81 FR 64051 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 181 (September 19, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 181 (September 19, 2016)
| Page Range | 64051-64053 | |
| FR Document | 2016-22191 |
[Federal Register Volume 81, Number 181 (Monday, September 19, 2016)] [Rules and Regulations] [Pages 64051-64053] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-22191] ======================================================================== Rules and Regulations Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. ======================================================================== Federal Register / Vol. 81, No. 181 / Monday, September 19, 2016 / Rules and Regulations [[Page 64051]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-5591; Directorate Identifier 2014-NM-193-AD; Amendment 39-18651; AD 2016-19-02] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2005-15-07 for certain Airbus Model A320-111 airplanes and Model A320-200 series airplanes. AD 2005-15-07 required 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. This new AD requires additional modifications in the trailing edges of both wings. This new AD also removes airplanes from the applicability. 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. DATES: This AD is effective October 24, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 24, 2016. ADDRESSES: For service information identified in this final rule, 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 5591. 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800- 647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2005-15-07, Amendment 39-14196 (70 FR 43024, July 26, 2005) (``AD 2005-15-07''). AD 2005-15-07 applied to certain Airbus Model A320-111 airplanes and Model A320-200 series airplanes. The NPRM published in the Federal Register on April 20, 2016 (81 FR 23199). The NPRM was prompted by reports of wire chafing in the left- hand wing trailing edge. The NPRM proposed to continue to require 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. The NPRM proposed to require additional modifications in the trailing edges of both wings. The NPRM also proposed to remove airplanes from the applicability. 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. 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], 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 [[Page 64052]] 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 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. This AD also removes Model A320-111 airplanes from the applicability because those airplanes are no longer on the U.S. type certificate data sheet (there are no more A320-111 airplanes in service in the U.S. and none in storage). 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. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD as proposed, except for minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 We reviewed Airbus 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 for installing the additional anti- chafing protection. Airbus Service Bulletin A320-92-1052, dated December 5, 2007, describes procedures for replacing the current electrical cable with the new standard one. Airbus Service Bulletin A320-24-1062, Revision 07, dated November 28, 2011, describes procedures for 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. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 47 airplanes of U.S. registry. The actions required by AD 2005-15-07, and retained in this 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 were 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 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 AD on U.S. operators to be $914,620, or $19,460 per product. According to the manufacturer, some of the costs of this 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 AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2005-15-07, Amendment 39-14196 (70 FR 43024, July 26, 2005), and adding the following new AD: 2016-19-02 Airbus: Amendment 39-18651; Docket No. FAA-2016-5591; Directorate Identifier 2014-NM-193-AD. (a) Effective Date This AD is effective October 24, 2016. (b) Affected ADs This AD replaces AD 2005-15-07, Amendment 39-14196 (70 FR 43024, July 26, 2005) (``AD 2005-15-07''). [[Page 64053]] (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, With Revised Service Information 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. (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, Revision 01, dated November 28, 2011, as required by paragraph (h)(1) of this AD, remains in place. (i) New 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) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(4) and (m)(5) of this AD. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on October 24, 2016. (i) Airbus Service Bulletin A320-24-1062, Revision 07, dated November 28, 2011. (ii) Airbus Service Bulletin A320-92-1049, Revision 01, dated November 28, 2011. (iii) Airbus Service Bulletin A320-92-1052, dated December 5, 2007. (4) 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. (5) 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. (6) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on September 6, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-22191 Filed 9-16-16; 8:45 am] BILLING CODE 4910-13-P
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Rules and Regulations Federal Register
Vol. 81, No. 181
Monday, September 19, 2016
This section of the FEDERAL REGISTER Rond Point Maurice Bellonte, 31707 wing root areas. The NPRM proposed to
contains regulatory documents having general Blagnac Cedex, France; telephone +33 5 require additional modifications in the
applicability and legal effect, most of which 61 93 36 96; fax +33 5 61 93 44 51; email trailing edges of both wings. The NPRM
are keyed to and codified in the Code of account.airworth-eas@airbus.com; also proposed to remove airplanes from
Federal Regulations, which is published under Internet http://www.airbus.com. You the applicability. We are issuing this AD
50 titles pursuant to 44 U.S.C. 1510.
