80 FR 8571 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 32 (February 18, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 32 (February 18, 2015)
| Page Range | 8571-8575 | |
| FR Document | 2015-02922 |
[Federal Register Volume 80, Number 32 (Wednesday, February 18, 2015)] [Proposed Rules] [Pages 8571-8575] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-02922] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-0243; Directorate Identifier 2014-NM-114-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for all [[Page 8572]] Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4- 600R series airplanes, and A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. This proposed AD was prompted by reports of cracked aluminum support struts of the trimmable horizontal stabilizer (THS) caused by stress corrosion. This proposed AD would require inspections to identify the part number of each support strut, repetitive inspections for cracking of the THS support strut ends, installation of reinforcing clamps on strut ends, and replacement of support struts, if necessary. We are proposing this AD to detect and correct cracked THS support struts, which could lead to the rupture of all four support struts making the remaining structure unable to carry limit loads, which could result in loss of the THS and reduced control of the airplane. DATES: We must receive comments on this proposed AD by April 6, 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--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 0243; 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: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 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-2015-0243; Directorate Identifier 2014-NM-114-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 2014-0164, dated July 11, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes, and A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. The MCAI states: During scheduled maintenance, several Trimmable Horizontal Stabilizer (THS) support struts were found cracked at the strut ends. The THS is supported and articulated at frame (FR) 91 in the tail cone. Lateral movement is prevented by four diagonal support struts. Investigations revealed that the cracks were caused by stress corrosion and propagated from the inside to the outside of the strut. This condition, if not detected and corrected, could lead to the rupture of all four THS support struts at FR91, which would make the remaining structure unable to carry limit loads, potentially resulting in loss of the Horizontal Tail Plane. To address this unsafe condition, EASA issued [EASA] AD 2014- 0121 [http://ad.easa.europa.eu/ad/2014-0121] to require repetitive High Frequency Eddy Current (HFEC) inspections of the THS support strut ends, installation of reinforcing clamps on strut ends and, depending on findings, replacement of damaged support struts. Installation of reinforcing clamps on strut ends is considered a temporary solution pending introduction of a re-designed support strut. Since that [EASA] AD was issued, it was discovered that the [EASA] AD appeared to also require HFEC inspections of steel struts, which are not prone to cracking. The unsafe condition exists only on support struts made of aluminum, which were introduced through Airbus modification (mod) 06101, but may also have been installed in service as replacement parts on aeroplanes in pre-mod 06101 configuration. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2014-0121, which is superseded, and clarifies the need for an initial identification of the support struts installed on aeroplanes in pre-mod 06101 configuration. The related Airbus Service Bulletins (SB) remain unchanged. 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- 0243. Relevant Service Information Under 1 CFR Part 51 Airbus has issued the following service information. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. Airbus Service Bulletin A300-53-0394, dated February 14, 2014. This service information describes procedures for reinforcing the support struts of the THS at frame 91 in the fuselage tail section of Airbus Model A300 series airplanes. Airbus Service Bulletin A300-53-0395, dated February 14, 2014. This service information describes procedures for inspecting for cracking of the support struts of the THS at frame 91 in the fuselage tail section of Airbus Model A300 series airplanes. Airbus Service Bulletin A300-53-6172, dated February 14, 2014. This service information describes procedures for reinforcing the support struts of the THS at frame 91 in the fuselage tail section of Airbus Model A300-600 series airplanes. [[Page 8573]] Airbus Service Bulletin A300-53-6174, dated February 14, 2014. This service information describes procedures for inspecting for cracking of the support struts of the THS at frame 91 in the fuselage tail section of Airbus Model A300-600 series airplanes. Airbus Service Bulletin A310-53-2136, dated February 14, 2014. This service information describes procedures for reinforcing the support struts of the THS at frame 91 in the fuselage tail section of Airbus Model A310 series airplanes. Airbus Service Bulletin A310-53-2137, dated February 14, 2014. This service information describes procedures for inspecting for cracking of the support struts of the THS at frame 91 in the fuselage tail section of Airbus Model A310 series airplanes. 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. Differences Between This Proposed AD and the MCAI or Service Information Unlike the procedures described in Airbus Service Bulletin A300-53- 0395; Airbus Service Bulletin A300-53-6174; and Airbus Service Bulletin A310-53-2137; each dated February 14, 2014; this proposed AD would not permit further flight if cracks are detected in the aluminum support strut ends of the trimmable horizontal stabilizer at frame 91. We have determined that, because of the safety implications and consequences associated with that cracking, any cracked aluminum support strut ends of the trimmable horizontal stabilizer must be repaired or modified before further flight. This difference has been coordinated with EASA and Airbus. Costs of Compliance We estimate that this proposed AD affects 174 airplanes of U.S. registry. We also estimate that it would take about 5 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 $2,100 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $439,350, or $2,525 per product. In addition, we estimate that any necessary follow-on actions would take about 15 work-hours and require parts costing $10,000, for a cost of $11,275 per product. We have no way of determining the number of aircraft that might need these actions. Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this proposed AD is 2120-0056. The paperwork cost associated with this proposed AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this proposed AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES-200. 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-2015-0243; Directorate Identifier 2014-NM- 114-AD. (a) Comments Due Date We must receive comments by April 6, 2015. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes specified in paragraphs (c)(1) through (c)(6) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4- 103, and B4-203 airplanes. (2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes. (3) Airbus Model A300 B4-605R and B4-622R airplanes. (4) Airbus Model A300 F4-605R and F4-622R airplanes. [[Page 8574]] (5) Airbus Model A300 C4-605R Variant F airplanes. (6) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by reports of cracked aluminum support struts of the trimmable horizontal stabilizer (THS) caused by stress corrosion. We are issuing this AD to detect and correct cracked THS support struts, which could lead to the rupture of all four support struts making the remaining structure unable to carry limit loads, which could result in loss of the THS and reduced control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection for Part Number For airplanes in pre-modification 06101 configuration: Within 12 months after the effective date of this AD, do an inspection to identify the part number (P/N) of each support strut installed on the trimmable horizontal stabilizer (THS) at frame (FR) 91, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraphs (g)(1) through (g)(3) of this AD. A review of airplane maintenance records is acceptable in lieu of this inspection, provided those records can be relied upon for that purpose and the part number can be positively identified from that review. If no aluminum strut(s) having P/N R21449, R21449D, R21449G, or R21449H is found during any inspection required by this paragraph no further action is required by this AD for that horizontal stabilizer, except for paragraph (l) of this AD. (1) For Airbus Model A300 series airplanes: Airbus Service Bulletin A300-53-0395, dated February 14, 2014. (2) For Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes): Airbus Service Bulletin A300-53- 6174, dated February 14, 2014. (3) For Airbus Model A310 series airplanes: Airbus Service Bulletin A310-53-2137, dated February 14, 2014. (h) Repetitive High Frequency Eddy Current (HFEC) Inspections For airplanes in post-modification 06101 configuration; and for airplanes in pre-modification 06101 configuration on which one or more aluminum support strut(s) having P/N R21449, P/N R21449D, P/N R21449G, or P/N R21449H was found during the inspection by paragraph (g) of this AD: Within the applicable compliance times specified in paragraphs (h)(1), (h)(2), or (h)(3) of this AD, do an HFEC inspection for cracking of the aluminum THS support strut ends at FR 91, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraphs (g)(1) through (g)(3) of this AD. Reinforcing clamps already installed on strut ends must be removed before accomplishing the HFEC inspection and re-installed after the inspection, in accordance with the Accomplishment Instructions of the applicable service bulletin specified in paragraphs (g)(1) through (g)(3) of this AD. Repeat the inspection thereafter at intervals not to exceed 24 months. (1) For airplanes having manufacturer serial number (MSN) 0499 through MSN 0747 inclusive (post-mod 06101): Within 12 months after the effective date of this AD. (2) For airplanes having MSN 0748 through MSN 0878 inclusive (post-mod 06101): Within 18 months after the effective date of this AD. (3) For airplanes having MSN 0001 through MSN 0498 inclusive (pre-mod 06101) having one or more aluminum struts: Within 24 months after the effective date of this AD. (i) Installation of Reinforcing Clamps Concurrently with the initial HFEC inspection required by paragraph (h) of this AD, identify struts having P/N R21449, P/N R21449D, P/N R21449G, or P/N R21449H with no reinforcing clamps previously installed, and before next flight, install reinforcing clamps on each strut end, in accordance with the Accomplishment Instructions of the applicable service bulletin specified in paragraphs (i)(1) through (i)(3) of this AD. (1) For Airbus Model A300 series airplanes: Airbus Service Bulletin A300-53-0394, dated February 14, 2014. (2) For Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes): Airbus Service Bulletin A300-53- 6172, dated February 14, 2014. (3) For Airbus Model A310 series airplanes: Airbus Service Bulletin A310-53-2136, dated February 14, 2014. (j) Corrective Actions If, during any inspection required by paragraph (h) of this AD, any cracking is found, before further flight, replace the affected THS support strut(s) with serviceable struts and install clamps on each strut end, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraphs (g)(1) through (g)(3) of this AD. (k) Clarification Installation of reinforcing clamps as required by paragraph (i) of this AD, and the replacement of support struts and/or the installation of clamps as required by paragraph (j) of this AD, do not constitute terminating action for the repetitive inspections required by paragraph (h) of this AD. (l) Reporting At the applicable time specified in paragraphs (l)(1) and (l)(2) of this AD: After accomplishment of any inspection required by paragraphs (g) and (h) of this AD, report all inspection results to Airbus, including no findings, in accordance with the Accomplishment Instructions of the applicable service bulletins specified in paragraphs (g)(1) through (g)(3) of this AD, and paragraphs (i)(1) through (i)(3) of this AD. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (m) 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: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-2125; 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 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. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) European [[Page 8575]] Aviation Safety Agency Airworthiness Directive 2014-0164, dated July 11, 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-2015-0243. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on February 2, 2015. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-02922 Filed 2-17-15; 8:45 am] BILLING CODE 4910-13-P
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(b) Affected ADs Amendment 39–17280 (77 FR 73908, paragraph (m)(1) of this AD. Information may
This AD replaces AD 2012–24–10, December 12, 2012), with revised service be emailed to: 9-ANM-Seattle-ACO-AMOC-
Amendment 39–17280 (77 FR 73908, information. Within 60 months after January Requests@faa.gov.
