80 FR 74723 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 229 (November 30, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 229 (November 30, 2015)
| Page Range | 74723-74726 | |
| FR Document | 2015-30216 |
[Federal Register Volume 80, Number 229 (Monday, November 30, 2015)] [Proposed Rules] [Pages 74723-74726] From the Federal Register Online [www.thefederalregister.org] [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 [email protected]; 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: [email protected]. 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 [email protected]; 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
![Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules 74723
a proposed AD (80 FR 32315, June 8, DEPARTMENT OF TRANSPORTATION Airworthiness Office—EIAS, 1 Rond
2015). The proposed AD had applied to Point Maurice Bellonte, 31707 Blagnac
Rolls-Royce Deutschland Ltd & Co KG Federal Aviation Administration Cedex, France; telephone +33 5 61 93 36
(RRD) Tay 650–15 and Tay 651–54 96; fax +33 5 61 93 44 51; email
turbofan engines. The NPRM proposed 14 CFR Part 39 account.airworth–eas@airbus.com;
to reduce the cyclic life limits for [Docket No. FAA–2015–6539; Directorate Internet http://www.airbus.com. You
certain HPT disks. The proposed action Identifier 2015–NM–036–AD] may view this referenced service
was prompted by an analysis that information at the FAA, Transport
RIN 2120–AA64 Airplane Directorate, 1601 Lind Avenue
showed the need to reduce the cyclic
SW., Renton, WA. For information on
life limits for certain HPT disks. The Airworthiness Directives; Airbus the availability of this material at the
proposed actions intended to prevent Airplanes FAA, call 425–227–1221.
failure of the HPT disk, which could
result in uncontained disk release, AGENCY: Federal Aviation Examining the AD Docket
Administration (FAA), DOT.
damage to the engine, and damage to the You may examine the AD docket on
airplane. ACTION: Notice of proposed rulemaking
the Internet at http://
(NPRM). www.regulations.gov by searching for
Since we issued the NPRM (80 FR
32315, June 8, 2015), additional SUMMARY: We propose to adopt a new and locating Docket No. FAA–2015–
information became available after the airworthiness directive (AD) for all 6539; or in person at the Docket
public comment period closed on Airbus Model A318–111 and –112 Management Facility between 9 a.m.
August 7, 2015. airplanes; Model A319–111, –112, –113, and 5 p.m., Monday through Friday,
–114, and –115 airplanes; Model A320– except Federal holidays. The AD docket
Upon further consideration, we contains this proposed AD, the
211, –212, and –214 airplanes; and
hereby withdraw the proposed rule regulatory evaluation, any comments
Model A321–111, –112, –211, –212, and
because we will propose to supersede received, and other information. The
–213 airplanes. This proposed AD was
AD 2006–18–14 (71 FR 52988, street address for the Docket Operations
prompted by an evaluation by the
September 8, 2006). design approval holder (DAH) office (telephone 800–647–5527) is in
Withdrawal of the NPRM (80 FR indicating that the forward engine the ADDRESSES section. Comments will
32315, June 8, 2015) constitutes only mounts are subject to widespread be available in the AD docket shortly
such action, and does not preclude the fatigue damage (WFD). This proposed after receipt.
agency from issuing another notice in AD would require repetitive detailed FOR FURTHER INFORMATION CONTACT:
the future, nor does it commit the inspections of the right and left forward Sanjay Ralhan, Aerospace Engineer,
agency to any course of action in the engine mounts, and corrective action if International Branch, ANM–116,
necessary. These inspections are Transport Airplane Directorate, FAA,
future.
required by AD 2015–05–02. This 1601 Lind Avenue SW., Renton, WA
Since this action only withdraws a 98057–3356; telephone 425–227–1405;
proposed AD would reduce the
notice of proposed rulemaking, it is fax 425–227–1149.
compliance times for those inspections.
neither a proposed nor a final rule. We are proposing this AD to detect and SUPPLEMENTARY INFORMATION:
Therefore, Executive Order 12866, the correct fatigue cracking in the forward
Regulatory Flexibility Act, or DOT Comments Invited
engine mounts, which could result in
Regulatory Policies and Procedures (44 reduced structural integrity of the We invite you to send any written
FR 11034, February 26, 1979) do not airplane and could lead to in-flight loss relevant data, views, or arguments about
cover this withdrawal. of an engine, possibly resulting in this proposed AD. Send your comments
reduced controllability of the airplane. to an address listed under the
List of Subjects in 14 CFR Part 39 ADDRESSES section. Include ‘‘Docket No.