may view this referenced service to prevent wire chafing in the trailing
The Code of Federal Regulations is sold by information at the FAA, Transport edge of the wings, which could result in
the Superintendent of Documents. Prices of Airplane Directorate, 1601 Lind Avenue a short circuit in the vicinity of the fuel
new books are listed in the first FEDERAL SW., Renton, WA. For information on tanks, consequently resulting in a
REGISTER issue of each week. the availability of this material at the potential source of ignition in a fuel
FAA, call 425–227–1221. It is also tank vapor space and consequent fuel
available on the Internet at http:// tank explosion.
DEPARTMENT OF TRANSPORTATION www.regulations.gov by searching for The European Aviation Safety Agency
and locating Docket No. FAA–2016– (EASA), which is the Technical Agent
Federal Aviation Administration 5591. for the Member States of the European
Union, has issued EASA Airworthiness
14 CFR Part 39 Examining the AD Docket Directive 2014–0198, dated September
[Docket No. FAA–2016–5591; Directorate You may examine the AD docket on 5, 2014 (referred to after this as the
Identifier 2014–NM–193–AD; Amendment the Internet at http:// Mandatory Continuing Airworthiness
39–18651; AD 2016–19–02] www.regulations.gov by searching for Information, or ‘‘the MCAI’’), to correct
RIN 2120–AA64
and locating Docket No. FAA–2016– an unsafe condition for certain Airbus
5591; or in person at the Docket Model A320–211, –212, and –231
Airworthiness Directives; Airbus Management Facility between 9 a.m. airplanes. The MCAI states:
Airplanes and 5 p.m., Monday through Friday, Prompted by an accident * * *, the FAA
except Federal holidays. The AD docket published Special Federal Aviation
AGENCY: Federal Aviation contains this AD, the regulatory Regulation (SFAR) 88 [(66 FR 23086, May 7,
Administration (FAA), Department of evaluation, any comments received, and 2001)], and the Joint Aviation Authorities
Transportation (DOT). other information. The address for the (JAA) published Interim Policy INT/POL/25/
ACTION: Final rule. Docket Office (telephone 800–647–5527) 12.
is Docket Management Facility, U.S. Prompted by that regulation, the results of
SUMMARY: We are superseding Department of Transportation, Docket an Airbus review of the A320 type design
Airworthiness Directive (AD) 2005–15– identified, on certain aeroplanes, a possible
Operations, M–30, West Building
07 for certain Airbus Model A320–111 ignition source in fuel tank vapour space(s).
Ground Floor, Room W12–140, 1200 That condition, if not corrected, could result
airplanes and Model A320–200 series New Jersey Avenue SE., Washington,
airplanes. AD 2005–15–07 required in a fuel tank explosion and consequent loss
DC 20590. of the aeroplane.
installing insulator and cable ties to the It was, therefore, decided to modify the
FOR FURTHER INFORMATION CONTACT:
electrical cables of the S routes at the cable routes of the wing trailing edge, aft of
Sanjay Ralhan, Aerospace Engineer,
gaps in the raceway in the wing trailing the rear spar and wing tip of those
International Branch, ANM–116,
edge and the wing tip and wing root aeroplanes, to be applied in service in
Transport Airplane Directorate, FAA,
areas. This new AD requires additional accordance with the instructions of Airbus
1601 Lind Avenue SW., Renton, WA Service Bulletin (SB) A320–24–1062
modifications in the trailing edges of
98057–3356; telephone 425–227–1405; Revision 05. Following that decision, DGAC
both wings. This new AD also removes
fax 425–227–1149. France issued AD F–2004–173 (EASA
airplanes from the applicability. This
AD was prompted by reports of wire SUPPLEMENTARY INFORMATION: approval number 2004–10570) to require that
modification.
