81 FR 23199 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 76 (April 20, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 76 (April 20, 2016)
| Page Range | 23199-23202 | |
| FR Document | 2016-08953 |
[Federal Register Volume 81, Number 76 (Wednesday, April 20, 2016)] [Proposed Rules] [Pages 23199-23202] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-08953] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-5591; Directorate Identifier 2014-NM-193-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2005-15- 07, for certain Airbus Model A320-111 airplanes and Model A320-200 series airplanes. AD 2005-15-07 currently requires installing insulator and cable ties to the electrical cables of the S routes at the gaps in the raceway in the wing trailing edge and the wing tip and wing root areas. Since we issued AD 2005-15-07, we have received reports of wire chafing in the left-hand wing trailing edge. This proposed AD would require additional modifications in the trailing edges of both wings. This proposed AD would also remove airplanes from the applicability. We are proposing this AD to prevent wire chafing in the trailing edge of the wings, which could result in a short circuit in the vicinity of the fuel tanks, consequently resulting in a potential source of ignition in a fuel tank vapor space and consequent fuel tank explosion. DATES: We must receive comments on this proposed AD by June 6, 2016. ADDRESSES: You may send comments by any of the following methods: [[Page 23200]]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 NPRM, 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-2016- 5591; 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-2016-5591; Directorate Identifier 2014-NM-193-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 On July 13, 2005, we issued AD 2005-15-07, Amendment 39-14196 (70 FR 43024, July 26, 2005) (``AD 2005-15-07''). AD 2005-15-07 requires actions intended to address an unsafe condition on certain Airbus Model A320-111 airplanes and Model A320-200 series airplanes. Since we issued AD 2005-15-07, we have received reports of wire chafing in the left-hand wing trailing edge. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0198, dated September 5, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A320-211, -212, and -231 airplanes. The MCAI states: Prompted by an accident * * *, the FAA published Special Federal Aviation Regulation (SFAR) 88 [(66 FR 23086, May 7, 2001)], and the Joint Aviation Authorities (JAA) published Interim Policy INT/POL/ 25/12. Prompted by that regulation, the results of an Airbus review of the A320 type design identified, on certain aeroplanes, a possible ignition source in fuel tank vapour space(s). That condition, if not corrected, could result in a fuel tank explosion and consequent loss of the aeroplane. It was, therefore, decided to modify the cable routes of the wing trailing edge, aft of the rear spar and wing tip of those aeroplanes, to be applied in service in accordance with the instructions of Airbus Service Bulletin (SB) A320-24-1062 Revision 05. Following that decision, DGAC France issued AD F-2004-173 (EASA approval number 2004-10570) to require that modification. After that AD was issued, it was found that additional work, introduced by Airbus SB A320-24-1062 Revision 05, was not included as part of the normal accomplishment instructions, which meant that the additional work might not be accomplished. Consequently, EASA issued AD 2008-0051, retaining the requirements of DGAC France AD F- 2004-173 [which corresponds to FAA AD 2005-15-07, Amendment 39-14196 (70 FR 43024, July 26, 2005)], which was superseded, and required the accomplishment of the additional work in accordance with the instructions of Airbus SB A320-24-1062 Revision 06. EASA AD 2008- 0051 was revised to reduce the Applicability and to add a clarification to paragraph (2). After EASA AD 2008-0051R1 was issued, some operators reported wire chafing in the left hand wing trailing edge. Investigation established that the wire chafing, initiated at raceway gaps, was either due to maintenance action(s), or to structure vibrations. Prompted by these findings, Airbus developed two modifications to prevent any further wire chafing by introducing an additional protection at raceway gaps and a new cable standard in the trailing edges of both wings. Airbus published SB A320-92-1049 and SB A320- 92-1052 to make these modifications available for in-service application. At the time of incorporation of Airbus SB A320-24-1062, these two modifications were considered recommended only. EASA recently determined that this condition, if not corrected, could lead to a short circuit on 115 volts in the vicinity of fuel tanks, consequently creating another risk of ignition source in a fuel tank vapour space. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2008-0051R1, which is superseded, and requires modifications to install the additional anti-chafing protection and the new cable standard. This proposed AD also removes Model A320-214, -232, and -233 airplanes from the applicability because those airplane models have been modified in production or in service. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-5591. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletins A320-92-1049, Revision 01, dated November 28, 2011; A320-92-1052, dated December 5, 2007; and A320-24-1062, Revision 07, dated November 28, 2011. Airbus Service Bulletin A320-92-1049, Revision 01, dated November 28, 2011, describes procedures to install the additional anti-chafing protection. Airbus Service Bulletin A320-92-1052, dated December 5, 2007, describes procedures to replace the current electrical cable with the new standard one. Airbus A320-24-1062, Revision 07, dated November 28, 2011, describes procedures to install insulator and cable ties to the electrical cables of the S routes at the gaps in the raceway in the wing trailing edge and the wing tip and wing root areas. This service information is reasonably available because the interested parties have access to it through their normal [[Page 23201]] course of business or by the means identified in the ADDRESSES section. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Difference Between This Proposed AD and the MCAI or Service Information The MCAI specifies a compliance time of 72 months for modifying the trailing edges of both wings. However, this proposed AD would require a compliance time of 60 months to be consistent with the 60-month compliance time for installing the insulator and cable ties to the electrical cables of the S routes at the gaps in the raceway in the wing trailing edge and the wing tip and wing root areas specified in AD 2005-15-07. This difference has been coordinated with EASA. Costs of Compliance We estimate that this proposed AD affects 47 airplanes of U.S. registry. The actions required by AD 2005-15-07, and retained in this proposed AD take about 35 work-hours per product, at an average labor rate of $85 per work-hour. Required parts cost about $0 per product. Based on these figures, the estimated cost of the actions that are required by AD 2005-15-07 is $2,975 per product. We also estimate that it would take about 76 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $13,000 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $914,620, or $19,460 per product. According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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 removing Airworthiness Directive (AD) 2005-15-07, Amendment 39-14196 (70 FR 43024, July 26, 2005), and adding the following new AD: Airbus: Docket No. FAA-2016-5591; Directorate Identifier 2014-NM- 193-AD. (a) Comments Due Date We must receive comments by June 6, 2016. (b) Affected ADs This AD replaces AD 2005-15-07, Amendment 39-14196 (70 FR 43024, July 26, 2005) (``AD 2005-15-07''). (c) Applicability This AD applies to Airbus Model A320-211, -212, and -231 airplanes, certificated in any category, all manufacturer serial numbers except those on which Airbus Modification 22626 has been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 24, Electrical Power; and Code 92. (e) Reason This AD was prompted by reports of wire chafing in the left-hand wing trailing edge. We are issuing this AD to prevent wire chafing in the trailing edge of the wings, which could result in a short circuit in the vicinity of the fuel tanks, consequently resulting in a potential source of ignition in a fuel tank vapor space and consequent fuel tank explosion. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Modification This paragraph restates the requirements of paragraph (f) of AD 2005-15-07, with revised service information. Within 60 months after August 30, 2005 (the effective date of AD 2005-15-07), install insulator and cable ties to the electrical cables of the S routes at the gaps in the raceway in the wing trailing edge and the wing tip and wing root areas, in accordance with Airbus Service Bulletin A320-24-1062, Revision 05, dated June 27, 2002; or the Accomplishment Instructions of Airbus Service Bulletin A320-24-1062, Revision 07, dated November 28, 2011. As of the effective date of this AD, only Airbus Service Bulletin A320-24-1062, Revision 07, dated November 28, 2011, may be used. (h) New Requirement of This AD: Modification of Trailing Edges Within 60 months after the effective date of this AD, modify the trailing edges of both wings by accomplishing the actions specified in paragraphs (h)(1) and (h)(2) of this AD. (1) Install the additional anti-chafing protection in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-92-1049, Revision 01, dated November 28, 2011. [[Page 23202]] (2) Replace the current electrical cable with the new standard one in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-92-1052, dated December 5, 2007. During the replacement, ensure that the anti-chafing protection specified in Airbus Service Bulletin A320-92-1049, as required by paragraph (h)(1) of this AD, remains in place. (i) Additional Modification For airplanes on which the installation specified in Airbus Service Bulletin A320-24-1062, Revision 05, dated June 27, 2002, has been done: Within 60 months after the effective date of this AD, install insulators and cable ties, in accordance with ``Modification--Additional Work (Introduced at Revision No. 06)'' of the Accomplishment Instructions of Airbus Service Bulletin A320-24- 1062, Revision 07, dated November 28, 2011. (j) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraphs (g) and (i) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-24-1062, Revision 06, dated June 26, 2007, which is not incorporated by reference in this AD. (2) This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-92- 1049, dated July 23, 2007, which is not incorporated by reference in this AD. (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: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0198, dated September 5, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-5591. (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 April 4, 2016. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-08953 Filed 4-19-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules 23199
SW., Washington, DC 20585–0121. L’Enfant Plaza, Room 6097, SW., including Federal Register documents,
Telephone: (202) 287–6307. Email: Washington, DC public meeting attendee lists and
Johanna.Jochum@Hq.Doe.Gov. • Thursday, September 29, 2016 at 8:00 transcripts, comments, and other
SUPPLEMENTARY INFORMATION: On a.m. to 3:00 p.m. EST at 950 L’Enfant supporting documents/materials. All
January 20, 2016, ASRAC met and Plaza, Room 6097, SW., Washington, documents in the docket are listed in
unanimously passed the DC the www.regulations.gov index.