DATES: We must receive comments on FAA–2015–6539; Directorate Identifier
Air transportation, Aircraft, Aviation this proposed AD by January 14, 2016. 2015–NM–036–AD’’ at the beginning of
safety, Incorporation by reference, ADDRESSES: You may send comments, your comments. We specifically invite
Safety. using the procedures found in 14 CFR comments on the overall regulatory,
The Withdrawal 11.43 and 11.45, by any of the following economic, environmental, and energy
methods: aspects of this proposed AD. We will
Accordingly, the notice of proposed • Federal eRulemaking Portal: Go to consider all comments received by the
rulemaking, Docket No. FAA–2015– http://www.regulations.gov. Follow the closing date and may amend this
1014; Directorate Identifier 2015–NE– instructions for submitting comments. proposed AD based on those comments.
14–AD, published in the Federal • Fax: 202–493–2251. We will post all comments we
Register on June 8, 2015 (80 FR 32315), • Mail: U.S. Department of receive, without change, to http://
is withdrawn. Transportation, Docket Operations, M– www.regulations.gov, including any
30, West Building Ground Floor, Room personal information you provide. We
Issued in Burlington, Massachusetts, on W12–140, 1200 New Jersey Avenue SE., will also post a report summarizing each
November 20, 2015. Washington, DC 20590. substantive verbal contact we receive
Colleen M. D’Alessandro, • Hand Delivery: U.S. Department of
jstallworth on DSK7TPTVN1PROD with PROPOSALS
about this proposed AD.
Directorate Manager, Engine & Propeller Transportation, Docket Operations, M–
Directorate, Aircraft Certification Service. 30, West Building Ground Floor, Room Discussion
[FR Doc. 2015–30010 Filed 11–27–15; 8:45 am] W12–140, 1200 New Jersey Avenue SE., Structural fatigue damage is
BILLING CODE 4910–13–P Washington, DC, between 9 a.m. and 5 progressive. It begins as minute cracks,
p.m., Monday through Friday, except and those cracks grow under the action
Federal holidays. of repeated stresses. This can happen
For service information identified in because of normal operational
this proposed AD, contact Airbus, conditions and design attributes, or
VerDate Sep<11>2014 15:18 Nov 27, 2015 Jkt 238001 PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 E:\FR\FM\30NOP1.SGM 30NOP1](https://thefederalregister.org/doc/80_FR_74952/page/1.svg)
![74724 Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules
because of isolated situations or while providing operators with certainty Tolerant Airworthiness Limitation Items
incidents such as material defects, poor regarding the LOV applicable to their (DT ALI), of the Airbus A318/A319/
fabrication quality, or corrosion pits, airplanes. A320/A321 ALS, Revision 02, dated
dings, or scratches. Fatigue damage can Failure of a forward engine mount May 28, 2013. AD 2015–05–02
occur locally, in small areas or could lead to in-flight loss of an engine, corresponds to EASA AD 2013–0147,
structural design details, or globally. possibly resulting in reduced dated July 16, 2013. We considered the
Global fatigue damage is general controllability of the airplane. fleet size that would be affected by
degradation of large areas of structure The European Aviation Safety Agency superseding AD 2015–05–02, and the
with similar structural details and stress (EASA), which is the Technical Agent consequent workload associated with
levels. Multiple-site damage is global for the Member States of the European revising maintenance record entries,
damage that occurs in a large structural Union, has issued EASA Airworthiness and determined that this proposed AD
element such as a single rivet line of a Directive 2015–0038, dated March 4, should not supersede AD 2015–05–02.