December 12, 2012). 16, 2013 (the effective date of AD 2012–24– (2) Before using any approved AMOC,
10), except as provided by paragraph (j) of notify your appropriate principal inspector,
(c) Applicability this AD: Replace the duct assembly with a or lacking a principal inspector, the manager
This AD applies to The Boeing Company new duct assembly, do wiring changes, and of the local flight standards district office/
Model 747–400 and –400F series airplanes, route certain wire bundles, in accordance certificate holding district office.
certificated in any category, as identified in with the Accomplishment Instructions of (3) An AMOC that provides an acceptable
Boeing Alert Service Bulletin 747–21A2523, Boeing Alert Service Bulletin 747–21A2523, level of safety may be used for any repair
Revision 2, dated June 7, 2013. Revision 1, dated October 3, 2011; or Boeing required by this AD if it is approved by
Alert Service Bulletin 747–21A2523, Boeing Commercial Airplanes Organization
(d) Subject Revision 2, dated June 7, 2013. As of the Designation Authorization (ODA) that has
Air Transport Association (ATA) of effective date of this AD, only Boeing Alert been authorized by the Manager, Seattle
America Code 21, Air Conditioning; 31, Service Bulletin 747–21A2523, Revision 2, ACO, to make those findings. For a repair
Instruments. dated June 7, 2013, may be used to method to be approved, the repair must meet
accomplish the actions required by this the certification basis of the airplane, and the
(e) Unsafe Condition paragraph. approval must specifically refer to this AD.
This AD was prompted by reports of (4) AMOCs approved for AD 2012–24–10,
intermittent or blank displays of a certain (i) New Installation of Pressure Switch Amendment 39–17280 (77 FR 73908,
integrated display unit (IDU) in the flight Bracket and Altitude Pressure Switch December 12, 2012), are approved as AMOCs
deck. We are issuing this AD to prevent IDU Within 60 months after the effective date for the corresponding provisions of
malfunctions, which could affect the ability of this AD: Install a new or serviceable paragraphs (g) and (h) of this AD.
of the flightcrew to read primary displays for pressure switch bracket and a new or
airplane attitude, altitude, or airspeed, and serviceable altitude pressure switch on the (m) Related Information
consequently reduce the ability of the forward side of the station 400 bulkhead, do (1) For more information about this AD,
flightcrew to maintain control of the airplane. wiring changes, route certain wire bundles, contact Ana Martinez Hueto, Aerospace
install a new hose assembly, and perform a Engineer, Cabin Safety and Environmental
(f) Compliance leak check and a functional logic test, in Systems Branch, ANM–150S, FAA, Seattle
Comply with this AD within the accordance with the Accomplishment Aircraft Certification Office (ACO), 1601 Lind
compliance times specified, unless already Instructions of the service information Avenue SW., Renton, WA 98057–3356;
done. specified in paragraph (i)(1) or (i)(2) of this phone: 425–917–6592; fax: 425–917–6591;
AD, as applicable. email: ana.m.hueto@faa.gov.
