80 FR 7989 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 30 (February 13, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 30 (February 13, 2015)
| Page Range | 7989-7992 | |
| FR Document | 2015-02536 |
[Federal Register Volume 80, Number 30 (Friday, February 13, 2015)] [Proposed Rules] [Pages 7989-7992] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-02536] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-0083; Directorate Identifier 2014-NM-131-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A330-200, A330-200 Freighter, and A330-300 series airplanes; and all A340-200 and A340-300 series airplanes. This proposed AD was prompted by reports that a bracket that attaches the cockpit instrument panel to the airplane structure, does not sustain the fatigue loads of the design service goal. This proposed AD would require repetitive inspections of that bracket for cracking and to determine if both lugs are fully broken, an inspection for cracking of an adjacent bracket, if necessary, and corrective actions if necessary. This AD would also provide an optional modification, which would terminate the repetitive inspections. We are proposing this AD to detect and correct cracking on a bracket of the cockpit instrument panel, which, combined with failure of the horizontal beam, could lead to collapse of the cockpit panel, and reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by March 30, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 0083; 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-0083; Directorate Identifier 2014-NM-131-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 The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0127, dated May 15, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A330-200, A330-200 Freighter, and A330-300 series airplanes; and all A340-200, and A340-300 series airplanes. The MCAI states: During flight tests, high stress levels have been measured on the bracket No 6 which attaches the cockpit instrument panel to the aeroplane structure, apparently introduced through the nose landing gear due to bumps on the runway. Airbus determined that the bracket does not sustain the fatigue loads during the Design Service Goal (DSG). This condition, if not detected and corrected, combined with failure of the horizontal beam, could lead to collapse of the cockpit panel, possibly resulting in reduced control of the aeroplane. To address this potential unsafe condition, Airbus developed a program to inspect the condition of the affected cockpit instrument panel bracket No 6, and designed a stronger (reinforced titanium undrilled) bracket. The new bracket can be installed in-service through Airbus Service Bulletin (SB) A330-25-3548 or SB A340-25- 4354, as applicable to aeroplane type. For the reasons described above, this [EASA] AD requires repetitive inspections of the cockpit instrument panel bracket No 6 and, depending on findings, the accomplishment of applicable corrective actions. This [EASA] AD also provides the installation of the stronger bracket as optional terminating action for the repetitive actions required by this [EASA] AD. The corrective actions include replacing bracket No. 6 and bracket No. 7 with serviceable parts, and repair, as applicable. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 0083. [[Page 7990]] Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. Airbus Service Bulletin A330-25-3538, Revision 02, dated April 24, 2014, which provides procedures for inspection of cockpit instrument panel bracket 6. Airbus Service Bulletin A330-25-3548, dated October 31, 2013, which provides procedures for reinforcement of cockpit instrument panel bracket 6. Airbus Service Bulletin A340-25-4351, Revision 01, dated January 31, 2014, which provides procedures for inspection of cockpit instrument panel bracket 6. Airbus Service Bulletin A340-25-4354, dated October 31, 2013, which provides procedures for reinforcement of cockpit instrument panel bracket 6. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. This service information is reasonably available; see ADDRESSES for ways to access this service information. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Explanation of ``RC'' Procedures and Tests in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directives Implementation Aviation Rulemaking Committee (AD ARC), to enhance the AD system. One enhancement was a new process for annotating which procedures and tests in the service information are required for compliance with an AD. Differentiating these procedures and tests from other tasks in the service information is expected to improve an owner's/operator's understanding of crucial AD requirements and help provide consistent judgment in AD compliance. The actions specified in Airbus Service Bulletin A330-25-3538, Revision 02, dated April 24, 2014; and Airbus Service Bulletin A340-25-4351, Revision 01, dated January 31, 2014; include procedures and tests that are identified as RC (required for compliance) because these procedures have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. As specified in a NOTE under the Accomplishment Instructions of the specified service information, procedures and tests identified