recommendation to form a Circulator Members of the public are welcome to However, not all documents listed in
Pumps Working Group. The purpose of observe the business of the meeting and, the index may be publicly available,
the working group is to discuss and, if if time allows, may make oral such as information that is exempt from
possible, reach consensus regarding statements during the specified period public disclosure.
definitions, test procedures, and energy for public comment. To attend the Issued in Washington, DC, on April 14,
conservation standards, to form the meeting and/or to make oral statements 2016.
basis of proposed energy conservation regarding any of the items on the Kathleen B. Hogan,
standards and test procedures. The agenda, email asrac@ee.doe.gov. In the Deputy Assistant Secretary for Energy
Working Group consists of email, please indicate your name, Efficiency, Energy Efficiency and Renewable
representatives of parties having a organization (if appropriate), Energy.
defined stake in the outcome of the citizenship, and contact information. [FR Doc. 2016–09126 Filed 4–19–16; 8:45 am]
proposed standards, and will consult as Please note that foreign nationals BILLING CODE 6450–01–P
appropriate with a range of experts on participating in the public meeting are
technical issues. Per the ASRAC subject to advance security screening
Charter, the Working Group is expected procedures which require advance
to make a concerted effort to negotiate notice prior to attendance at the public DEPARTMENT OF TRANSPORTATION
a final term sheet by September 30, meeting. If you are a foreign national,
Federal Aviation Administration
2016. This document announces the and wish to participate in the public
next series of meetings for this working meeting, please inform DOE as soon as
14 CFR Part 39
group. possible by contacting Ms. Regina
DOE will host public meetings and Washington at (202) 586–1214 or by [Docket No. FAA–2016–5591; Directorate
webinars on the below dates. email: Regina.Washington@ee.doe.gov Identifier 2014–NM–193–AD]
• Wednesday, May 4, 2016 at 9:00 a.m. so that the necessary procedures can be
to 5:00 p.m. EST at 955 L’Enfant completed. Anyone attending the RIN 2120–AA64
Plaza, Room 8037B, SW., Washington, meeting will be required to present a
DC government photo identification, such Airworthiness Directives; Airbus
• Thursday, May 5, 2016 from 8:00 a.m. as a passport, driver’s license, or Airplanes
to 3:00 p.m. EST at 955 L’Enfant government identification. Due to the
AGENCY: Federal Aviation
Plaza, Room 8037B, SW., Washington, required security screening upon entry,
Administration (FAA), DOT.
DC individuals attending should arrive
ACTION: Notice of proposed rulemaking
• Thursday, June 16, 2016 at 9:00 a.m. early to allow for the extra time needed.
to 5:00 p.m. EST at Navigant Offices, Due to the REAL ID Act implemented (NPRM).