lap splice joining two large skin panels. 2015 (referred to after this as the Although this proposed AD would not
Global damage can also occur in Mandatory Continuing Airworthiness supersede AD 2015–05–02, paragraph
multiple elements such as adjacent Information, or ‘‘the MCAI’’), to correct (g) of this proposed AD would terminate
frames or stringers. Multiple–site- an unsafe condition for all Airbus the initial and repetitive inspections for
damage and multiple-element-damage Model A318–111 and –112 airplanes; the corresponding inspections in
cracks are typically too small initially to Model A319–111, –112, –113, –114, and paragraph (n)(2) of AD 2015–05–02,
be reliably detected with normal –115 airplanes; Model A320–211, –212, Amendment 39–18112 (80 FR 15152,
inspection methods. Without and –214 airplanes; and Model A321– March 23, 2015), for Airbus
intervention, these cracks will grow, 111, –112, –211, –212, and –213 Airworthiness Limitation Tasks
and eventually compromise the airplanes. The MCAI states: 712111–01–1, 712111–01–2, 712111–
structural integrity of the airplane, in a During a A320 Extended Service Goal 01–3, and 71211–01–4, ‘‘Detailed
condition known as widespread fatigue (ESG) residual fatigue test, in which new Inspection of Forward Engine Mount
damage (WFD). As an airplane ages, loads were used, taking into account the Installation.’’
WFD will likely occur, and will results of the 2006 fleet survey, the CFM56–
certainly occur if the airplane is 5A/5B forward engine mount experienced a FAA’s Determination and Requirements
operated long enough without any failure before reaching the threshold/interval of This Proposed AD
intervention. for the detailed inspection of that forward
engine mount, as identified in Airbus A318/ This product has been approved by
The FAA’s WFD final rule (75 FR
A319/A320/A321 Airworthiness Limitations the aviation authority of another
69746, November 15, 2010) became
Section (ALS) Part 2 (hereafter referred to in country, and is approved for operation
effective on January 14, 2011. The WFD this [EASA] AD as ‘the ALS’) task 712111– in the United States. Pursuant to our
rule requires certain actions to prevent 01. In case of total loss of the primary load bilateral agreement with the State of
structural failure due to WFD path, the current maintenance requirements Design Authority, we have been notified
throughout the operational life of do not ensure the design integrity of the
of the unsafe condition described in the
certain existing transport category remaining structure.
This condition, if not corrected, could lead MCAI and service information
airplanes and all of these airplanes that
to in-flight loss of an engine, possibly referenced above. We are proposing this
will be certificated in the future. For
resulting in reduced control of the aeroplane AD because we evaluated all pertinent
existing and future airplanes subject to
the WFD rule, the rule requires that and injury to persons on the ground. information and determined an unsafe
DAHs establish a limit of validity (LOV)
For the reasons described above, this condition exists and is likely to exist or
[EASA] AD requires implementation of a develop on other products of these same
of the engineering data that support the reduced threshold and interval for the
structural maintenance program. type designs.
detailed inspections (DET) of the forward
Operators affected by the WFD rule may engine mount on both right hand (RH) and Interim Action
not fly an airplane beyond its LOV, left hand (LH) sides, as specified in the ALS,
unless an extended LOV is approved. task 712111–01. We consider this proposed AD
The WFD rule (75 FR 69746, Once further investigations and test are interim action. Once further
November 15, 2010) does not require completed, the threshold and interval of the investigations and tests are completed,
identifying and developing maintenance ALS task 712111–01 will likely be modified the initial compliance time and
actions if the DAHs can show that such accordingly. repetitive intervals for Airbus
actions are not necessary to prevent Required actions include repair of Airworthiness Limitation Tasks
WFD before the airplane reaches the discrepancies (cracks) found during the 712111–01–1, 712111–01–2, 712111–
LOV. Many LOVs, however, do depend inspection. You may examine the MCAI 01–3, and 712111–01–4, ‘‘Detailed
on accomplishment of future in the AD docket on the Internet at Inspection of Forward Engine Mount
maintenance actions. As stated in the http://www.regulations.gov by searching Installation,’’ could be revised and we
WFD rule, any maintenance actions for and locating Docket No. FAA–2015– might consider further rulemaking at
necessary to reach the LOV will be 6539. that time.
