This Rulemaking 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. jstallworth on DSK7TPTVN1PROD with PROPOSALS 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: 15:18 Nov 27, 2015 Jkt 238001 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. 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. VerDate Sep<11>2014 PART 39—AIRWORTHINESS DIRECTIVES § 39.13 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2015–6539; Directorate Identifier 2015–NM–036–AD. (a) Comments Due Date We must receive comments by January 14, 2016. (b) Affected AD This AD affects AD 2015–05–02, Amendment 39–18112 (80 FR 15152, March 23, 2015). (c) Applicability This AD applies to the Airbus airplanes, certificated in any category, identified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD. (1) Model A318–111 and –112 airplanes. (2) Model A319–111, –112, –113, –114, and –115 airplanes. (3) Model A320–211, –212, and –214 airplanes. (4) Model A321–111, –112, –211, –212, and –213 airplanes. (d) Subject Air Transport Association (ATA) of America Code 05, Periodic Inspections. (e) Reason This AD was prompted by an evaluation by the design approval holder indicating that the forward engine mounts are subject to widespread fatigue damage. We are issuing this AD to detect and correct fatigue cracking in the forward engine mounts, which could result in reduced structural integrity of the airplane and could lead to in-flight loss of an engine, possibly resulting in reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections At the latest of the times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD: Do a detailed inspection of the left and right forward engine mounts for discrepancies (cracking), using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA. Repeat the inspection thereafter at intervals not to exceed 800 flight cycles. Note 1 to paragraphs (g) and (h) of this AD: Guidance for the inspection and engine mount replacement can be found in Task 712111–210–040 of the Airbus A318/A319/ A320/A321 Maintenance Manual. (1) Within 800 flight cycles since the first flight of the airplane. (2) Within 800 flight cycles since the most recent detailed inspection specified in Airbus Frm 00011 Fmt 4702 Airworthiness Limitation Tasks 712111–01– 1, 712111–01–2, 712111–01–3, or 712111– 01–4, ‘‘Detailed Inspection of Forward Engine Mount Installation,’’ as applicable. (3) Within 800 flight cycles after the effective date of this AD. (h) Corrective Action [Amended] ■ PO 00000 74725 Sfmt 4702 If any discrepancy (cracking) is found during any inspection required by paragraph (g) of this AD: Before further flight, replace the affected forward engine mount with a serviceable part, 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). (i) No Terminating Action Replacement of a forward engine mount does not constitute terminating action for the repetitive inspections required by paragraph (g) of this AD. (j) Termination of Certain Tasks Required by AD 2015–05–02, Amendment 39–18112 (80 FR 15152, March 23, 2015) Accomplishment of the inspections required by paragraph (g) of this AD terminates the initial and repetitive inspections specified in paragraph (n)(2) of AD 2015–05–02, Amendment 39–18112 (80 FR 15152, March 23, 2015), for Airbus Airworthiness Limitation Tasks 712111–01– 1, 712111–01–2, 712111–01–3, and 712111– 01–4, ‘‘Detailed Inspection of Forward Engine Mount Installation.’’ (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-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 EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. E:\FR\FM\30NOP1.SGM 30NOP1 74726 Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules (l) 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. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0038, dated March 4, 2015, 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– 2015–6539. (2) 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. 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 November 20, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–30216 Filed 11–27–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–6541; Directorate Identifier 2015–NM–135–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 737–600, –700, –700C, –800, –900, and –900ER series airplanes. This proposed AD was prompted by reports of a manufacturing oversight, in which a supplier omitted the required protective finish on certain bushings installed in the rear spar upper chord on horizontal stabilizers, which could lead to galvanic corrosion and consequent cracking of the rear spar upper chord. This proposed AD would require an inspection or records check to determine if affected horizontal stabilizers are installed, related investigative actions, and for affected horizontal stabilizers, repetitive jstallworth on DSK7TPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 15:18 Nov 27, 2015 Jkt 238001 inspections for any crack of the horizontal stabilizer rear spar upper chord, and corrective action if necessary. We are proposing this AD to detect and correct cracking of the rear spar upper chord, which can result in the failure of the upper chord and consequent departure of the horizontal stabilizer from the airplane, which can lead to loss of continued safe flight and landing. DATES: We must receive comments on this proposed AD by January 14, 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 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone: 206–544–5000, extension 1; fax: 206–766–5680; Internet: https:// www.myboeingfleet.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– 6541. 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– 6541; 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 Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Jason Deutschman, Aerospace Engineer, PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6595; fax: 425–917–6590; email: jason.deutschman@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2015–6541; Directorate Identifier 2015– NM–135–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 because of 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 We received reports of a manufacturing oversight, in which the required protective finish (zinc-nickel alloy plate or cadmium plate) was omitted on the 182A1508–4/–5/–6 bushings (in line with the terminal fitting holes) installed in the rear spar upper chord on horizontal stabilizers with certain serial numbers. This issue was discovered after production of the affected stabilizers. The 182A1508–4/–5/–6 bushings are made from aluminum-nickel-bronze. Installing these bushings, without the required protective finish, into the 2024–T3511 aluminum horizontal stabilizer rear spar upper chord can lead to galvanic corrosion between the dissimilar metals. Bushings with galvanic corrosion, if not corrected, can lead to cracking of the rear spar upper chord, which can result in the failure of the upper chord and consequent departure of the horizontal stabilizer from the airplane, which can lead to loss of continued safe flight and landing. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737–55A1097, dated July 1, 2015. The service information describes procedures for an inspection or records review to determine if affected horizontal stabilizers are installed, E:\FR\FM\30NOP1.SGM 30NOP1