(g) Retained Software Update
(1) For Model 747–400F series airplanes: (2) For service information identified in
This paragraph restates the requirements of Boeing Alert Service Bulletin 747–21–2532, this AD, contact Boeing Commercial
paragraph (g) of AD 2012–24–10, dated February 13, 2014. Airplanes, Attention: Data & Services
Amendment 39–17280 (77 FR 73908, (2) For Model 747–400BCF series Management, P.O. Box 3707, MC 2H–65,
December 12, 2012), with revised service airplanes: Boeing Alert Service Bulletin 747– Seattle, WA 98124–2207; telephone 206–
information. Within 12 months after January 21–2533, dated February 13, 2014. 544–5000, extension 1; fax 206–766–5680;
16, 2013 (the effective date of AD 2012–24– Internet https://www.myboeingfleet.com. You
10), except as provided by paragraph (j) of (j) Actions for Group 21 Airplanes
may view this referenced service information
this AD: Install integrated display system For Group 21 airplanes, as identified in at the FAA, Transport Airplane Directorate,
software, in accordance with the Boeing Alert Service Bulletin 747–21A2523, 1601 Lind Avenue SW., Renton, Washington.
Accomplishment Instructions of Boeing Alert Revision 2, dated June 7, 2013, do the actions For information on the availability of this
Service Bulletin 747–21A2523, Revision 1, specified in paragraphs (j)(1) and (j)(2) of this material at the FAA, call 425–227–1221.
dated October 3, 2011; or Boeing Alert AD, in accordance with the Accomplishment
Service Bulletin 747–21A2523, Revision 2, Instructions of Boeing Alert Service Bulletin Issued in Renton, Washington, on February
dated June 7, 2013. As of the effective date 747–21A2523, Revision 2, dated June 7, 2, 2015.
of this AD, only Boeing Alert Service Bulletin 2013. Dionne Palermo,
747–21A2523, Revision 2, dated June 7, (1) Within 12 months after the effective Acting Manager, Transport Airplane
2013, may be used to accomplish the actions date of this AD, install integrated display Directorate, Aircraft Certification Service.
required by this paragraph. system software.
Note 1 to paragraph (g) and (j) of this AD: [FR Doc. 2015–02925 Filed 2–17–15; 8:45 am]
(2) Within 60 months after the effective
Boeing Alert Service Bulletin 747–21A2523, date of this AD, replace the duct assembly BILLING CODE 4910–13–P
Revision 1, dated October 3, 2011; and with a new duct assembly, do wiring
Boeing Alert Service Bulletin 747–21A2523, changes, and route certain wire bundles.
Revision 2, dated June 7, 2013; refer to DEPARTMENT OF TRANSPORTATION
Boeing Service Bulletin 747–31–2426, dated (k) Credit for Previous Actions
July 29, 2010 (for airplanes with Rolls-Royce This paragraph provides credit for actions Federal Aviation Administration
engines); Boeing Service Bulletin 747–31– required by paragraphs (g) and (h) of this AD,
2427, dated July 29, 2010 (for airplanes with if those actions were performed before the 14 CFR Part 39
General Electric engines); and Boeing Service effective date of this AD using Boeing Alert
Bulletin 747–31–2428, dated July 29, 2010 Service Bulletin 747–21A2523, Revision 1, [Docket No. FAA–2015–0243; Directorate
(for airplanes with Pratt & Whitney engines); dated October 3, 2011. Identifier 2014–NM–114–AD]
as additional sources of guidance for the
(l) Alternative Methods of Compliance RIN 2120–AA64
software installation specified by paragraph
(AMOCs)
(g) of this AD. Boeing Service Bulletin 747–
(1) The Manager, Seattle Aircraft Airworthiness Directives; Airbus
mstockstill on DSK4VPTVN1PROD with PROPOSALS
31–2426, dated July 29, 2010; Boeing Service
Bulletin 747–31–2427, dated July 29, 2010; Certification Office (ACO), FAA, has the Airplanes
and Boeing Service Bulletin 747–31–2428, authority to approve AMOCs for this AD, if
requested using the procedures found in 14 AGENCY: Federal Aviation
dated July 29, 2010; are not incorporated by
reference in this AD. CFR 39.19. In accordance with 14 CFR 39.19, Administration (FAA), DOT.
send your request to your principal inspector ACTION: Notice of proposed rulemaking
(h) Retained Duct Assembly Replacement or local Flight Standards District Office, as (NPRM).
and Wiring Changes appropriate. If sending information directly
This paragraph restates the requirements of to the manager of the ACO, send it to the SUMMARY: We propose to adopt a new
paragraph (h) of AD 2012–24–10, attention of the person identified in airworthiness directive (AD) for all
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Airbus Model A300 series airplanes; Management Facility between 9 a.m. Investigations revealed that the cracks were
Model A300 B4–600, B4–600R, and F4– and 5 p.m., Monday through Friday, caused by stress corrosion and propagated
600R series airplanes, and A300 C4– except Federal holidays. The AD docket from the inside to the outside of the strut.