as RC must be done to comply with the proposed AD. However, procedures and tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an alternative method of compliance (AMOC), provided the procedures and tests identified as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to procedures or tests identified as RC will require approval of an AMOC. Costs of Compliance We estimate that this proposed AD affects 76 airplanes of U.S. registry. We also estimate that it would take about 8 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $51,680, or $680 per product. We have received no definitive data that would enable us to provide cost estimates for the follow-on repairs specified in this AD. In addition, we estimate that any necessary follow-on replacements would take about 23 work-hours and require parts costing $0, for a cost of $1,955 per product. We have no way of determining the number of aircraft that might need these actions. We estimate that the optional modification would take about 9 work hours and require parts costing $1,770, for a cost of $2,535. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): Airbus: Docket No. FAA-2015-0083; Directorate Identifier 2014-NM- 131-AD. (a) Comments Due Date We must receive comments by March 30, 2015. (b) Affected ADs None. [[Page 7991]] (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category. (1) Model A330-201, -202, -203, -223, -243, -223F, -243F, -301, -302, -303, -321, -322, -323, -341, -342, and -313 airplanes, all manufacturer serial numbers except those on which Airbus Modification 203287 has been embodied in production. (2) Model A340-211, -212, -213, -311, -312, and -313 airplanes, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 25, Equipment/ Furnishings. (e) Reason This AD was prompted by reports that a bracket that attaches the cockpit instrument panel to the airplane structure, does not sustain the fatigue loads of the design service goal. We are issuing this AD to detect and correct cracking on a bracket of the cockpit instrument panel, which, combined with failure of the horizontal beam, could lead to collapse of the cockpit panel, and reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection of Bracket No. 6 of the Cockpit Instrument Panel At the latest of the times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD: Do a detailed inspection of bracket No. 6 of the cockpit instrument panel for cracking and to determine if both bracket lugs are fully broken, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-25-3538, Revision 02, dated April 24, 2014; or Airbus Service Bulletin A340- 25-4351, Revision 01, dated January 31, 2014; as applicable. Repeat the inspection thereafter at intervals not to exceed 2,600 flight cycles. (1) Prior to accumulating 17,200 total flight cycles since the airplane's first flight. (2) Prior to bracket No. 6 of the cockpit instrument panel accumulating 17,200 total flight cycles since installation on an airplane. (3) Within 500 flight cycles after the effective date of this AD. (h) Inspection and Corrective Actions (1) If, during any inspection required by paragraph (g) of this AD, any cracking of bracket No. 6 of the cockpit instrument panel is found, but both bracket lugs are not fully broken: Within 2,600 flight cycles after that inspection, replace bracket No. 6 of the cockpit instrument panel with a serviceable part, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-25- 3538, Revision 02, dated April 24, 2014; or Airbus Service Bulletin A340-25-4351, Revision 01, dated January 31, 2014; as applicable. Replacement of bracket No. 6 of the cockpit instrument panel does not constitute terminating action for the repetitive inspections required by paragraph (g) of this AD. (2) If, during any inspection required by paragraph (g) of this AD, any cracking of bracket No. 6 of the cockpit instrument panel is found and both bracket lugs are fully broken: Before further flight, do a detailed inspection of bracket No. 7 of the cockpit instrument panel for cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-25-3538, Revision 02, dated April 24, 2014; or Airbus Service Bulletin A340-25-4351, Revision 01, dated January 31, 2014; as applicable. (i) If, during the inspection required by paragraph (h)(2) of this AD, no cracking is found in bracket No. 7 of the cockpit instrument panel: Before further flight, replace bracket No. 6 and bracket No. 7 of the cockpit instrument panel with serviceable parts, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-25-3538, Revision 02, dated April 24, 2014; or Airbus Service Bulletin A340-25-4351, Revision 01, dated January 31, 2014; as applicable. Replacement of bracket No. 6 of the cockpit instrument panel does not constitute terminating action for the repetitive inspections required by paragraph (g) of this AD. (ii) If, during the inspection required by paragraph (h)(2) of this AD, any cracking is found in bracket No. 7 of the cockpit instrument panel: Although Airbus Service Bulletin A330-25-3538, Revision 02, dated April 24, 2014; and Airbus Service Bulletin A340- 25-4351, Revision 01, dated January 31, 2014; specify to contact Airbus for repair instructions, and specify that action as ``RC'' (Required for Compliance), repair the cracking before further flight using a repair method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). (i) Optional Terminating Modification for Paragraph (g) of This AD Modifying an airplane by replacing bracket No. 6 of the cockpit instrument panel with a new, reinforced bracket, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-25- 3548, dated October 31, 2013; or Airbus Service Bulletin A340-25- 4354, dated October 31, 2013; as applicable; terminates the repetitive inspections required by paragraph (g) of this AD. (j) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraph (j)(1), (j)(2), or (j)(3) of this AD, which are not incorporated by reference in this AD. (1) Airbus Service Bulletin A330-25-3538, dated September 10, 2013. (2) Airbus Service Bulletin A330-25-3538, Revision 01, dated April 24, 2014. (3) Airbus Service Bulletin A340-25-4351, dated September 10, 2014. (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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (h)(2)(ii) of this AD, if Airbus Service Bulletin A330-25- 3538, Revision 02, dated April 24, 2014; or Airbus Service Bulletin A340-25-4351, Revision 01, dated January 31, 2014; contain procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures and tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from, using accepted methods in accordance with the operators maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0127, dated May 15, 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-2015-0083. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. [[Page 7992]] Issued in Renton, Washington, on January 30, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-02536 Filed 2-12-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 30 / Friday, February 13, 2015 / Proposed Rules 7989
(2) For service information identified in 11.43 and 11.45, by any of the following comments on the overall regulatory,
this AD, contact Airbus SAS, Airworthiness methods: economic, environmental, and energy
Office—EAL, 1 Rond Point Maurice Bellonte, • Federal eRulemaking Portal: Go to aspects of this proposed AD. We will
31707 Blagnac Cedex, France; telephone +33 http://www.regulations.gov. Follow the consider all comments received by the
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
instructions for submitting comments. closing date and may amend this
Internet http://www.airbus.com. You may • Fax: 202–493–2251. proposed AD based on those comments.
view this service information at the FAA, • Mail: U.S. Department of We will post all comments we
Transport Airplane Directorate, 1601 Lind Transportation, Docket Operations, M– receive, without change, to http://
Avenue SW., Renton, WA. For information 30, West Building Ground Floor, Room www.regulations.gov, including any
on the availability of this material at the W12–140, 1200 New Jersey Avenue SE., personal information you provide. We
FAA, call 425–227–1221. Washington, DC 20590. will also post a report summarizing each
Issued in Renton, Washington, on January • Hand Delivery: U.S. Department of substantive verbal contact we receive
30, 2015. Transportation, Docket Operations, M– about this proposed AD.
Jeffrey E. Duven, 30, West Building Ground Floor, Room
Manager, Transport Airplane Directorate, W12–140, 1200 New Jersey Avenue SE., Discussion
Aircraft Certification Service. Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except The European Aviation Safety Agency
[FR Doc. 2015–02537 Filed 2–12–15; 8:45 am]
Federal holidays. (EASA), which is the Technical Agent
BILLING CODE 4910–13–P for the Member States of the European
For service information identified in
this proposed AD, contact Airbus SAS, Union, has issued EASA Airworthiness
Airworthiness Office—EAL, 1 Rond Directive 2014–0127, dated May 15,
DEPARTMENT OF TRANSPORTATION
Point Maurice Bellonte, 31707 Blagnac 2014 (referred to after this as the
Federal Aviation Administration Cedex, France; telephone +33 5 61 93 36 Mandatory Continuing Airworthiness
96; fax +33 5 61 93 45 80; email Information, or ‘‘the MCAI’’), to correct
14 CFR Part 39 airworthiness.A330–A340@airbus.com; an unsafe condition for certain Airbus
Internet http://www.airbus.com. You Model A330–200, A330–200 Freighter,
[Docket No. FAA–2015–0083; Directorate may view this referenced service and A330–300 series airplanes; and all
Identifier 2014–NM–131–AD] information at the FAA, Transport A340–200, and A340–300 series
Airplane Directorate, 1601 Lind Avenue airplanes. The MCAI states:
RIN 2120–AA64
SW., Renton, WA. For information on During flight tests, high stress levels have
Airworthiness Directives; Airbus the availability of this material at the been measured on the bracket No 6 which
FAA, call 425–227–1221. attaches the cockpit instrument panel to the
Airplanes
aeroplane structure, apparently introduced
AGENCY: Federal Aviation Examining the AD Docket through the nose landing gear due to bumps
Administration (FAA), DOT. You may examine the AD docket on on the runway. Airbus determined that the
the Internet at http:// bracket does not sustain the fatigue loads
ACTION: Notice of proposed rulemaking
www.regulations.gov by searching for during the Design Service Goal (DSG). This
(NPRM).
and locating Docket No. FAA–2015– condition, if not detected and corrected,
SUMMARY: We propose to adopt a new combined with failure of the horizontal
0083; or in person at the Docket
airworthiness directive (AD) for certain beam, could lead to collapse of the cockpit
Management Facility between 9 a.m.
panel, possibly resulting in reduced control
Airbus Model A330–200, A330–200 and 5 p.m., Monday through Friday, of the aeroplane.
Freighter, and A330–300 series except Federal holidays. The AD docket To address this potential unsafe condition,
airplanes; and all A340–200 and A340– contains this proposed AD, the Airbus developed a program to inspect the
300 series airplanes. This proposed AD regulatory evaluation, any comments condition of the affected cockpit instrument
was prompted by reports that a bracket received, and other information. The panel bracket No 6, and designed a stronger
that attaches the cockpit instrument street address for the Docket Operations (reinforced titanium undrilled) bracket. The
panel to the airplane structure, does not office (telephone 800–647–5527) is in new bracket can be installed in-service
sustain the fatigue loads of the design the ADDRESSES section. Comments will through Airbus Service Bulletin (SB) A330–
service goal. This proposed AD would be available in the AD docket shortly 25–3548 or SB A340–25–4354, as applicable
require repetitive inspections of that after receipt. to aeroplane type.
bracket for cracking and to determine if FOR FURTHER INFORMATION CONTACT: For the reasons described above, this
both lugs are fully broken, an inspection Vladimir Ulyanov, Aerospace Engineer, [EASA] AD requires repetitive inspections of
for cracking of an adjacent bracket, if International Branch, ANM–116, the cockpit instrument panel bracket No 6
necessary, and corrective actions if and, depending on findings, the
Transport Airplane Directorate, FAA,
necessary. This AD would also provide accomplishment of applicable corrective
1601 Lind Avenue SW., Renton, WA actions. This [EASA] AD also provides the
an optional modification, which would 98057–3356; telephone 425–227–1138;
terminate the repetitive inspections. We installation of the stronger bracket as
fax 425–227–1149. optional terminating action for the repetitive
are proposing this AD to detect and
SUPPLEMENTARY INFORMATION: actions required by this [EASA] AD.
correct cracking on a bracket of the
cockpit instrument panel, which, Comments Invited
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
The corrective actions include replacing
combined with failure of the horizontal We invite you to send any written bracket No. 6 and bracket No. 7 with
beam, could lead to collapse of the relevant data, views, or arguments about serviceable parts, and repair, as
cockpit panel, and reduced this proposed AD. Send your comments applicable.
controllability of the airplane. to an address listed under the You may examine the MCAI in the
DATES: We must receive comments on ADDRESSES section. Include ‘‘Docket No. AD docket on the Internet at http://
this proposed AD by March 30, 2015. FAA–2015–0083; Directorate Identifier www.regulations.gov by searching for
ADDRESSES: You may send comments, 2014–NM–131–AD’’ at the beginning of and locating Docket No. FAA–2015–
using the procedures found in 14 CFR your comments. We specifically invite 0083.
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Related Service Information Under 1 include procedures and tests that are promoting safe flight of civil aircraft in
CFR Part 51 identified as RC (required for air commerce by prescribing regulations
Airbus has issued the following compliance) because these procedures for practices, methods, and procedures
service information. have a direct effect on detecting, the Administrator finds necessary for
• Airbus Service Bulletin A330–25– preventing, resolving, or eliminating an safety in air commerce. This regulation
3538, Revision 02, dated April 24, 2014, identified unsafe condition. is within the scope of that authority
As specified in a NOTE under the because it addresses an unsafe condition
which provides procedures for
Accomplishment Instructions of the that is likely to exist or develop on
inspection of cockpit instrument panel
specified service information, products identified in this rulemaking
bracket 6.
procedures and tests identified as RC action.
• Airbus Service Bulletin A330–25–
must be done to comply with the
3548, dated October 31, 2013, which Regulatory Findings
proposed AD. However, procedures and
provides procedures for reinforcement
tests that are not identified as RC are We determined that this proposed AD
of cockpit instrument panel bracket 6.
recommended. Those procedures and would not have federalism implications
• Airbus Service Bulletin A340–25–
tests that are not identified as RC may under Executive Order 13132. This
4351, Revision 01, dated January 31,
be deviated from using accepted proposed AD would not have a
2014, which provides procedures for
methods in accordance with the substantial direct effect on the States, on
inspection of cockpit instrument panel
operator’s maintenance or inspection the relationship between the national
bracket 6.
program without obtaining approval of Government and the States, or on the
• Airbus Service Bulletin A340–25–
an alternative method of compliance distribution of power and
4354, dated October 31, 2013, which
(AMOC), provided the procedures and responsibilities among the various
provides procedures for reinforcement
tests identified as RC can be done and levels of government.
of cockpit instrument panel bracket 6.
the airplane can be put back in a For the reasons discussed above, I
The actions described in this service
serviceable condition. Any substitutions certify this proposed regulation:
information are intended to correct the
or changes to procedures or tests 1. Is not a ‘‘significant regulatory
unsafe condition identified in the
identified as RC will require approval of action’’ under Executive Order 12866;
MCAI. This service information is
an AMOC.
reasonably available; see ADDRESSES for 2. Is not a ‘‘significant rule’’ under the
ways to access this service information. Costs of Compliance DOT Regulatory Policies and Procedures
FAA’s Determination and Requirements We estimate that this proposed AD (44 FR 11034, February 26, 1979);
of This Proposed AD affects 76 airplanes of U.S. registry. 3. Will not affect intrastate aviation in
We also estimate that it would take Alaska; and
This product has been approved by about 8 work-hours per product to 4. Will not have a significant
the aviation authority of another comply with the basic requirements of economic impact, positive or negative,
country, and is approved for operation this proposed AD. The average labor on a substantial number of small entities
in the United States. Pursuant to our rate is $85 per work-hour. Based on under the criteria of the Regulatory
bilateral agreement with the State of these figures, we estimate the cost of Flexibility Act.
Design Authority, we have been notified this proposed AD on U.S. operators to
of the unsafe condition described in the be $51,680, or $680 per product. List of Subjects in 14 CFR Part 39
MCAI and service information We have received no definitive data Air transportation, Aircraft, Aviation
referenced above. We are proposing this that would enable us to provide cost safety, Incorporation by reference,
AD because we evaluated all pertinent estimates for the follow-on repairs Safety.
information and determined an unsafe specified in this AD.
condition exists and is likely to exist or In addition, we estimate that any The Proposed Amendment
develop on other products of these same necessary follow-on replacements
type designs. Accordingly, under the authority
would take about 23 work-hours and delegated to me by the Administrator,
Explanation of ‘‘RC’’ Procedures and require parts costing $0, for a cost of the FAA proposes to amend 14 CFR part
Tests in Service Information $1,955 per product. We have no way of 39 as follows:
determining the number of aircraft that
The FAA worked in conjunction with might need these actions. PART 39—AIRWORTHINESS
industry, under the Airworthiness We estimate that the optional DIRECTIVES
Directives Implementation Aviation modification would take about 9 work
Rulemaking Committee (AD ARC), to hours and require parts costing $1,770, ■ 1. The authority citation for part 39
enhance the AD system. One for a cost of $2,535. continues to read as follows:
enhancement was a new process for
annotating which procedures and tests Authority for This Rulemaking Authority: 49 U.S.C. 106(g), 40113, 44701.
in the service information are required Title 49 of the United States Code § 39.13 [Amended]
for compliance with an AD. specifies the FAA’s authority to issue
Differentiating these procedures and rules on aviation safety. Subtitle I, ■ 2. The FAA amends § 39.13 by adding
tests from other tasks in the service section 106, describes the authority of the following new airworthiness
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
information is expected to improve an the FAA Administrator. ‘‘Subtitle VII: directive (AD):
owner’s/operator’s understanding of Aviation Programs,’’ describes in more Airbus: Docket No. FAA–2015–0083;
crucial AD requirements and help detail the scope of the Agency’s Directorate Identifier 2014–NM–131–AD.
provide consistent judgment in AD authority. (a) Comments Due Date
compliance. The actions specified in We are issuing this rulemaking under
We must receive comments by March 30,
Airbus Service Bulletin A330–25–3538, the authority described in ‘‘Subtitle VII, 2015.
Revision 02, dated April 24, 2014; and Part A, Subpart III, Section 44701:
Airbus Service Bulletin A340–25–4351, General requirements.’’ Under that (b) Affected ADs
Revision 01, dated January 31, 2014; section, Congress charges the FAA with None.
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![7992 Federal Register / Vol. 80, No. 30 / Friday, February 13, 2015 / Proposed Rules
Issued in Renton, Washington, on January Airworthiness Office—EAW, 1 Rond Mandatory Continuing Airworthiness
30, 2015. Point Maurice Bellonte, 31707 Blagnac Information, or ‘‘the MCAI’’), to correct
Jeffrey E. Duven, Cedex, France; telephone +33 5 61 93 36 an unsafe condition for certain Airbus
Manager, Transport Airplane Directorate, 96; fax +33 5 61 93 44 51; email Model A300 B4–2C, B4–103, and B4–
Aircraft Certification Service. account.airworth-eas@airbus.com; 203 airplanes; Airbus Model A300 B4–
[FR Doc. 2015–02536 Filed 2–12–15; 8:45 am] Internet http://www.airbus.com. You 600 series airplanes; and Airbus Model
BILLING CODE 4910–13–P may view this referenced service A300 B4–600R series airplanes. The
information at the FAA, Transport MCAI states:
Airplane Directorate, 1601 Lind Avenue During routine inspection on an A300–600
DEPARTMENT OF TRANSPORTATION SW., Renton, WA. For information on aeroplane, a crack was found in the right-
the availability of this material at the hand frame (FR) 40 forward fitting between
Federal Aviation Administration FAA, call 425–227–1221. stringer (STRG) 32 and STRG 33. The subject
Examining the AD Docket aeroplane had previously been modified, as
14 CFR Part 39
a crack prevention measure, in accordance
[Docket No. FAA–2015–0084; Directorate You may examine the AD docket on with Airbus SB A300–57–6053 (mod 10453).
Identifier 2014–NM–181–AD] the Internet at http:// To ensure the structural integrity of FR 40,
www.regulations.gov by searching for pending completion of the full root cause
RIN 2120–AA64 and locating Docket No. FAA–2015– analysis using a refined Finite Element
0084; or in person at the Docket Model (FEM), EASA issued AD 2009–0094
Airworthiness Directives; Airbus
Management Facility between 9 a.m. [dated April 21, 2009, http://
Airplanes
and 5 p.m., Monday through Friday, ad.easa.europa.eu/ad/2009–0094], to require,
AGENCY: Federal Aviation except Federal holidays. The AD docket a one-time Detailed Visual Inspection (DVI)
Administration (FAA), DOT. contains this proposed AD, the of A300 and A300–600 aeroplanes on which
ACTION: Notice of proposed rulemaking regulatory evaluation, any comments Airbus SB A300–53–0297 or SB A300–57–
(NPRM). received, and other information. The 6053, as applicable, was embodied as a crack
street address for the Docket Operations prevention measure.
SUMMARY: We propose to adopt a new office (telephone 800–647–5527) is in Thereafter, cracks were found during
airworthiness directive (AD) for certain the ADDRESSES section. Comments will maintenance check in the FR 40 forward
Airbus Model A300 B4–2C, B4–103, and fitting on two aeroplanes, one A300 with
be available in the AD docket shortly
B4–203 airplanes; Airbus Model A300 Airbus SB A300–53–0297 embodied and one
after receipt.
B4–600 series airplanes; and Airbus A300–600 with Airbus SB A300–57–6053
FOR FURTHER INFORMATION CONTACT: Dan embodied. EASA AD 2009–0094 had been
Model A300 B4–600R series airplanes. Rodina, Aerospace Engineer, accomplished on both aeroplanes.
This proposed AD was prompted by International Branch, ANM–116, Consequently, EASA issued AD 2011–0163
reports indicating that, on airplanes that Transport Airplane Directorate, FAA, [dated August 30, 2011, http://
received a certain repair following crack 1601 Lind Avenue SW., Renton, WA ad.easa.europa.eu/ad/2011-0163],
findings, cracks can re-initiate. This 98057–3356; telephone 425–227–2125; superseding EASA AD 2009–0094, to require,
proposed AD would require repetitive fax 425–227–1149. for aeroplanes modified preventively,
inspections for cracking of the frame SUPPLEMENTARY INFORMATION: repetitive DVI of the FR 40 forward fitting
(FR) 40 forward fittings for airplanes (without nut removal), accomplishment of a
previously repaired. We are proposing Comments Invited one-time Eddy Current (EC) inspection or
this AD to detect and correct cracking We invite you to send any written liquid penetrant inspection of this area (with
on the FR 40 forward fittings, which relevant data, views, or arguments about nut removal) and, depending on findings, the
could result in rupture of the forward this proposed AD. Send your comments accomplishment of associated corrective
fittings and reduction of in-flight actions.
to an address listed under the
structural strength. A detailed FEM study was recently
ADDRESSES section. Include ‘‘Docket No.
completed which demonstrated that, on
DATES: We must receive comments on FAA–2015–0084; Directorate Identifier aeroplanes repaired following crack findings
this proposed AD by March 30, 2015. 2014–NM–181–AD’’ at the beginning of in accordance with the instructions of Airbus
ADDRESSES: You may send comments, your comments. We specifically invite SB A300–53–0297 or SB A300–57–6053 at
using the procedures found in 14 CFR comments on the overall regulatory, any revision, as applicable, cracks can re-
11.43 and 11.45, by any of the following economic, environmental, and energy initiate.
methods: aspects of this proposed AD. We will For the reasons described above, this
• Federal eRulemaking Portal: Go to consider all comments received by the [EASA] AD requires repetitive inspections of
http://www.regulations.gov. Follow the closing date and may amend this the FR 40 forward fitting for aeroplanes
instructions for submitting comments. proposed AD based on those comments. repaired in accordance with the instructions
• Fax: 202–493–2251. We will post all comments we of Airbus SB A300–53–0297 or SB A300–57–
• Mail: U.S. Department of receive, without change, to http:// 6053 following crack findings.
Transportation, Docket Operations, M– www.regulations.gov, including any
The corrective actions include a
30, West Building Ground Floor, Room personal information you provide. We
repair using a method approved by the
W12–140, 1200 New Jersey Avenue SE., will also post a report summarizing each
Manager, International Branch, ANM–
Washington, DC 20590. substantive verbal contact we receive
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
• Hand Delivery: U.S. Department of 116, Transport Airplane Directorate,
about this proposed AD.
Transportation, Docket Operations, M– FAA; or the European Aviation Safety
30, West Building Ground Floor, Room Discussion Agency (EASA); or Airbus’s EASA
W12–140, 1200 New Jersey Avenue SE., The European Aviation Safety Agency Design Organization Approval (DOA).
Washington, DC, between 9 a.m. and 5 (EASA), which is the Technical Agent You may examine the MCAI in the
p.m., Monday through Friday, except for the Member States of the European AD docket on the Internet at http://
Federal holidays. Union, has issued EASA Airworthiness www.regulations.gov by searching for
For service information identified in Directive 2014–0199, dated September and locating Docket No. FAA–2015–
this proposed AD, contact Airbus SAS, 05, 2014 (referred to after this as the 0084.
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Document Created: 2015-12-18 13:18:12
Document Modified: 2015-12-18 13:18:12
| 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 March 30, 2015. | |
| Contact | Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. | |
| FR Citation | 80 FR 7989 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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