Agencies

[Federal Register Volume 80, Number 229 (Monday, November 30, 2015)]
[Proposed Rules]
[Pages 74723-74726]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-30216]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-6539; Directorate Identifier 2015-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 A318-111 and -112 airplanes; Model A319-111, -112, -113, -
114, and -115 airplanes; Model A320-211, -212, and -214 airplanes; and 
Model A321-111, -112, -211, -212, and -213 airplanes. This proposed AD 
was prompted by an evaluation by the design approval holder (DAH) 
indicating that the forward engine mounts are subject to widespread 
fatigue damage (WFD). This proposed AD would require repetitive 
detailed inspections of the right and left forward engine mounts, and 
corrective action if necessary. These inspections are required by AD 
2015-05-02. This proposed AD would reduce the compliance times for 
those inspections. We are proposing this AD to detect and correct 
fatigue cracking in the forward engine mounts, which could result in 
reduced structural integrity of the airplane and could lead to in-
flight loss of an engine, possibly resulting in reduced controllability 
of the airplane.

DATES: We must receive comments on this proposed AD by January 14, 
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 proposed 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. 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-2015-
6539; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

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

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-6539; 
Directorate Identifier 2015-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

    Structural fatigue damage is progressive. It begins as minute 
cracks, and those cracks grow under the action of repeated stresses. 
This can happen because of normal operational conditions and design 
attributes, or

[[Page 74724]]