This condition, if not detected and
605R Variant F airplanes (collectively contains this proposed AD, the corrected, could lead to the rupture of all
called Model A300–600 series regulatory evaluation, any comments four THS support struts at FR91, which
airplanes); and Model A310 series received, and other information. The would make the remaining structure unable
airplanes. This proposed AD was street address for the Docket Operations to carry limit loads, potentially resulting in
prompted by reports of cracked office (telephone 800–647–5527) is in loss of the Horizontal Tail Plane.
aluminum support struts of the the ADDRESSES section. Comments will To address this unsafe condition, EASA
trimmable horizontal stabilizer (THS) be available in the AD docket shortly issued [EASA] AD 2014–0121 [http://
ad.easa.europa.eu/ad/2014-0121] to require
caused by stress corrosion. This after receipt.
repetitive High Frequency Eddy Current
proposed AD would require inspections (HFEC) inspections of the THS support strut
FOR FURTHER INFORMATION CONTACT: Dan
to identify the part number of each ends, installation of reinforcing clamps on
Rodina, Aerospace Engineer,
support strut, repetitive inspections for strut ends and, depending on findings,
International Branch, ANM–116,
cracking of the THS support strut ends, replacement of damaged support struts.
Transport Airplane Directorate, FAA, Installation of reinforcing clamps on strut
installation of reinforcing clamps on
1601 Lind Avenue SW., Renton, WA ends is considered a temporary solution
strut ends, and replacement of support
98057–3356; telephone 425–227–2125; pending introduction of a re-designed
struts, if necessary. We are proposing
fax 425–227–1149. support strut.
this AD to detect and correct cracked Since that [EASA] AD was issued, it was
THS support struts, which could lead to SUPPLEMENTARY INFORMATION: discovered that the [EASA] AD appeared to
the rupture of all four support struts Comments Invited also require HFEC inspections of steel struts,
making the remaining structure unable which are not prone to cracking. The unsafe
to carry limit loads, which could result We invite you to send any written condition exists only on support struts made
in loss of the THS and reduced control relevant data, views, or arguments about of aluminum, which were introduced
of the airplane. through Airbus modification (mod) 06101,
this proposed AD. Send your comments
but may also have been installed in service
DATES: We must receive comments on to an address listed under the as replacement parts on aeroplanes in pre-
this proposed AD by April 6, 2015. ADDRESSES section. Include ‘‘Docket No. mod 06101 configuration.
ADDRESSES: You may send comments, FAA–2015–0243; Directorate Identifier For the reason described above, this
using the procedures found in 14 CFR 2014–NM–114–AD’’ at the beginning of [EASA] AD retains the requirements of EASA
your comments. We specifically invite AD 2014–0121, which is superseded, and
11.43 and 11.45, by any of the following
comments on the overall regulatory, clarifies the need for an initial identification
methods: of the support struts installed on aeroplanes
• Federal eRulemaking Portal: Go to economic, environmental, and energy
in pre-mod 06101 configuration. The related
http://www.regulations.gov. Follow the aspects of this proposed AD. We will Airbus Service Bulletins (SB) remain
instructions for submitting comments. consider all comments received by the unchanged.
• Fax: 202–493–2251. closing date and may amend this
proposed AD based on those comments. You may examine the MCAI in the
• Mail: U.S. Department of AD docket on the Internet at http://
Transportation, Docket Operations, M– We will post all comments we www.regulations.gov by searching for
30, West Building Ground Floor, Room receive, without change, to http:// and locating Docket No. FAA–2015–
W12–140, 1200 New Jersey Avenue SE., www.regulations.gov, including any 0243.
Washington, DC 20590. personal information you provide. We
• Hand Delivery: U.S. Department of will also post a report summarizing each Relevant Service Information Under 1
Transportation, Docket Operations, M– substantive verbal contact we receive CFR Part 51
30, West Building Ground Floor, Room about this proposed AD. Airbus has issued the following
W12–140, 1200 New Jersey Avenue SE., service information. The actions
Discussion
Washington, DC, between 9 a.m. and 5 described in this service information are
p.m., Monday through Friday, except The European Aviation Safety Agency intended to correct the unsafe condition
Federal holidays. (EASA), which is the Technical Agent identified in the MCAI.
For service information identified in for the Member States of the European • Airbus Service Bulletin A300–53–
this proposed AD, contact Airbus SAS, Union, has issued EASA Airworthiness 0394, dated February 14, 2014. This
Airworthiness Office—EAW, 1 Rond Directive 2014–0164, dated July 11, service information describes
Point Maurice Bellonte, 31707 Blagnac 2014 (referred to after this as the procedures for reinforcing the support
Cedex, France; telephone +33 5 61 93 36 Mandatory Continuing Airworthiness struts of the THS at frame 91 in the
96; fax +33 5 61 93 44 51; email Information, or ‘‘the MCAI’’), to correct fuselage tail section of Airbus Model
account.airworth-eas@airbus.com; an unsafe condition for all Airbus A300 series airplanes.