chafing in the left-hand wing trailing Discussion After that AD was issued, it was found that
edge. We are issuing this AD to prevent additional work, introduced by Airbus SB
We issued a notice of proposed
wire chafing in the trailing edge of the A320–24–1062 Revision 05, was not
rulemaking (NPRM) to amend 14 CFR
wings, which could result in a short included as part of the normal
part 39 to supersede AD 2005–15–07,
circuit in the vicinity of the fuel tanks, accomplishment instructions, which meant
Amendment 39–14196 (70 FR 43024, that the additional work might not be
consequently resulting in a potential
July 26, 2005) (‘‘AD 2005–15–07’’). AD accomplished. Consequently, EASA issued
source of ignition in a fuel tank vapor
2005–15–07 applied to certain Airbus AD 2008–0051, retaining the requirements of
space and consequent fuel tank
Model A320–111 airplanes and Model DGAC France AD F–2004–173 [which
explosion.
A320–200 series airplanes. The NPRM corresponds to FAA AD 2005–15–07], which
DATES: This AD is effective October 24, published in the Federal Register on was superseded, and required the
2016. April 20, 2016 (81 FR 23199). The accomplishment of the additional work in
The Director of the Federal Register NPRM was prompted by reports of wire accordance with the instructions of Airbus
rmajette on DSK2TPTVN1PROD with RULES
approved the incorporation by reference chafing in the left-hand wing trailing SB A320–24–1062 Revision 06. EASA AD
of certain publications listed in this AD 2008–0051 was revised to reduce the
edge. The NPRM proposed to continue Applicability and to add a clarification to
as of October 24, 2016. to require installing insulator and cable paragraph (2).
ADDRESSES: For service information ties to the electrical cables of the S After EASA AD 2008–0051R1 was issued,
identified in this final rule, contact routes at the gaps in the raceway in the some operators reported wire chafing in the
Airbus, Airworthiness Office—EIAS, 1 wing trailing edge and the wing tip and left hand wing trailing edge. Investigation
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![64052 Federal Register / Vol. 81, No. 181 / Monday, September 19, 2016 / Rules and Regulations
established that the wire chafing, initiated at 1062, Revision 07, dated November 28, air commerce by prescribing regulations
raceway gaps, was either due to maintenance 2011. for practices, methods, and procedures
action(s), or to structure vibrations. Airbus Service Bulletin A320–92– the Administrator finds necessary for
Prompted by these findings, Airbus 1049, Revision 01, dated November 28, safety in air commerce. This regulation
developed two modifications to prevent any
2011, describes procedures for installing is within the scope of that authority
further wire chafing by introducing an
additional protection at raceway gaps and a the additional anti-chafing protection. because it addresses an unsafe condition
new cable standard in the trailing edges of Airbus Service Bulletin A320–92– that is likely to exist or develop on
both wings. 1052, dated December 5, 2007, describes products identified in this rulemaking
Airbus published SB A320–92–1049 and procedures for replacing the current action.
SB A320–92–1052 to make these electrical cable with the new standard
modifications available for in-service one. Regulatory Findings
application. At the time of incorporation of Airbus Service Bulletin A320–24– We determined that this AD will not
Airbus SB A320–24–1062, these two 1062, Revision 07, dated November 28, have federalism implications under
modifications were considered recommended 2011, describes procedures for installing Executive Order 13132. This AD will
only.
insulator and cable ties to the electrical not have a substantial direct effect on
EASA recently determined that this
condition, if not corrected, could lead to a cables of the S routes at the gaps in the the States, on the relationship between
short circuit on 115 volts in the vicinity of raceway in the wing trailing edge and the national government and the States,
fuel tanks, consequently creating another risk the wing tip and wing root areas. or on the distribution of power and
of ignition source in a fuel tank vapour space. This service information is reasonably responsibilities among the various
For the reasons described above, this available because the interested parties levels of government.