mandated by airworthiness directives Costs of Compliance
through separate rulemaking actions. Related AD
In the context of WFD, this action is AD 2015–05–02, Amendment 39– We estimate that this proposed AD
necessary to enable DAHs to propose 18112 (80 FR 15152, March 23, 2015), affects 940 airplanes of U.S. registry.
jstallworth on DSK7TPTVN1PROD with PROPOSALS
LOVs that allow operators the longest which is applicable to all Airbus Model We also estimate that it would take
operational lives for their airplanes, and A318, A319, A320, and A321 series about 1 work-hour per product to
still ensure that WFD will not occur. airplanes, requires revising the comply with the basic requirements of
This approach allows for an maintenance or inspection program, as this proposed AD. The average labor
implementation strategy that provides applicable, to incorporate certain rate is $85 per work-hour. Based on
flexibility to DAHs in determining the Airworthiness Limitation Items. these figures, we estimate the cost of
timing of service information Paragraph (n)(2) of AD 2015–05–02 this proposed AD on U.S. operators to
development (with FAA approval), requires incorporating Part 2-Damage– be $79,900, or $85 per product.
VerDate Sep<11>2014 15:18 Nov 27, 2015 Jkt 238001 PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 E:\FR\FM\30NOP1.SGM 30NOP1](https://thefederalregister.org/doc/80_FR_74952/page/2.svg)
![Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules 74725
We have received no definitive data PART 39—AIRWORTHINESS Airworthiness Limitation Tasks 712111–01–
that would enable us to provide cost DIRECTIVES 1, 712111–01–2, 712111–01–3, or 712111–
estimates for the on-condition parts cost 01–4, ‘‘Detailed Inspection of Forward
specified in this AD. ■ 1. The authority citation for part 39 Engine Mount Installation,’’ as applicable.
continues to read as follows: (3) Within 800 flight cycles after the
Authority for This Rulemaking effective date of this AD.
Authority: 49 U.S.C. 106(g), 40113, 44701.
Title 49 of the United States Code (h) Corrective Action
§ 39.13 [Amended]
specifies the FAA’s authority to issue If any discrepancy (cracking) is found
rules on aviation safety. Subtitle I, ■ 2. The FAA amends § 39.13 by adding during any inspection required by paragraph
section 106, describes the authority of the following new airworthiness (g) of this AD: Before further flight, replace
the FAA Administrator. ‘‘Subtitle VII: directive (AD): the affected forward engine mount with a
Aviation Programs,’’ describes in more Airbus: Docket No. FAA–2015–6539; serviceable part, using a method approved by
Directorate Identifier 2015–NM–036–AD. the Manager, International Branch, ANM–
detail the scope of the Agency’s
116, Transport Airplane Directorate, FAA; or
authority. (a) Comments Due Date the European Aviation Safety Agency
We are issuing this rulemaking under We must receive comments by January 14, (EASA); or Airbus’s EASA Design
the authority described in ‘‘Subtitle VII, 2016. Organization Approval (DOA).