because of isolated situations or incidents such as material defects, 
poor fabrication quality, or corrosion pits, dings, or scratches. 
Fatigue damage can occur locally, in small areas or structural design 
details, or globally. Global fatigue damage is general degradation of 
large areas of structure with similar structural details and stress 
levels. Multiple-site damage is global damage that occurs in a large 
structural element such as a single rivet line of a lap splice joining 
two large skin panels. Global damage can also occur in multiple 
elements such as adjacent frames or stringers. Multiple-site-damage and 
multiple-element-damage cracks are typically too small initially to be 
reliably detected with normal inspection methods. Without intervention, 
these cracks will grow, and eventually compromise the structural 
integrity of the airplane, in a condition known as widespread fatigue 
damage (WFD). As an airplane ages, WFD will likely occur, and will 
certainly occur if the airplane is operated long enough without any 
intervention.
    The FAA's WFD final rule (75 FR 69746, November 15, 2010) became 
effective on January 14, 2011. The WFD rule requires certain actions to 
prevent structural failure due to WFD throughout the operational life 
of certain existing transport category airplanes and all of these 
airplanes that will be certificated in the future. For existing and 
future airplanes subject to the WFD rule, the rule requires that DAHs 
establish a limit of validity (LOV) of the engineering data that 
support the structural maintenance program. Operators affected by the 
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV 
is approved.
    The WFD rule (75 FR 69746, November 15, 2010) does not require 
identifying and developing maintenance actions if the DAHs can show 
that such actions are not necessary to prevent WFD before the airplane 
reaches the LOV. Many LOVs, however, do depend on accomplishment of 
future maintenance actions. As stated in the WFD rule, any maintenance 
actions necessary to reach the LOV will be mandated by airworthiness 
directives through separate rulemaking actions.
    In the context of WFD, this action is necessary to enable DAHs to 
propose LOVs that allow operators the longest operational lives for 
their airplanes, and still ensure that WFD will not occur. This 
approach allows for an implementation strategy that provides 
flexibility to DAHs in determining the timing of service information 
development (with FAA approval), while providing operators with 
certainty regarding the LOV applicable to their airplanes.
    Failure of a forward engine mount could lead to in-flight loss of 
an engine, possibly resulting in reduced controllability of the 
airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0038, dated March 4, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A318-111 and -112 airplanes; Model A319-111, -112, -113, -114, and -115 
airplanes; Model A320-211, -212, and -214 airplanes; and Model A321- 
111, -112, -211, -212, and -213 airplanes. The MCAI states:

    During a A320 Extended Service Goal (ESG) residual fatigue test, 
in which new loads were used, taking into account the results of the 
2006 fleet survey, the CFM56-5A/5B forward engine mount experienced 
a failure before reaching the threshold/interval for the detailed 
inspection of that forward engine mount, as identified in Airbus 
A318/A319/A320/A321 Airworthiness Limitations Section (ALS) Part 2 
(hereafter referred to in this [EASA] AD as `the ALS') task 712111-
01. In case of total loss of the primary load path, the current 
maintenance requirements do not ensure the design integrity of the 
remaining structure.
    This condition, if not corrected, could lead to in-flight loss 
of an engine, possibly resulting in reduced control of the aeroplane 
and injury to persons on the ground.
    For the reasons described above, this [EASA] AD requires 
implementation of a reduced threshold and interval for the detailed 
inspections (DET) of the forward engine mount on both right hand 
(RH) and left hand (LH) sides, as specified in the ALS, task 712111-
01.
    Once further investigations and test are completed, the 
threshold and interval of the ALS task 712111-01 will likely be 
modified accordingly.

    Required actions include repair of discrepancies (cracks) found 
during the inspection. 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-2015-6539.

Related AD

    AD 2015-05-02, Amendment 39-18112 (80 FR 15152, March 23, 2015), 
which is applicable to all Airbus Model A318, A319, A320, and A321 
series airplanes, requires revising the maintenance or inspection 
program, as applicable, to incorporate certain Airworthiness Limitation 
Items. Paragraph (n)(2) of AD 2015-05-02 requires incorporating Part 2-
Damage-Tolerant Airworthiness Limitation Items (DT ALI), of the Airbus 
A318/A319/A320/A321 ALS, Revision 02, dated May 28, 2013. AD 2015-05-02 
corresponds to EASA AD 2013-0147, dated July 16, 2013. We considered 
the fleet size that would be affected by superseding AD 2015-05-02, and 
the consequent workload associated with revising maintenance record 
entries, and determined that this proposed AD should not supersede AD 
2015-05-02.
    Although this proposed AD would not supersede AD 2015-05-02, 
paragraph (g) of this proposed AD would terminate the initial and 
repetitive inspections for the corresponding inspections in paragraph 
(n)(2) of AD 2015-05-02, Amendment 39-18112 (80 FR 15152, March 23, 
2015), for Airbus Airworthiness Limitation Tasks 712111-01-1, 712111-
01-2, 712111-01-3, and 71211-01-4, ``Detailed Inspection of Forward 
Engine Mount Installation.''