[EASA] AD retains the requirements of EASA have access to it through their normal For the reasons discussed above, I
AD 2008–0051R1, which is superseded, and course of business or by the means certify that this AD:
requires modifications to install the identified in the ADDRESSES section. 1. Is not a ‘‘significant regulatory
additional anti-chafing protection and the action’’ under Executive Order 12866;
new cable standard. Costs of Compliance 2. Is not a ‘‘significant rule’’ under the
This AD also removes Model A320– We estimate that this AD affects 47 DOT Regulatory Policies and Procedures
214, –232, and –233 airplanes from the airplanes of U.S. registry. (44 FR 11034, February 26, 1979);
applicability because those airplane The actions required by AD 2005–15– 3. Will not affect intrastate aviation in
models have been modified in 07, and retained in this AD take about Alaska; and
production or in service. This AD also 35 work-hours per product, at an 4. Will not have a significant
removes Model A320–111 airplanes average labor rate of $85 per work-hour. economic impact, positive or negative,
from the applicability because those Required parts cost about $0 per on a substantial number of small entities
airplanes are no longer on the U.S. type product. Based on these figures, the under the criteria of the Regulatory
certificate data sheet (there are no more estimated cost of the actions that were Flexibility Act.
A320–111 airplanes in service in the required by AD 2005–15–07 is $2,975
per product. List of Subjects in 14 CFR Part 39
U.S. and none in storage). You may
examine the MCAI in the AD docket on We also estimate that it would take Air transportation, Aircraft, Aviation
the Internet at http:// about 76 work-hours per product to safety, Incorporation by reference,
www.regulations.gov by searching for comply with the basic requirements of Safety.
and locating Docket No. FAA–2016– this AD. The average labor rate is $85
Adoption of the Amendment
5591. per work-hour. Required parts would
cost about $13,000 per product. Based Accordingly, under the authority
Comments on these figures, we estimate the cost of delegated to me by the Administrator,
We gave the public the opportunity to this AD on U.S. operators to be the FAA amends 14 CFR part 39 as
participate in developing this AD. We $914,620, or $19,460 per product. follows:
received no comments on the NPRM or According to the manufacturer, some
on the determination of the cost to the of the costs of this AD may be covered PART 39—AIRWORTHINESS
public. under warranty, thereby reducing the DIRECTIVES
cost impact on affected individuals. We ■ 1. The authority citation for part 39
Conclusion do not control warranty coverage for continues to read as follows:
We reviewed the available data and affected individuals. As a result, we
determined that air safety and the have included all costs in our cost Authority: 49 U.S.C. 106(g), 40113, 44701.
public interest require adopting this AD estimate. § 39.13 [Amended]
as proposed, except for minor editorial
Authority for This Rulemaking ■ 2. The FAA amends § 39.13 by
changes. We have determined that these
minor changes: Title 49 of the United States Code removing Airworthiness Directive (AD)
• Are consistent with the intent that specifies the FAA’s authority to issue 2005–15–07, Amendment 39–14196 (70
was proposed in the NPRM for rules on aviation safety. Subtitle I, FR 43024, July 26, 2005), and adding the
correcting the unsafe condition; and section 106, describes the authority of following new AD:
• Do not add any additional burden the FAA Administrator. ‘‘Subtitle VII: 2016–19–02 Airbus: Amendment 39–18651;
upon the public than was already Aviation Programs,’’ describes in more Docket No. FAA–2016–5591; Directorate
proposed in the NPRM. detail the scope of the Agency’s Identifier 2014–NM–193–AD.
rmajette on DSK2TPTVN1PROD with RULES
authority. (a) Effective Date
Related Service Information Under 1 We are issuing this rulemaking under
CFR Part 51 the authority described in ‘‘Subtitle VII, This AD is effective October 24, 2016.
We reviewed Airbus Service Bulletins Part A, Subpart III, Section 44701: (b) Affected ADs
A320–92–1049, Revision 01, dated General requirements.’’ Under that This AD replaces AD 2005–15–07,
November 28, 2011; A320–92–1052, section, Congress charges the FAA with Amendment 39–14196 (70 FR 43024, July 26,
dated December 5, 2007; and A320–24– promoting safe flight of civil aircraft in 2005) (‘‘AD 2005–15–07’’).
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![Federal Register / Vol. 81, No. 181 / Monday, September 19, 2016 / Rules and Regulations 64053
(c) Applicability at Revision No. 06)’’ of the Accomplishment (m) Material Incorporated by Reference
This AD applies to Airbus Model A320– Instructions of Airbus Service Bulletin A320– (1) The Director of the Federal Register
211, –212, and –231 airplanes, certificated in 24–1062, Revision 07, dated November 28, approved the incorporation by reference
any category, all manufacturer serial numbers 2011. (IBR) of the service information listed in this
except those on which Airbus Modification (j) Credit for Previous Actions paragraph under 5 U.S.C. 552(a) and 1 CFR
22626 has been embodied in production. part 51.
(1) This paragraph provides credit for (2) You must use this service information
(d) Subject actions required by paragraphs (g) and (i) of as applicable to do the actions required by
Air Transport Association (ATA) of this AD, if those actions were performed this AD, unless this AD specifies otherwise.
America Code 24, Electrical Power; and Code before the effective date of this AD using (3) The following service information was
92. Airbus Service Bulletin A320–24–1062, approved for IBR on October 24, 2016.
(e) Reason Revision 06, dated June 26, 2007, which is (i) Airbus Service Bulletin A320–24–1062,
not incorporated by reference in this AD. Revision 07, dated November 28, 2011.
This AD was prompted by reports of wire (2) This paragraph provides credit for (ii) Airbus Service Bulletin A320–92–1049,
chafing in the left-hand wing trailing edge. Revision 01, dated November 28, 2011.
actions required by paragraph (h) of this AD,
We are issuing this AD to prevent wire (iii) Airbus Service Bulletin A320–92–
if those actions were performed before the
chafing in the trailing edge of the wings, 1052, dated December 5, 2007. (4) For service
which could result in a short circuit in the effective date of this AD using Airbus Service
Bulletin A320–92–1049, dated July 23, 2007, information identified in this AD, contact
vicinity of the fuel tanks, consequently Airbus, Airworthiness Office—EIAS, 1 Rond
resulting in a potential source of ignition in which is not incorporated by reference in this
AD. Point Maurice Bellonte, 31707 Blagnac
a fuel tank vapor space and consequent fuel Cedex, France; telephone +33 5 61 93 36 96;
tank explosion. (k) Other FAA AD Provisions fax +33 5 61 93 44 51; email
(f) Compliance The following provisions also apply to this account.airworth-eas@airbus.com; Internet
AD: http://www.airbus.com.
Comply with this AD within the (5) You may view this service information
compliance times specified, unless already (1) Alternative Methods of Compliance
at the FAA, Transport Airplane Directorate,
done. (AMOCs): The Manager, International
1601 Lind Avenue SW., Renton, WA. For
Branch, ANM–116, Transport Airplane
(g) Retained Modification, With Revised information on the availability of this
Directorate, FAA, has the authority to material at the FAA, call 425–227–1221.
Service Information
approve AMOCs for this AD, if requested (6) You may view this service information
This paragraph restates the requirements of using the procedures found in 14 CFR 39.19. that is incorporated by reference at the
paragraph (f) of AD 2005–15–07, with revised In accordance with 14 CFR 39.19, send your National Archives and Records
service information. Within 60 months after request to your principal inspector or local Administration (NARA). For information on
August 30, 2005 (the effective date of AD Flight Standards District Office, as
2005–15–07), install insulator and cable ties the availability of this material at NARA, call
appropriate. If sending information directly 202–741–6030, or go to: http://
to the electrical cables of the S routes at the to the International Branch, send it to ATTN:
gaps in the raceway in the wing trailing edge www.archives.gov/federal-register/cfr/ibr-
Sanjay Ralhan, Aerospace Engineer, locations.html.
and the wing tip and wing root areas, in
International Branch, ANM–116, Transport
accordance with Airbus Service Bulletin Issued in Renton, Washington, on
A320–24–1062, Revision 05, dated June 27, Airplane Directorate, FAA, 1601 Lind
September 6, 2016.
2002; or the Accomplishment Instructions of Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149. Michael Kaszycki,
Airbus Service Bulletin A320–24–1062,
Information may be emailed to: 9-ANM-116- Acting Manager, Transport Airplane
Revision 07, dated November 28, 2011. As of
AMOC-REQUESTS@faa.gov. Before using Directorate, Aircraft Certification Service.
the effective date of this AD, only Airbus
Service Bulletin A320–24–1062, Revision 07, any approved AMOC, notify your appropriate [FR Doc. 2016–22191 Filed 9–16–16; 8:45 am]
dated November 28, 2011, may be used. principal inspector, or lacking a principal BILLING CODE 4910–13–P
inspector, the manager of the local flight
(h) New Requirement of This AD: standards district office/certificate holding
Modification of Trailing Edges district office. The AMOC approval letter DEPARTMENT OF TRANSPORTATION
Within 60 months after the effective date must specifically reference this AD.
of this AD, modify the trailing edges of both (2) Contacting the Manufacturer: As of the Federal Aviation Administration
wings by accomplishing the actions specified effective date of this AD, for any requirement
in paragraphs (h)(1) and (h)(2) of this AD. in this AD to obtain corrective actions from
(1) Install the additional anti-chafing 14 CFR Part 39
a manufacturer, the action must be
protection in accordance with the accomplished using a method approved by [Docket No. FAA–2016–4229; Directorate
Accomplishment Instructions of Airbus the Manager, International Branch, ANM– Identifier 2015–CE–038–AD; Amendment
Service Bulletin A320–92–1049, Revision 01, 116, Transport Airplane Directorate, FAA; or 39–18657; AD 2016–19–08]
dated November 28, 2011. the European Aviation Safety Agency
(2) Replace the current electrical cable with RIN 2120–AA64
(EASA); or Airbus’s EASA Design
the new standard one in accordance with the
Organization Approval (DOA). If approved by Airworthiness Directives; Viking Air
Accomplishment Instructions of Airbus
the DOA, the approval must include the Limited Airplanes
Service Bulletin A320–92–1052, dated
December 5, 2007. During the replacement, DOA-authorized signature.
ensure that the anti-chafing protection (l) Related Information
AGENCY: Federal Aviation
specified in Airbus Service Bulletin A320– Administration (FAA), Department of
(1) Refer to Mandatory Continuing Transportation (DOT).
92–1049, Revision 01, dated November 28,
2011, as required by paragraph (h)(1) of this Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0198, dated ACTION: Final rule.
AD, remains in place.
September 5, 2014, for related information. SUMMARY: We are adopting a new
(i) New Additional Modification This MCAI may be found in the AD docket
airworthiness directive (AD) for Viking
rmajette on DSK2TPTVN1PROD with RULES
For airplanes on which the installation on the Internet at http://www.regulations.gov
by searching for and locating Docket No. Air Limited Models DHC–2 Mk. I, DHC–
specified in Airbus Service Bulletin A320–
24–1062, Revision 05, dated June 27, 2002, FAA–2016–5591. 2 Mk. II, and DHC–2 Mk. III airplanes.
has been done: Within 60 months after the (2) Service information identified in this This AD results from mandatory
effective date of this AD, install insulators AD that is not incorporated by reference is continuing airworthiness information
and cable ties, in accordance with available at the addresses specified in (MCAI) issued by an aviation authority
‘‘Modification—Additional Work (Introduced paragraphs (m)(4) and (m)(5) of this AD. of another country to identify and
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Document Created: 2016-09-17 02:30:21
Document Modified: 2016-09-17 02:30:21
| 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 | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective October 24, 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 64051 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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