Part A, Subpart III, Section 44701: (b) Affected AD (i) No Terminating Action
General requirements.’’ Under that
This AD affects AD 2015–05–02, Replacement of a forward engine mount
section, Congress charges the FAA with Amendment 39–18112 (80 FR 15152, March does not constitute terminating action for the
promoting safe flight of civil aircraft in 23, 2015). repetitive inspections required by paragraph
air commerce by prescribing regulations (g) of this AD.
for practices, methods, and procedures (c) Applicability
the Administrator finds necessary for This AD applies to the Airbus airplanes, (j) Termination of Certain Tasks Required by
safety in air commerce. This regulation certificated in any category, identified in AD 2015–05–02, Amendment 39–18112 (80
is within the scope of that authority paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of FR 15152, March 23, 2015)
this AD. Accomplishment of the inspections
because it addresses an unsafe condition (1) Model A318–111 and –112 airplanes.
that is likely to exist or develop on required by paragraph (g) of this AD
(2) Model A319–111, –112, –113, –114, and
products identified in this rulemaking terminates the initial and repetitive
–115 airplanes.
inspections specified in paragraph (n)(2) of
action. (3) Model A320–211, –212, and –214
airplanes. AD 2015–05–02, Amendment 39–18112 (80
Regulatory Findings (4) Model A321–111, –112, –211, –212, and FR 15152, March 23, 2015), for Airbus
–213 airplanes. Airworthiness Limitation Tasks 712111–01–
We determined that this proposed AD 1, 712111–01–2, 712111–01–3, and 712111–
would not have federalism implications (d) Subject 01–4, ‘‘Detailed Inspection of Forward
under Executive Order 13132. This Air Transport Association (ATA) of Engine Mount Installation.’’
proposed AD would not have a America Code 05, Periodic Inspections.
(k) Other FAA AD Provisions
substantial direct effect on the States, on (e) Reason The following provisions also apply to this
the relationship between the national
This AD was prompted by an evaluation by AD:
Government and the States, or on the the design approval holder indicating that (1) Alternative Methods of Compliance
distribution of power and the forward engine mounts are subject to (AMOCs): The Manager, International
responsibilities among the various widespread fatigue damage. We are issuing Branch, ANM–116, Transport Airplane
levels of government. this AD to detect and correct fatigue cracking Directorate, FAA, has the authority to
For the reasons discussed above, I in the forward engine mounts, which could approve AMOCs for this AD, if requested
certify this proposed regulation: result in reduced structural integrity of the using the procedures found in 14 CFR 39.19.
airplane and could lead to in-flight loss of an In accordance with 14 CFR 39.19, send your
1. Is not a ‘‘significant regulatory engine, possibly resulting in reduced request to your principal inspector or local
action’’ under Executive Order 12866; controllability of the airplane. Flight Standards District Office, as
2. Is not a ‘‘significant rule’’ under the (f) Compliance appropriate. If sending information directly
DOT Regulatory Policies and Procedures to the International Branch, send it to ATTN:
Comply with this AD within the Sanjay Ralhan, Aerospace Engineer,
(44 FR 11034, February 26, 1979); compliance times specified, unless already International Branch, ANM–116, Transport
3. Will not affect intrastate aviation in done.
Airplane Directorate, FAA, 1601 Lind
Alaska; and (g) Repetitive Inspections Avenue SW., Renton, WA 98057–3356;
4. Will not have a significant At the latest of the times specified in telephone 425–227–1405; fax 425–227–1149.
economic impact, positive or negative, paragraphs (g)(1), (g)(2), and (g)(3) of this AD: Information may be emailed to: 9-ANM-116-
on a substantial number of small entities Do a detailed inspection of the left and right AMOC-REQUESTS@faa.gov. Before using
forward engine mounts for discrepancies any approved AMOC, notify your appropriate
under the criteria of the Regulatory
(cracking), using a method approved by the principal inspector, or lacking a principal
Flexibility Act. inspector, the manager of the local flight
Manager, International Branch, ANM–116,
List of Subjects in 14 CFR Part 39 Transport Airplane Directorate, FAA. Repeat standards district office/certificate holding
the inspection thereafter at intervals not to district office. The AMOC approval letter
Air transportation, Aircraft, Aviation exceed 800 flight cycles. must specifically reference this AD.