Internet http://www.airbus.com. You Model A300 series airplanes; Model • Airbus Service Bulletin A300–53–
may view this referenced service A300 B4–600, B4–600R, and F4–600R 0395, dated February 14, 2014. This
information at the FAA, Transport series airplanes, and A300 C4–605R service information describes
Airplane Directorate, 1601 Lind Avenue Variant F airplanes (collectively called procedures for inspecting for cracking of
SW., Renton, WA. For information on Model A300–600 series airplanes); and the support struts of the THS at frame
91 in the fuselage tail section of Airbus
mstockstill on DSK4VPTVN1PROD with PROPOSALS
the availability of this material at the Model A310 series airplanes. The MCAI
FAA, call 425–227–1221. states: Model A300 series airplanes.
• Airbus Service Bulletin A300–53–
Examining the AD Docket During scheduled maintenance, several 6172, dated February 14, 2014. This
Trimmable Horizontal Stabilizer (THS)
You may examine the AD docket on support struts were found cracked at the strut
service information describes
the Internet at http:// ends. The THS is supported and articulated procedures for reinforcing the support
www.regulations.gov by searching for at frame (FR) 91 in the tail cone. Lateral struts of the THS at frame 91 in the
and locating Docket No. FAA–2015– movement is prevented by four diagonal fuselage tail section of Airbus Model
0243; or in person at the Docket support struts. A300–600 series airplanes.
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![Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Proposed Rules 8573
• Airbus Service Bulletin A300–53– this proposed AD. The average labor Regulatory Findings
6174, dated February 14, 2014. This rate is $85 per work-hour. Required We determined that this proposed AD
service information describes parts would cost about $2,100 per would not have federalism implications
procedures for inspecting for cracking of product. Based on these figures, we under Executive Order 13132. This
the support struts of the THS at frame estimate the cost of this proposed AD on proposed AD would not have a
91 in the fuselage tail section of Airbus U.S. operators to be $439,350, or $2,525 substantial direct effect on the States, on
Model A300–600 series airplanes. per product. the relationship between the national
• Airbus Service Bulletin A310–53– In addition, we estimate that any Government and the States, or on the
2136, dated February 14, 2014. This necessary follow-on actions would take distribution of power and
service information describes about 15 work-hours and require parts responsibilities among the various
procedures for reinforcing the support costing $10,000, for a cost of $11,275 levels of government.
struts of the THS at frame 91 in the per product. We have no way of For the reasons discussed above, I
fuselage tail section of Airbus Model determining the number of aircraft that certify this proposed regulation:
A310 series airplanes. might need these actions. 1. Is not a ‘‘significant regulatory
• Airbus Service Bulletin A310–53– action’’ under Executive Order 12866;
2137, dated February 14, 2014. This Paperwork Reduction Act 2. Is not a ‘‘significant rule’’ under the
service information describes DOT Regulatory Policies and Procedures
procedures for inspecting for cracking of A federal agency may not conduct or (44 FR 11034, February 26, 1979);
the support struts of the THS at frame sponsor, and a person is not required to 3. Will not affect intrastate aviation in
91 in the fuselage tail section of Airbus respond to, nor shall a person be subject Alaska; and
Model A310 series airplanes. This to penalty for failure to comply with a 4. Will not have a significant
service information is reasonably collection of information subject to the economic impact, positive or negative,
available; see ADDRESSES for ways to requirements of the Paperwork on a substantial number of small entities
access this service information. Reduction Act unless that collection of under the criteria of the Regulatory
information displays a current valid Flexibility Act.
FAA’s Determination and Requirements OMB control number. The control
of This Proposed AD number for the collection of information List of Subjects in 14 CFR Part 39
This product has been approved by required by this proposed AD is 2120– Air transportation, Aircraft, Aviation
the aviation authority of another 0056. The paperwork cost associated safety, Incorporation by reference,
country, and is approved for operation with this proposed AD has been Safety.
in the United States. Pursuant to our detailed in the Costs of Compliance
The Proposed Amendment
bilateral agreement with the State of section of this document and includes
Design Authority, we have been notified time for reviewing instructions, as well Accordingly, under the authority
of the unsafe condition described in the as completing and reviewing the delegated to me by the Administrator,
MCAI and service information collection of information. Therefore, all the FAA proposes to amend 14 CFR part
referenced above. We are proposing this reporting associated with this proposed 39 as follows:
AD because we evaluated all pertinent AD is mandatory. Comments concerning
information and determined an unsafe the accuracy of this burden and PART 39—AIRWORTHINESS
condition exists and is likely to exist or suggestions for reducing the burden DIRECTIVES
develop on other products of these same should be directed to the FAA at 800 ■ 1. The authority citation for part 39
type designs. Independence Ave. SW., Washington, continues to read as follows:
DC 20591, ATTN: Information
Differences Between This Proposed AD Authority: 49 U.S.C. 106(g), 40113, 44701.