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.

Interim Action

    We consider this proposed AD interim action. Once further 
investigations and tests are completed, the initial compliance time and 
repetitive intervals for Airbus Airworthiness Limitation Tasks 712111-
01-1, 712111-01-2, 712111-01-3, and 712111-01-4, ``Detailed Inspection 
of Forward Engine Mount Installation,'' could be revised and we might 
consider further rulemaking at that time.

Costs of Compliance

    We estimate that this proposed AD affects 940 airplanes of U.S. 
registry.
    We also estimate that it would take about 1 work-hour per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $79,900, or $85 
per product.

[[Page 74725]]

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

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    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-2015-6539; Directorate Identifier 2015-NM-
036-AD.

(a) Comments Due Date

    We must receive comments by January 14, 2016.

(b) Affected AD

    This AD affects AD 2015-05-02, Amendment 39-18112 (80 FR 15152, 
March 23, 2015).

(c) Applicability

    This AD applies to the Airbus airplanes, certificated in any 
category, identified in paragraphs (c)(1), (c)(2), (c)(3), and 
(c)(4) of this AD.
    (1) Model A318-111 and -112 airplanes.
    (2) Model A319-111, -112, -113, -114, and -115 airplanes.
    (3) Model A320-211, -212, and -214 airplanes.
    (4) Model A321-111, -112, -211, -212, and -213 airplanes.

 (d) Subject

    Air Transport Association (ATA) of America Code 05, Periodic 
Inspections.

(e) Reason

    This AD was prompted by an evaluation by the design approval 
holder indicating that the forward engine mounts are subject to 
widespread fatigue damage. We are issuing this AD to detect and 
correct fatigue cracking in the forward engine mounts, which could 
result in reduced structural integrity of the airplane and could 
lead to in-flight loss of an engine, possibly resulting in reduced 
controllability of the airplane.

(f) Compliance

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

(g) Repetitive Inspections

    At the latest of the times specified in paragraphs (g)(1), 
(g)(2), and (g)(3) of this AD: Do a detailed inspection of the left 
and right forward engine mounts for discrepancies (cracking), using 
a method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA. Repeat the inspection 
thereafter at intervals not to exceed 800 flight cycles.
    Note 1 to paragraphs (g) and (h) of this AD: Guidance for the 
inspection and engine mount replacement can be found in Task 712111-
210-040 of the Airbus A318/A319/A320/A321 Maintenance Manual.
    (1) Within 800 flight cycles since the first flight of the 
airplane.
    (2) Within 800 flight cycles since the most recent detailed 
inspection specified in Airbus Airworthiness Limitation Tasks 
712111-01-1, 712111-01-2, 712111-01-3, or 712111-01-4, ``Detailed 
Inspection of Forward Engine Mount Installation,'' as applicable.
    (3) Within 800 flight cycles after the effective date of this 
AD.

(h) Corrective Action

    If any discrepancy (cracking) is found during any inspection 
required by paragraph (g) of this AD: Before further flight, replace 
the affected forward engine mount with a serviceable part, 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).

(i) No Terminating Action

    Replacement of a forward engine mount does not constitute 
terminating action for the repetitive inspections required by 
paragraph (g) of this AD.

(j) Termination of Certain Tasks Required by AD 2015-05-02, Amendment 
39-18112 (80 FR 15152, March 23, 2015)

    Accomplishment of the inspections required by paragraph (g) of 
this AD terminates the initial and repetitive inspections specified 
in paragraph (n)(2) of AD 2015-05-02, Amendment 39-18112 (80 FR 
15152, March 23, 2015), for Airbus Airworthiness Limitation Tasks 
712111-01-1, 712111-01-2, 712111-01-3, and 712111-01-4, ``Detailed 
Inspection of Forward Engine Mount Installation.''

(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 EASA; 
or Airbus's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.

[[Page 74726]]

(l) 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.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0038, dated March 4, 2015, 
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-2015-6539.
    (2) 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. 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 November 20, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-30216 Filed 11-27-15; 8:45 am]
BILLING CODE 4910-13-P