jstallworth on DSK7TPTVN1PROD with PROPOSALS
safety, Incorporation by reference, Note 1 to paragraphs (g) and (h) of this AD: (2) Contacting the Manufacturer: For any
Safety. Guidance for the inspection and engine requirement in this AD to obtain corrective
mount replacement can be found in Task actions from a manufacturer, the action must
The Proposed Amendment 712111–210–040 of the Airbus A318/A319/ be accomplished using a method approved
A320/A321 Maintenance Manual. by the Manager, International Branch, ANM–
Accordingly, under the authority (1) Within 800 flight cycles since the first 116, Transport Airplane Directorate, FAA; or
delegated to me by the Administrator, flight of the airplane. the EASA; or Airbus’s EASA DOA. If
the FAA proposes to amend 14 CFR part (2) Within 800 flight cycles since the most approved by the DOA, the approval must
39 as follows: recent detailed inspection specified in Airbus include the DOA-authorized signature.
VerDate Sep<11>2014 15:18 Nov 27, 2015 Jkt 238001 PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 E:\FR\FM\30NOP1.SGM 30NOP1](https://thefederalregister.org/doc/80_FR_74952/page/3.svg)
![74726 Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules
(l) Special Flight Permits inspections for any crack of the Airframe Branch, ANM–120S, FAA,
Special flight permits, as described in horizontal stabilizer rear spar upper Seattle Aircraft Certification Office
Section 21.197 and Section 21.199 of the chord, and corrective action if (ACO), 1601 Lind Avenue SW., Renton,
Federal Aviation Regulations (14 CFR 21.197 necessary. We are proposing this AD to WA 98057–3356; phone: 425–917–6595;
and 21.199), are not allowed. detect and correct cracking of the rear fax: 425–917–6590; email:
(m) Related Information spar upper chord, which can result in jason.deutschman@faa.gov.
(1) Refer to Mandatory Continuing the failure of the upper chord and SUPPLEMENTARY INFORMATION:
Airworthiness Information (MCAI) EASA consequent departure of the horizontal
stabilizer from the airplane, which can Comments Invited
Airworthiness Directive 2015–0038, dated
March 4, 2015, for related information. This lead to loss of continued safe flight and We invite you to send any written
MCAI may be found in the AD docket on the landing. relevant data, views, or arguments about
Internet at http://www.regulations.gov by DATES: We must receive comments on this proposal. Send your comments to
searching for and locating Docket No. FAA– an address listed under the ADDRESSES
2015–6539.
this proposed AD by January 14, 2016.
section. Include ‘‘Docket No. FAA–
(2) For service information identified in ADDRESSES: You may send comments,
2015–6541; Directorate Identifier 2015–
this AD contact Airbus, Airworthiness using the procedures found in 14 CFR
Office—EIAS, 1 Rond Point Maurice
NM–135–AD’’ at the beginning of your
11.43 and 11.45, by any of the following
Bellonte, 31707 Blagnac Cedex, France; comments. We specifically invite
methods:
comments on the overall regulatory,
telephone +33 5 61 93 36 96; fax +33 5 61 • Federal eRulemaking Portal: Go to
93 44 51; email account.airworth-eas@ economic, environmental, and energy
http://www.regulations.gov. Follow the
airbus.com; Internet http://www.airbus.com. aspects of this proposed AD. We will
You may view this service information at the
instructions for submitting comments.
consider all comments received by the
FAA, Transport Airplane Directorate, 1601 • Fax: 202–493–2251.
closing date and may amend this
Lind Avenue SW., Renton, WA. For • Mail: U.S. Department of
proposed AD because of those
information on the availability of this Transportation, Docket Operations, M–
comments.
material at the FAA, call 425–227–1221. 30, West Building Ground Floor, Room
We will post all comments we
Issued in Renton, Washington, on W12–140, 1200 New Jersey Avenue SE.,
receive, without change, to http://
November 20, 2015. Washington, DC 20590.
www.regulations.gov, including any
Jeffrey E. Duven, • Hand Delivery: Deliver to Mail
personal information you provide. We
Manager, Transport Airplane Directorate,
address above between 9 a.m. and 5
will also post a report summarizing each
Aircraft Certification Service. p.m., Monday through Friday, except
substantive verbal contact we receive
Federal holidays.