Collection Clearance Officer, AES–200.
and the MCAI or Service Information
Authority for This Rulemaking § 39.13 [Amended]
Unlike the procedures described in
■ 2. The FAA amends § 39.13 by adding
Airbus Service Bulletin A300–53–0395; Title 49 of the United States Code the following new airworthiness
Airbus Service Bulletin A300–53–6174; specifies the FAA’s authority to issue directive (AD):
and Airbus Service Bulletin A310–53– rules on aviation safety. Subtitle I,
2137; each dated February 14, 2014; this Airbus: Docket No. FAA–2015–0243;
section 106, describes the authority of Directorate Identifier 2014–NM–114–AD.
proposed AD would not permit further the FAA Administrator. ‘‘Subtitle VII:
flight if cracks are detected in the Aviation Programs,’’ describes in more (a) Comments Due Date
aluminum support strut ends of the detail the scope of the Agency’s We must receive comments by April 6,
trimmable horizontal stabilizer at frame authority. 2015.
91. We have determined that, because of (b) Affected ADs
the safety implications and We are issuing this rulemaking under
consequences associated with that the authority described in ‘‘Subtitle VII, None.
cracking, any cracked aluminum Part A, Subpart III, Section 44701: (c) Applicability
support strut ends of the trimmable General requirements.’’ Under that This AD applies to the Airbus airplanes
horizontal stabilizer must be repaired or section, Congress charges the FAA with specified in paragraphs (c)(1) through (c)(6)
modified before further flight. This promoting safe flight of civil aircraft in of this AD, certificated in any category, all
air commerce by prescribing regulations
mstockstill on DSK4VPTVN1PROD with PROPOSALS
difference has been coordinated with manufacturer serial numbers.
EASA and Airbus. for practices, methods, and procedures (1) Airbus Model A300 B2–1A, B2–1C,
the Administrator finds necessary for B2K–3C, B2–203, B4–2C, B4–103, and B4–
Costs of Compliance safety in air commerce. This regulation 203 airplanes.
is within the scope of that authority (2) Airbus Model A300 B4–601, B4–603,
We estimate that this proposed AD B4–620, and B4–622 airplanes.
affects 174 airplanes of U.S. registry. because it addresses an unsafe condition (3) Airbus Model A300 B4–605R and B4–
We also estimate that it would take that is likely to exist or develop on 622R airplanes.
about 5 work-hours per product to products identified in this rulemaking (4) Airbus Model A300 F4–605R and F4–
comply with the basic requirements of action. 622R airplanes.
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![Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Proposed Rules 8575
Aviation Safety Agency Airworthiness 11.43 and 11.45, by any of the following comments on the overall regulatory,
Directive 2014–0164, dated July 11, 2014, for methods: economic, environmental, and energy
related information. This MCAI may be • Federal eRulemaking Portal: Go to aspects of this proposed AD. We will
found in the AD docket on the Internet at http://www.regulations.gov. Follow the consider all comments received by the
http://www.regulations.gov by searching for
and locating Docket No. FAA–2015–0243.
instructions for submitting comments. closing date and may amend this
(2) For service information identified in • Fax: 202–493–2251. proposed AD based on those comments.
this AD, contact Airbus SAS, Airworthiness • Mail: U.S. Department of We will post all comments we
Office—EAW, 1 Rond Point Maurice Transportation, Docket Operations, M– receive, without change, to http://
Bellonte, 31707 Blagnac Cedex, France; 30, West Building Ground Floor, Room www.regulations.gov, including any
telephone +33 5 61 93 36 96; fax +33 5 61 W12–140, 1200 New Jersey Avenue SE., personal information you provide. We
93 44 51; email account.airworth-eas@ Washington, DC 20590. will also post a report summarizing each
airbus.com; Internet http://www.airbus.com. • Hand Delivery: U.S. Department of substantive verbal contact we receive
You may view this service information at the Transportation, Docket Operations, M–
FAA, Transport Airplane Directorate, 1601 about this proposed AD.
Lind Avenue SW., Renton, WA. For
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE., Discussion
information on the availability of this
material at the FAA, call 425–227–1221. Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except As described in FAA Advisory
Issued in Renton, Washington, on February
Federal holidays. Circular 120 104 (http://www.faa.gov/
2, 2015. documentLibrary/media/Advisory_
For service information identified in
Dionne Palermo,
this proposed AD, contact Airbus SAS, Circular/120-104.pdf), several programs
Acting Manager, Transport Airplane Airworthiness Office—EAW, 1 Rond have been developed to support
Directorate, Aircraft Certification Service.
Point Maurice Bellonte, 31707 Blagnac initiatives that will ensure the
[FR Doc. 2015–02922 Filed 2–17–15; 8:45 am]
Cedex, France; telephone +33 5 61 93 36 continued airworthiness of aging
BILLING CODE 4910–13–P 96; fax +33 5 61 93 44 51; email airplane structure. The last element of
account.airworth-eas@airbus.com; those initiatives is the requirement to
Internet http://www.airbus.com. You establish a LOV of the engineering data
DEPARTMENT OF TRANSPORTATION
may view this referenced service that support the structural maintenance
information at the FAA, Transport program under 14 CFR 26.21. This
Federal Aviation Administration proposed AD is the result of an
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on assessment of the previously established
14 CFR Part 39 programs by Airbus during the process
the availability of this material at the
[Docket No. FAA–2015–0086; Directorate FAA, call 425–227–1221. of establishing the LOV for Airbus
Identifier 2014–NM–191–AD] Model A310–203 airplanes. The actions
Examining the AD Docket specified in this proposed AD are
RIN 2120–AA64
You may examine the AD docket on necessary to complete certain programs
the Internet at http:// to ensure the continued airworthiness of
Airworthiness Directives; Airbus aging airplane structure and to support
Airplanes www.regulations.gov by searching for
and locating Docket No. FAA–2015– an airplane reaching its LOV.
AGENCY: Federal Aviation 0086; or in person at the Docket The European Aviation Safety Agency
Administration (FAA), DOT. Management Facility between 9 a.m. (EASA), which is the Technical Agent
ACTION: Notice of proposed rulemaking and 5 p.m., Monday through Friday, for the Member States of the European
(NPRM). except Federal holidays. The AD docket Union, has issued EASA Airworthiness
contains this proposed AD, the Directive 2014–0191, dated August 29,
SUMMARY: We propose to adopt a new regulatory evaluation, any comments 2014 (referred to after this as the
airworthiness directive (AD) for all received, and other information. The Mandatory Continuing Airworthiness
Airbus Model A310–203 airplanes. This street address for the Docket Operations Information, or ‘‘the MCAI’’), to correct
proposed AD is intended to complete office (telephone 800–647–5527) is in an unsafe condition for all Airbus
certain mandated programs intended to the ADDRESSES section. Comments will Model A310–203 airplanes. The MCAI
support the airplane reaching its limit of be available in the AD docket shortly states:
validity (LOV) of the engineering data after receipt. During fatigue analysis performed in the
that support the established structural FOR FURTHER INFORMATION CONTACT: Dan scope of the Extended Service Goal, taking
maintenance program. This proposed Rodina, Aerospace Engineer, into account the certification loads and the
AD was prompted by reports that side International Branch, ANM–116, new lift-off loads, Airbus determined that
link clevis bolts of the front engine Transport Airplane Directorate, FAA, side link clevis engine mount bolts do not
mount do not meet the Design Service meet the Design Service Goal (DSG)
1601 Lind Avenue SW., Renton,
Goal (DSG) requirements on airplanes requirements on aeroplanes equipped with
Washington 98057–3356; telephone CF6–80A3 engines.
equipped with General Electric 425–227–2125; fax 425–227–1149.
Company CF6–80A3 engines. This This condition, if not corrected, could lead
SUPPLEMENTARY INFORMATION: to failure of the front engine mount, possibly
proposed AD would require repetitive resulting in-flight separation of the engine
replacement of all side link clevis Comments Invited from the aeroplane.
mstockstill on DSK4VPTVN1PROD with PROPOSALS
engine mount bolts. We are proposing We invite you to send any written To address this potential unsafe condition,
this AD to prevent failure of the front relevant data, views, or arguments about Airbus issued Service Bulletin (SB) A310–
engine mount, and consequent possible this proposed AD. Send your comments 71–2038 to introduce a life limit on the side
departure of the engine. link clevis engine mount bolts.
to an address listed under the For the reason described above, this
DATES: We must receive comments on ADDRESSES section. Include ‘‘Docket No. [EASA] AD requires implementation of the
this proposed AD by April 6, 2015. FAA–2015–0086; Directorate Identifier new life limit and replacement of all side
ADDRESSES: You may send comments, 2014–NM–191–AD’’ at the beginning of link clevis engine mount bolts that have
using the procedures found in 14 CFR your comments. We specifically invite exceeded the new limit.
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Document Created: 2018-02-16 11:10:28
Document Modified: 2018-02-16 11:10:28
| 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 April 6, 2015. | |
| Contact | Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. | |
| FR Citation | 80 FR 8571 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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