1200 19th St NW., #700, Washington, by the Department of Homeland SUMMARY: We propose to supersede
DC Security (DHS) recent changes have Airworthiness Directive (AD) 2005–15–
• Friday, June 17, 2016 at 8:00 a.m. to been made regarding ID requirements 07, for certain Airbus Model A320–111
3:00 p.m. EST at 955 L’Enfant Plaza, for individuals wishing to enter Federal airplanes and Model A320–200 series
Room 8037B, SW., Washington, DC buildings from specific states and U.S. airplanes. AD 2005–15–07 currently
• Tuesday, July 12, 2016 at 9:00 a.m. to territories. Driver’s licenses from the requires installing insulator and cable
5:00 p.m. EST at 955 L’Enfant Plaza, following states or territory will not be ties to the electrical cables of the S
Room 8037B, SW., Washington, DC accepted for building entry and one of routes at the gaps in the raceway in the
• Wednesday, July 13, 2016 at 8:00 a.m. the alternate forms of ID listed below wing trailing edge and the wing tip and
to 3:00 p.m. EST at 955 L’Enfant will be required. wing root areas. Since we issued AD
Plaza, Room 8037B, SW., Washington, DHS has determined that regular 2005–15–07, we have received reports
DC driver’s licenses (and ID cards) from the of wire chafing in the left-hand wing
• Wednesday, August 10, 2016 at 9:00 following jurisdictions are not trailing edge. This proposed AD would
a.m. to 5:00 p.m. EST at 955 L’Enfant acceptable for entry into DOE facilities: require additional modifications in the
Plaza, Room 8037B, SW., Washington, Alaska, Louisiana, New York, American trailing edges of both wings. This
DC Samoa, Maine, Oklahoma, Arizona, proposed AD would also remove
• Thursday, August 11, 2016 at 8:00 Massachusetts, Washington, and airplanes from the applicability. We are
a.m. to 3:00 p.m. EST at 950 L’Enfant Minnesota. proposing this AD to prevent wire
Plaza, Room 6097, SW., Washington, Acceptable alternate forms of Photo- chafing in the trailing edge of the wings,
DC ID include: U.S. Passport or Passport which could result in a short circuit in
• Wednesday, September 7, 2016 at Card; an Enhanced Driver’s License or the vicinity of the fuel tanks,
9:00 a.m. to 5:00 p.m. EST at 955 Enhanced ID-Card issued by the states consequently resulting in a potential
Lhorne on DSK5TPTVN1PROD with PROPOSALS
L’Enfant Plaza, Room 8037B, SW., of Minnesota, New York or Washington source of ignition in a fuel tank vapor
Washington, DC (Enhanced licenses issued by these space and consequent fuel tank
• Thursday, September 8, 2016 at 8:00 states are clearly marked Enhanced or explosion.
a.m. to 3:00 p.m. EST at 950 L’Enfant Enhanced Driver’s License); A military
Plaza, Room 6097, SW., Washington, ID or other Federal government issued DATES: We must receive comments on
DC Photo-ID card. this proposed AD by June 6, 2016.
• Wednesday, September 28, 2016 at Docket: The docket is available for ADDRESSES: You may send comments by
9:00 a.m. to 5:00 p.m. EST at 950 review at www.regulations.gov, any of the following methods:
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• Federal eRulemaking Portal: Go to aspects of this proposed AD. We will SB A320–24–1062 Revision 06. EASA AD
http://www.regulations.gov. Follow the consider all comments received by the 2008–0051 was revised to reduce the
instructions for submitting comments. closing date and may amend this Applicability and to add a clarification to
paragraph (2).
• Fax: 202–493–2251. proposed AD based on those comments.
After EASA AD 2008–0051R1 was issued,
• Mail: U.S. Department of We will post all comments we
some operators reported wire chafing in the
Transportation, Docket Operations, M– receive, without change, to http:// left hand wing trailing edge. Investigation
30, West Building Ground Floor, Room www.regulations.gov, including any established that the wire chafing, initiated at
W12–140, 1200 New Jersey Avenue SE., personal information you provide. We raceway gaps, was either due to maintenance
Washington, DC 20590. will also post a report summarizing each action(s), or to structure vibrations.
• Hand Delivery: U.S. Department of substantive verbal contact we receive Prompted by these findings, Airbus
Transportation, Docket Operations, M– about this proposed AD. developed two modifications to prevent any
30, West Building Ground Floor, Room further wire chafing by introducing an
Discussion additional protection at raceway gaps and a
W12–140, 1200 New Jersey Avenue SE.,
On July 13, 2005, we issued AD 2005– new cable standard in the trailing edges of
Washington, DC, between 9 a.m. and 5 both wings. Airbus published SB A320–92–
p.m., Monday through Friday, except 15–07, Amendment 39–14196 (70 FR
1049 and SB A320–92–1052 to make these
Federal holidays. 43024, July 26, 2005) (‘‘AD 2005–15–
modifications available for in-service
For service information identified in 07’’). AD 2005–15–07 requires actions application. At the time of incorporation of
this NPRM, contact Airbus, intended to address an unsafe condition Airbus SB A320–24–1062, these two
Airworthiness Office—EIAS, 1 Rond on certain Airbus Model A320–111 modifications were considered recommended
Point Maurice Bellonte, 31707 Blagnac airplanes and Model A320–200 series only.
Cedex, France; telephone +33 5 61 93 36 airplanes. EASA recently determined that this
96; fax +33 5 61 93 44 51; email Since we issued AD 2005–15–07, we condition, if not corrected, could lead to a
have received reports of wire chafing in short circuit on 115 volts in the vicinity of
account.airworth-eas@airbus.com; fuel tanks, consequently creating another risk
Internet http://www.airbus.com. You the left-hand wing trailing edge.
The European Aviation Safety Agency of ignition source in a fuel tank vapour space.
may view this referenced service For the reasons described above, this
information at the FAA, Transport (EASA), which is the Technical Agent
[EASA] AD retains the requirements of EASA
Airplane Directorate, 1601 Lind Avenue for the Member States of the European AD 2008–0051R1, which is superseded, and
SW., Renton, WA. For information on Union, has issued EASA Airworthiness requires modifications to install the
the availability of this material at the Directive 2014–0198, dated September additional anti-chafing protection and the
FAA, call 425–227–1221. 5, 2014 (referred to after this as the new cable standard.
Mandatory Continuing Airworthiness
Examining the AD Docket Information, or ‘‘the MCAI’’), to correct This proposed AD also removes
an unsafe condition for certain Airbus Model A320–214, –232, and –233
You may examine the AD docket on airplanes from the applicability because
the Internet at http:// Model A320–211, –212, and –231
airplanes. The MCAI states: those airplane models have been
www.regulations.gov by searching for modified in production or in service.
and locating Docket No. FAA–2016– Prompted by an accident * * *, the FAA You may examine the MCAI in the AD
5591; or in person at the Docket published Special Federal Aviation docket on the Internet at http://
Management Facility between 9 a.m. Regulation (SFAR) 88 [(66 FR 23086, May 7,
2001)], and the Joint Aviation Authorities www.regulations.gov by searching for
and 5 p.m., Monday through Friday, and locating Docket No. FAA–2016–
(JAA) published Interim Policy INT/POL/25/
except Federal holidays. The AD docket 12. 5591.
contains this proposed AD, the Prompted by that regulation, the results of
regulatory evaluation, any comments Related Service Information Under 1
an Airbus review of the A320 type design
received, and other information. The identified, on certain aeroplanes, a possible CFR Part 51
street address for the Docket Operations ignition source in fuel tank vapour space(s). Airbus has issued Service Bulletins
office (telephone 800–647–5527) is in That condition, if not corrected, could result A320–92–1049, Revision 01, dated
the ADDRESSES section. Comments will in a fuel tank explosion and consequent loss November 28, 2011; A320–92–1052,
be available in the AD docket shortly of the aeroplane.
It was, therefore, decided to modify the
dated December 5, 2007; and A320–24–
after receipt. 1062, Revision 07, dated November 28,
cable routes of the wing trailing edge, aft of
FOR FURTHER INFORMATION CONTACT: the rear spar and wing tip of those 2011.
Sanjay Ralhan, Aerospace Engineer, aeroplanes, to be applied in service in Airbus Service Bulletin A320–92–
International Branch, ANM–116, accordance with the instructions of Airbus 1049, Revision 01, dated November 28,
Transport Airplane Directorate, FAA, Service Bulletin (SB) A320–24–1062 2011, describes procedures to install the
1601 Lind Avenue SW., Renton, WA Revision 05. Following that decision, DGAC additional anti-chafing protection.
98057–3356; telephone 425–227–1405; France issued AD F–2004–173 (EASA Airbus Service Bulletin A320–92–
approval number 2004–10570) to require that
fax 425–227–1149. 1052, dated December 5, 2007, describes
modification.
SUPPLEMENTARY INFORMATION: After that AD was issued, it was found that procedures to replace the current
additional work, introduced by Airbus SB electrical cable with the new standard
Comments Invited one.
A320–24–1062 Revision 05, was not
We invite you to send any written included as part of the normal Airbus A320–24–1062, Revision 07,
relevant data, views, or arguments about accomplishment instructions, which meant dated November 28, 2011, describes
Lhorne on DSK5TPTVN1PROD with PROPOSALS
this proposed AD. Send your comments that the additional work might not be procedures to install insulator and cable
to an address listed under the accomplished. Consequently, EASA issued ties to the electrical cables of the S
AD 2008–0051, retaining the requirements of routes at the gaps in the raceway in the
ADDRESSES section. Include ‘‘Docket No.
DGAC France AD F–2004–173 [which
FAA–2016–5591; Directorate Identifier corresponds to FAA AD 2005–15–07,
wing trailing edge and the wing tip and
2014–NM–193–AD’’ at the beginning of Amendment 39–14196 (70 FR 43024, July 26, wing root areas.
your comments. We specifically invite 2005)], which was superseded, and required This service information is reasonably
comments on the overall regulatory, the accomplishment of the additional work available because the interested parties
economic, environmental, and energy in accordance with the instructions of Airbus have access to it through their normal
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![Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules 23201
course of business or by the means Authority for This Rulemaking § 39.13 [Amended]
identified in the ADDRESSES section. Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by
FAA’s Determination and Requirements specifies the FAA’s authority to issue removing Airworthiness Directive (AD)
of This Proposed AD rules on aviation safety. Subtitle I, 2005–15–07, Amendment 39–14196 (70
section 106, describes the authority of FR 43024, July 26, 2005), and adding the
This product has been approved by the FAA Administrator. ‘‘Subtitle VII: following new AD:
the aviation authority of another Aviation Programs,’’ describes in more Airbus: Docket No. FAA–2016–5591;
country, and is approved for operation detail the scope of the Agency’s Directorate Identifier 2014–NM–193–AD.
in the United States. Pursuant to our authority.
bilateral agreement with the State of We are issuing this rulemaking under (a) Comments Due Date
Design Authority, we have been notified the authority described in ‘‘Subtitle VII, We must receive comments by June 6,
of the unsafe condition described in the Part A, Subpart III, Section 44701: 2016.
MCAI and service information General requirements.’’ Under that (b) Affected ADs
referenced above. We are proposing this section, Congress charges the FAA with
AD because we evaluated all pertinent This AD replaces AD 2005–15–07,
promoting safe flight of civil aircraft in Amendment 39–14196 (70 FR 43024, July 26,
information and determined an unsafe air commerce by prescribing regulations 2005) (‘‘AD 2005–15–07’’).
condition exists and is likely to exist or for practices, methods, and procedures
develop on other products of the same (c) Applicability
the Administrator finds necessary for
type design. safety in air commerce. This regulation This AD applies to Airbus Model A320–
is within the scope of that authority 211, –212, and –231 airplanes, certificated in
Difference Between This Proposed AD any category, all manufacturer serial numbers
and the MCAI or Service Information because it addresses an unsafe condition
except those on which Airbus Modification
that is likely to exist or develop on 22626 has been embodied in production.
The MCAI specifies a compliance products identified in this rulemaking
time of 72 months for modifying the action. (d) Subject
trailing edges of both wings. However, Air Transport Association (ATA) of
this proposed AD would require a Regulatory Findings America Code 24, Electrical Power; and Code
compliance time of 60 months to be We determined that this proposed AD 92.
consistent with the 60-month would not have federalism implications (e) Reason
compliance time for installing the under Executive Order 13132. This This AD was prompted by reports of wire
insulator and cable ties to the electrical proposed AD would not have a chafing in the left-hand wing trailing edge.
cables of the S routes at the gaps in the substantial direct effect on the States, on We are issuing this AD to prevent wire
raceway in the wing trailing edge and the relationship between the national chafing in the trailing edge of the wings,
the wing tip and wing root areas Government and the States, or on the which could result in a short circuit in the
specified in AD 2005–15–07. This distribution of power and vicinity of the fuel tanks, consequently
difference has been coordinated with responsibilities among the various resulting in a potential source of ignition in
EASA. levels of government. a fuel tank vapor space and consequent fuel
For the reasons discussed above, I tank explosion.
Costs of Compliance
certify this proposed regulation: (f) Compliance
We estimate that this proposed AD 1. Is not a ‘‘significant regulatory Comply with this AD within the
affects 47 airplanes of U.S. registry. action’’ under Executive Order 12866; compliance times specified, unless already
The actions required by AD 2005–15– 2. Is not a ‘‘significant rule’’ under the done.
07, and retained in this proposed AD DOT Regulatory Policies and Procedures (g) Retained Modification
take about 35 work-hours per product, (44 FR 11034, February 26, 1979);
This paragraph restates the requirements of
at an average labor rate of $85 per work- 3. Will not affect intrastate aviation in
paragraph (f) of AD 2005–15–07, with revised
hour. Required parts cost about $0 per Alaska; and service information. Within 60 months after
product. Based on these figures, the 4. Will not have a significant August 30, 2005 (the effective date of AD
estimated cost of the actions that are economic impact, positive or negative, 2005–15–07), install insulator and cable ties
required by AD 2005–15–07 is $2,975 on a substantial number of small entities to the electrical cables of the S routes at the
per product. under the criteria of the Regulatory gaps in the raceway in the wing trailing edge
Flexibility Act. and the wing tip and wing root areas, in
We also estimate that it would take accordance with Airbus Service Bulletin
about 76 work-hours per product to List of Subjects in 14 CFR Part 39 A320–24–1062, Revision 05, dated June 27,
comply with the basic requirements of Air transportation, Aircraft, Aviation 2002; or the Accomplishment Instructions of
this proposed AD. The average labor safety, Incorporation by reference,
Airbus Service Bulletin A320–24–1062,
rate is $85 per work-hour. Required Revision 07, dated November 28, 2011. As of
Safety. the effective date of this AD, only Airbus
parts would cost about $13,000 per
product. Based on these figures, we The Proposed Amendment Service Bulletin A320–24–1062, Revision 07,
dated November 28, 2011, may be used.
estimate the cost of this proposed AD on Accordingly, under the authority
U.S. operators to be $914,620, or delegated to me by the Administrator, (h) New Requirement of This AD:
$19,460 per product. Modification of Trailing Edges
the FAA proposes to amend 14 CFR part
Lhorne on DSK5TPTVN1PROD with PROPOSALS
According to the manufacturer, some 39 as follows: Within 60 months after the effective date
of the costs of this proposed AD may be of this AD, modify the trailing edges of both
covered under warranty, thereby PART 39—AIRWORTHINESS wings by accomplishing the actions specified
DIRECTIVES in paragraphs (h)(1) and (h)(2) of this AD.
reducing the cost impact on affected (1) Install the additional anti-chafing
individuals. We do not control warranty protection in accordance with the
coverage for affected individuals. As a ■ 1. The authority citation for part 39
Accomplishment Instructions of Airbus
result, we have included all costs in our continues to read as follows: Service Bulletin A320–92–1049, Revision 01,
cost estimate. Authority: 49 U.S.C. 106(g), 40113, 44701. dated November 28, 2011.
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![23202 Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules
(2) Replace the current electrical cable with the DOA, the approval must include the hinge-box forward fittings on both
the new standard one in accordance with the DOA-authorized signature. wings. We are proposing this AD to
Accomplishment Instructions of Airbus detect and correct incorrectly oriented
(l) Related Information
Service Bulletin A320–92–1052, dated or fractured fasteners, which could
December 5, 2007. During the replacement, (1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA result in detachment of the flap hinge-
ensure that the anti-chafing protection
specified in Airbus Service Bulletin A320– Airworthiness Directive 2014–0198, dated box and the flap surface, and
92–1049, as required by paragraph (h)(1) of September 5, 2014, for related information. consequent reduced controllability of
this AD, remains in place. This MCAI may be found in the AD docket the airplane.
on the Internet at http://www.regulations.gov DATES: We must receive comments on
(i) Additional Modification by searching for and locating Docket No.
FAA–2016–5591.
this proposed AD by June 6, 2016.
For airplanes on which the installation
(2) For service information identified in ADDRESSES: You may send comments by
specified in Airbus Service Bulletin A320–
24–1062, Revision 05, dated June 27, 2002, this AD, contact Airbus, Airworthiness any of the following methods:
has been done: Within 60 months after the Office—EIAS, 1 Rond Point Maurice • Federal eRulemaking Portal: Go to
effective date of this AD, install insulators Bellonte, 31707 Blagnac Cedex, France; http://www.regulations.gov. Follow the
and cable ties, in accordance with telephone +33 5 61 93 36 96; fax +33 5 61 instructions for submitting comments.
‘‘Modification—Additional Work (Introduced 93 44 51; email account.airworth-eas@ • Fax: 202–493–2251.
at Revision No. 06)’’ of the Accomplishment airbus.com; Internet http://www.airbus.com. • Mail: U.S. Department of
Instructions of Airbus Service Bulletin A320– You may view this service information at the
FAA, Transport Airplane Directorate, 1601
Transportation, Docket Operations, M–
24–1062, Revision 07, dated November 28, 30, West Building Ground Floor, Room
2011. Lind Avenue SW., Renton, WA. For
information on the availability of this W12–140, 1200 New Jersey Avenue SE.,
(j) Credit for Previous Actions material at the FAA, call 425–227–1221. Washington, DC 20590.
(1) This paragraph provides credit for • Hand Delivery: U.S. Department of
Issued in Renton, Washington, on April 4,
actions required by paragraphs (g) and (i) of 2016. Transportation, Docket Operations, M–
this AD, if those actions were performed Jeffrey E. Duven,
30, West Building Ground Floor, Room
before the effective date of this AD using W12–140, 1200 New Jersey Avenue SE.,
Airbus Service Bulletin A320–24–1062, Manager, Transport Airplane Directorate,
Aircraft Certification Service.
Washington, DC, between 9 a.m. and 5
Revision 06, dated June 26, 2007, which is p.m., Monday through Friday, except
not incorporated by reference in this AD. [FR Doc. 2016–08953 Filed 4–19–16; 8:45 am]
Federal holidays.
(2) This paragraph provides credit for BILLING CODE 4910–13–P
For service information identified in
actions required by paragraph (h) of this AD,
if those actions were performed before the
this NPRM, contact Bombardier, Inc.,
effective date of this AD using Airbus Service 400 Côte-Vertu Road West, Dorval,
DEPARTMENT OF TRANSPORTATION
Bulletin A320–92–1049, dated July 23, 2007, Québec H4S 1Y9, Canada; telephone
which is not incorporated by reference in this Federal Aviation Administration 514–855–5000; fax 514–855–7401; email
AD. thd.crj@aero.bombardier.com; Internet
(k) Other FAA AD Provisions 14 CFR Part 39 http://www.bombardier.com. You may
view this referenced service information
The following provisions also apply to this [Docket No. FAA–2016–5593; Directorate at the FAA, Transport Airplane
AD: Identifier 2015–NM–184–AD]
(1) Alternative Methods of Compliance
Directorate, 1601 Lind Avenue SW.,
(AMOCs): The Manager, International RIN 2120–AA64 Renton, WA. For information on the
Branch, ANM–116, Transport Airplane availability of this material at the FAA,
Directorate, FAA, has the authority to Airworthiness Directives; Bombardier, call 425–227–1221.
approve AMOCs for this AD, if requested Inc. Airplanes
using the procedures found in 14 CFR 39.19.
Examining the AD Docket
AGENCY: Federal Aviation
In accordance with 14 CFR 39.19, send your You may examine the AD docket on
request to your principal inspector or local Administration (FAA), DOT.
the Internet at http://
Flight Standards District Office, as ACTION: Notice of proposed rulemaking www.regulations.gov by searching for
appropriate. If sending information directly (NPRM). and locating Docket No. FAA–2016–
to the International Branch, send it to ATTN:
SUMMARY: We propose to supersede 5593; or in person at the Docket
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport Airworthiness Directive (AD) 2015–02– Management Facility between 9 a.m.
Airplane Directorate, FAA, 1601 Lind 23, for certain Bombardier, Inc. Model and 5 p.m., Monday through Friday,
Avenue SW., Renton, WA 98057–3356; CL–600–1A11 (CL–600), CL–600–2A12 except Federal holidays. The AD docket
telephone 425–227–1405; fax 425–227–1149. (CL–601), and CL–600–2B16 (CL–601– contains this proposed AD, the
Information may be emailed to: 9-ANM-116- 3A, and CL–601–3R Variants) airplanes. regulatory evaluation, any comments
AMOC-REQUESTS@faa.gov. Before using received, and other information. The
AD 2015–02–23 currently requires
any approved AMOC, notify your appropriate street address for the Docket Operations
principal inspector, or lacking a principal repetitive inspections for fractured or
incorrectly oriented fasteners on the office (telephone 800–647–5527) is in
inspector, the manager of the local flight
inboard flap hinge-box forward fittings the ADDRESSES section. Comments will
standards district office/certificate holding
district office. The AMOC approval letter on both wings, and replacement of all be available in the AD docket shortly
must specifically reference this AD. fasteners if necessary. The preamble to after receipt.
(2) Contacting the Manufacturer: As of the AD 2015–02–23 explains that we FOR FURTHER INFORMATION CONTACT: Aziz
Ahmed, Aerospace Engineer, Airframe
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effective date of this AD, for any requirement consider the requirements interim
in this AD to obtain corrective actions from action and are considering further and Mechanical Systems Branch, ANE–
a manufacturer, the action must be 171, FAA, New York Aircraft
rulemaking. We now have determined
accomplished using a method approved by Certification Office, 1600 Stewart
the Manager, International Branch, ANM– that further rulemaking is indeed
116, Transport Airplane Directorate, FAA; or necessary, and that replacement of the Avenue, Suite 410, Westbury, NY
the European Aviation Safety Agency fasteners is necessary. This proposed 11590; telephone 516–228–7329; fax
(EASA); or Airbus’s EASA Design AD would require terminating action to 516–794–5531.
Organization Approval (DOA). If approved by replace the fasteners on the inboard flap SUPPLEMENTARY INFORMATION:
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Document Created: 2016-04-20 01:52:06
Document Modified: 2016-04-20 01:52:06
| 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 June 6, 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 | 81 FR 23199 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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