[FR Doc. 2015–30216 Filed 11–27–15; 8:45 am] about this proposed AD.
For service information identified in
BILLING CODE 4910–13–P
this proposed AD, contact Boeing Discussion
Commercial Airplanes, Attention: Data We received reports of a
DEPARTMENT OF TRANSPORTATION & Services Management, P.O. Box 3707, manufacturing oversight, in which the
MC 2H–65, Seattle, WA 98124–2207; required protective finish (zinc-nickel
Federal Aviation Administration telephone: 206–544–5000, extension 1; alloy plate or cadmium plate) was
fax: 206–766–5680; Internet: https:// omitted on the 182A1508–4/–5/–6
14 CFR Part 39 www.myboeingfleet.com. You may view bushings (in line with the terminal
this referenced service information at fitting holes) installed in the rear spar
[Docket No. FAA–2015–6541; Directorate the FAA, Transport Airplane
Identifier 2015–NM–135–AD] upper chord on horizontal stabilizers
Directorate, 1601 Lind Avenue SW., with certain serial numbers. This issue
RIN 2120–AA64 Renton, WA. For information on the was discovered after production of the
availability of this material at the FAA, affected stabilizers.
Airworthiness Directives; The Boeing call 425–227–1221. It is also available The 182A1508–4/–5/–6 bushings are
Company Airplanes on the Internet at http:// made from aluminum-nickel-bronze.
AGENCY: Federal Aviation www.regulations.gov by searching for Installing these bushings, without the
Administration (FAA), DOT. and locating Docket No. FAA–2015– required protective finish, into the
ACTION: Notice of proposed rulemaking
6541. 2024–T3511 aluminum horizontal
(NPRM). Examining the AD Docket stabilizer rear spar upper chord can lead
to galvanic corrosion between the
SUMMARY: We propose to adopt a new You may examine the AD docket on dissimilar metals. Bushings with
airworthiness directive (AD) for all The the Internet at http:// galvanic corrosion, if not corrected, can
Boeing Company Model 737–600, –700, www.regulations.gov by searching for lead to cracking of the rear spar upper
–700C, –800, –900, and –900ER series and locating Docket No. FAA–2015– chord, which can result in the failure of
airplanes. This proposed AD was 6541; or in person at the Docket the upper chord and consequent
prompted by reports of a manufacturing Management Facility between 9 a.m. departure of the horizontal stabilizer
oversight, in which a supplier omitted and 5 p.m., Monday through Friday, from the airplane, which can lead to
the required protective finish on certain except Federal holidays. The AD docket loss of continued safe flight and
bushings installed in the rear spar upper contains this proposed AD, the landing.
chord on horizontal stabilizers, which regulatory evaluation, any comments
jstallworth on DSK7TPTVN1PROD with PROPOSALS
could lead to galvanic corrosion and received, and other information. The Related Service Information Under 1
consequent cracking of the rear spar street address for the Docket Office CFR Part 51
upper chord. This proposed AD would (phone: 800–647–5527) is in the We reviewed Boeing Alert Service
require an inspection or records check ADDRESSES section. Comments will be Bulletin 737–55A1097, dated July 1,
to determine if affected horizontal available in the AD docket shortly after 2015. The service information describes
stabilizers are installed, related receipt. procedures for an inspection or records
investigative actions, and for affected FOR FURTHER INFORMATION CONTACT: review to determine if affected
horizontal stabilizers, repetitive Jason Deutschman, Aerospace Engineer, horizontal stabilizers are installed,
VerDate Sep<11>2014 15:18 Nov 27, 2015 Jkt 238001 PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 E:\FR\FM\30NOP1.SGM 30NOP1](https://thefederalregister.org/doc/80_FR_74952/page/4.svg)
Document Created: 2018-03-01 11:11:47
Document Modified: 2018-03-01 11:11:47
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by January 14, 2016. | |
| 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. | |
| FR Citation | 80 FR 74723 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR