81 FR 3301 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 13 (January 21, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 13 (January 21, 2016)
| Page Range | 3301-3304 | |
| FR Document | 2016-00376 |
[Federal Register Volume 81, Number 13 (Thursday, January 21, 2016)] [Rules and Regulations] [Pages 3301-3304] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-00376] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2014-1045; Directorate Identifier 2014-NM-031-AD; Amendment 39-18372; AD 2016-01-13] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for all Airbus Model A310 and Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes; and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). This AD was prompted by a report of skin disbonding and damage found on the composite side panel of the rudder, located between the rudder core and skin of a previously repaired area. This AD requires an inspection for disbonding or damage of certain rudders, and related investigative actions and corrective actions if necessary. We are issuing this AD to detect and correct disbonding and damage of the rudder, which could result in reduced structural integrity of the rudder and consequent reduced controllability of the airplane. DATES: This AD is effective February 25, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 25, 2016. ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-1045; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this final rule, 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 [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014- 1045. 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: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A310 and Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300- 600 series airplanes) series airplanes. The NPRM published in the Federal Register on January 23, 2015 (80 FR 3525). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0026, dated January 28, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A310 and Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes; and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). The MCAI states: A case of skin disbonding was reported on a composite side of a rudder installed on an A310 aeroplane. The investigation results revealed that this disbonding started from a skin panel area previously repaired in-service in accordance with the Structural Repair Manual (SRM). The initial damage has been identified as a disbonding between the core and the repaired area. This damage may not be visually detectable and likely propagates during normal operation due to the variation of pressure during ground-air-ground cycles. This condition, if not detected and corrected, could affect the structural integrity of the rudder, possibly resulting in reduced control of the aeroplane. For the reasons described above, this [EASA] AD requires a one- time thermography inspection of each repaired rudder or rudder whose maintenance records are incomplete and, depending on findings, accomplishment of applicable corrective and follow-up actions. Related investigative actions include doing a pulse thermography inspection for disbonding or damage of the left- and right-hand rudder side shells; a core ventilation through the inner skin, an elasticity laminate checker or ultrasonic inspection around the identified repairs in the booster area, and around identified fluid ingress; and a Tap test inspection of the glass fiber reinforced plastic area to identify skin-to-core disbonding and on identified repairs. Corrective actions include repairing or replacing any disbonded or damaged rudder. Depending on configuration and inspection results, the repetitive inspection intervals are 750 or 1,000 flight cycles, or 500 flight hours or 4 months, whichever occurs later. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-1045-0002. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (80 FR 3525, January 23, 2015) and the FAA's response to each comment. No Justification for Issuing NPRM (80 FR 3525, January 23, 2015) FedEx stated that Airbus has not provided any data or analysis showing the de-validated SRM procedures in the proposed AD (80 FR 3525, January 23, 2015) as inadequate. FedEx noted that one finding on a Model A310 airplane with skin disbonding and damage found on the composite side panel of the [[Page 3302]] rudder caused the de-validation of all Model A300 and A310 airplanes with rudder side shell repairs, and mandatory inspections of all rudders repaired using the structural repair manual (SRM). FedEx added that a heavy burden is being placed on operators with very little justification from the manufacturer. FedEx stated that Airbus has not provided new validated SRM procedures, yet FedEx is being required to inspect all rudders without having any available, developed repairs; instead repairs would need to be done 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). FedEx does not agree with the de- validation of the SRM procedures and mandating inspections of the entire fleet of airplanes, based on one finding. We infer that the commenter is asking for justification to support issuing this final rule. We acknowledge the commenter's concerns. However, the safety risk of undetected rudder skin disbonding that may not be detectable visually and could propagate during normal operation due to the variation of aerodynamic pressure during ground-air-ground cycles is sufficient to require the proposed actions. We also acknowledge that Airbus does not have new SRM procedures available, partially due to the unknown size and location of previously accomplished SRM repairs and the type of skin disbonding that may be identified that will result in each repair needing to be evaluated individually. Therefore, we have determined that inspections are necessary if an applicable SRM repair has been done, or if maintenance records are not available or are incomplete. The service information provides procedures for the detailed inspections; therefore, using a method approved by the FAA, EASA, or Airbus's EASA DOA is necessary only for repairs. We have determined it is necessary to proceed with issuing this final rule as proposed. Request To Allow Using Future Revisions of the SRM for Rudder Repairs FedEx asked that paragraph (i) of the proposed AD (80 FR 3525, January 23, 2015) be revised to allow a composite side shell panel repair on any rudder using future revisions of the SRM procedure identified in Figure A-GBBAA (Sheet 01 and 02) or Figure A-GBCAA (Sheet 02) of Airbus Service Bulletin A310-55-2051; or Figure A-GBBAA (Sheet 01, 02, or 03) or Figure A-GBCAA (Sheet 02 or 04) of Airbus Service Bulletin A300-55-6050. FedEx stated that when Airbus revalidates the SRM procedures, FedEx won't be able to use those procedures for the repair because it is not allowed per paragraph (i) of the proposed AD. We do not agree with the request. Although we understand the FedEx concerns, allowing the use of later revisions of service documents in an AD is not allowed by the Office of the Federal Register's regulations. However, after the manufacturer validates a later revision of the SRM procedures that provides an acceptable level of safety we can evaluate the later revision of the SRM as an alternative method of compliance, in accordance with the procedures specified in paragraph (m)(1) of this AD. Paragraph (i) of this AD only prohibits the use of specific SRM procedures identified in that paragraph. We have not changed this AD in this regard. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM (80 FR 3525, January 23, 2015) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 3525, January 23, 2015). Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletins A300-55-2051 and A310-55-6050, both Revision 01, both dated August 20, 2014. The service information describes procedures for inspecting the left- and right-hand rudder side shells for disbonding or damage, and related investigative actions and corrective actions if necessary. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 199 airplanes of U.S. registry. We also estimate that it will take about 4 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $0 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $67,660, or $340 per product. We have received no definitive data that would enable us to provide a cost estimate for the on-condition actions specified in this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under 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. Examining the AD Docket You may examine the AD docket on the Internet at: http://www.regulations.gov/#!docketDetail;D=FAA-2014-1045; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal [[Page 3303]] holidays. The AD docket contains this 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2016-01-13 Airbus: Amendment 39-18372; Docket No. FAA-2014-1045; Directorate Identifier 2014-NM-031-AD. (a) Effective Date This AD is effective February 25, 2016. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes; Model A300 B4-601, B4-603, B4- 620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; and Model A300 F4-605R, F4-622R, and A300 C4-605R Variant F airplanes; certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 55, Stabilizers. (e) Reason This AD was prompted by a report of skin disbonding and damage found on the composite side panel of the rudder, located between the rudder core and skin of a previously repaired area. We are issuing this AD to detect and correct disbonding and damage of the rudder, which could result in reduced structural integrity of the rudder, and consequent reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Rudder Assembly Identification Within 4 months after the effective date of this AD: Check the applicable rudder maintenance records to determine if any composite side shell panel repair has been done since first installation of the rudder, and do the applicable actions specified in paragraph (g)(1) or (g)(2) of this AD at the time specified in paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A300-55-6050, or A310-55- 2051, both Revision 01, both dated August 20, 2014; as applicable, except as provided by paragraph (j)(3) of this AD. (1) If a repair is identified based on the maintenance records: Perform a rudder thermography inspection of the repaired area only for disbonding or damage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-55-6050, or A310-55- 2051, both Revision 01, both dated August 20, 2014; as applicable. (2) If the rudder maintenance records are unavailable or incomplete: Perform a rudder thermography inspection of the complete side shell panels to identify and mark the repair locations for disbonding or damage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-55-6050, or A310-55- 2051, both Revision 01, both dated August 20, 2014; as applicable. (h) Related Investigative Actions/Repair or Replace If any disbonding or damage is found during any inspection required by paragraph (g)(1) or (g)(2) of this AD: Do the actions required by paragraphs (h)(1) and (h)(2) of this AD, as applicable. (1) At the time specified in paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A300-55-6050, or A310-55-2051, both Revision 01, both dated August 20, 2014; as applicable, except as required by paragraph (j)(1) of this AD; do the applicable related investigative actions identified in Tables 3, 4A, 4B, 4C, 4D, and 5 of paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A300-55-6050, or A310-55-2051, both Revision 01, both dated August 20, 2014; as applicable, to determine the type and extent of the disbonding or damage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-55-6050, or A310-55-2051, both Revision 01, both dated August 20, 2014; as applicable. Repeat the applicable inspection at the time specified in paragraph 1.E., ``Compliance'' of Airbus Service Bulletin A300-55-6050, or A310-55-2051, both Revision 01, both dated August 20, 2014; as applicable. (2) Before further flight: Repair any disbonding or damage found during any inspection required by paragraph (h)(1) of this AD, or replace any affected rudder, as applicable, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-55-6050, or A310-55-2051, both Revision 01, both dated August 20, 2014; as applicable, except as required by paragraph (j)(4) of this AD. (i) Repair Using Structural Repair Manual (SRM) Procedure Not Allowed As of the effective date of this AD, do not accomplish a composite side shell panel repair on any rudder using an SRM procedure identified in Figure A-GBBAA (Sheet 01 and 02) or Figure A-GBCAA (Sheet 02) of Airbus Service Bulletin A310-55-2051; or Figure A-GBBAA (Sheet 01, 02, or 03) or Figure A-GBCAA (Sheet 02 or 04) of Airbus Service Bulletin A300-55-6050; as applicable. (j) Exceptions to Service Information (1) Where Airbus Service Bulletins A300-55-6050; and A310-55- 2051; both Revision 01, both dated August 20, 2014; specify a compliance time ``from original service bulletin issue date,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where Airbus Service Bulletins A300-55-6050; and A310-55- 2051 both Revision 01, both dated August 20, 2014; specify to contact Airbus for appropriate action: Before further flight, repair 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). (3) Airplanes on which a rudder is installed having a serial number that is not in the range HF-1005 through HF-1323, inclusive; HF-1325, HF-1327, HF-1329, HF-1331, HF-1332, HF-1340, TS-1324, TS- 1326, TS-1328, TS-1330, TS-1333 through TS-1339, inclusive; TS-1341 through TS-1420, inclusive; or TS-2001 through TS-2197, inclusive; are not affected by the requirements of paragraphs (g) and (h) of this AD, provided that no repairs have been done in accordance with the applicable SRM specified in paragraph (i) of this AD on the composite side shell panel of that rudder since installation. (4) The compliance time for the initial detailed inspection of the restored area for loose or lost tape identified in Tables 3 and 4 of paragraph 1.E., ``Compliance,'' of Airbus Service Bulletins A300-55-6050 and A310-55-2051, both Revision 01, both dated August 20, 2014; specifies ``within 500 FH or 4 months after closing holes.'' This AD requires this action within 500 flight hours or 4 months, whichever occurs later, after the holes are closed. (k) 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 Airbus Service Bulletin A300-55-6050, or A310-55-2051, both dated September 11, 2012; as applicable; which are not incorporated by reference in this AD. (l) Parts Installation Limitations As of the effective date of this AD, no person may install any affected rudder on any airplane, unless the actions required by paragraphs (g) and (h) of this AD have been accomplished. (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 [[Page 3304]] 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: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (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 EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0026, dated January 28, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-1045-0002. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(3) and (o)(4) of this AD. (o) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Airbus Service Bulletin A300-55-6050, Revision 01, dated August 20, 2014. (ii) Airbus Service Bulletin A310-55-2051, Revision 01, dated August 20, 2014. (3) 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 [email protected]; Internet http://www.airbus.com. (4) 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on December 31, 2015. Phil Forde, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-00376 Filed 1-20-16; 8:45 am] BILLING CODE 4910-13-P
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(3) For service information identified in The Director of the Federal Register Model A300–600 series airplanes). The
this AD, contact Bombardier, Inc., 400 Côte- approved the incorporation by reference MCAI states:
Vertu Road West, Dorval, Québec H4S 1Y9, of certain publications listed in this AD
Canada; telephone 514–855–5000; fax 514– A case of skin disbonding was reported on
as of February 25, 2016. a composite side of a rudder installed on an
855–7401; email thd.crj@
aero.bombardier.com; Internet http:// ADDRESSES: You may examine the AD A310 aeroplane.
www.bombardier.com. docket on the Internet at http:// The investigation results revealed that this
(4) You may view this service information www.regulations.gov/ disbonding started from a skin panel area
at the FAA, Transport Airplane Directorate, previously repaired in-service in accordance
#!docketDetail;D=FAA-2014-1045; or in with the Structural Repair Manual (SRM).
1601 Lind Avenue SW., Renton, WA. For person at the Docket Management
information on the availability of this The initial damage has been identified as
Facility, U.S. Department of a disbonding between the core and the
material at the FAA, call 425–227–1221.
(5) You may view this service information
Transportation, Docket Operations, M– repaired area. This damage may not be
that is incorporated by reference at the 30, West Building Ground Floor, Room visually detectable and likely propagates
National Archives and Records W12–140, 1200 New Jersey Avenue SE., during normal operation due to the variation
Administration (NARA). For information on Washington, DC. of pressure during ground-air-ground cycles.
the availability of this material at NARA, call For service information identified in This condition, if not detected and
202–741–6030, or go to: http:// corrected, could affect the structural integrity
this final rule, contact Airbus SAS, of the rudder, possibly resulting in reduced
www.archives.gov/federal-register/cfr/ibr- Airworthiness Office—EAW, 1 Rond
locations.html. control of the aeroplane.
Point Maurice Bellonte, 31707 Blagnac For the reasons described above, this
Issued in Renton, Washington, on January Cedex, France; telephone +33 5 61 93 36 [EASA] AD requires a one-time
6, 2016. 96; fax +33 5 61 93 44 51; email thermography inspection of each repaired
Victor Wicklund, account.airworth-eas@airbus.com; rudder or rudder whose maintenance records
Acting Manager, Transport Airplane Internet http://www.airbus.com. You are incomplete and, depending on findings,
Directorate, Aircraft Certification Service. may view this referenced service accomplishment of applicable corrective and
[FR Doc. 2016–00630 Filed 1–20–16; 8:45 am] information at the FAA, Transport follow-up actions.
BILLING CODE 4910–13–P Airplane Directorate, 1601 Lind Avenue Related investigative actions include
SW., Renton, WA. For information on doing a pulse thermography inspection
the availability of this material at the for disbonding or damage of the left-
DEPARTMENT OF TRANSPORTATION FAA, call 425–227–1221. It is also and right-hand rudder side shells; a core
available on the Internet at http:// ventilation through the inner skin, an
Federal Aviation Administration www.regulations.gov by searching for elasticity laminate checker or ultrasonic
and locating Docket No. FAA–2014– inspection around the identified repairs
14 CFR Part 39 1045. in the booster area, and around
[Docket No. FAA–2014–1045; Directorate identified fluid ingress; and a Tap test
FOR FURTHER INFORMATION CONTACT: Dan
Identifier 2014–NM–031–AD; Amendment inspection of the glass fiber reinforced
Rodina, Aerospace Engineer,
39–18372; AD 2016–01–13] plastic area to identify skin-to-core
International Branch, ANM–116,
disbonding and on identified repairs.
RIN 2120–AA64 Transport Airplane Directorate, FAA,
Corrective actions include repairing or
1601 Lind Avenue SW., Renton, WA
Airworthiness Directives; Airbus replacing any disbonded or damaged
98057–3356; telephone 425–227–2125;
Airplanes rudder.
fax 425–227–1149.
Depending on configuration and
AGENCY: Federal Aviation SUPPLEMENTARY INFORMATION: inspection results, the repetitive
Administration (FAA), DOT. inspection intervals are 750 or 1,000
Discussion
ACTION: Final rule. flight cycles, or 500 flight hours or 4
We issued a notice of proposed months, whichever occurs later.
SUMMARY: We are adopting a new rulemaking (NPRM) to amend 14 CFR You may examine the MCAI in the
airworthiness directive (AD) for all part 39 by adding an AD that would AD docket on the Internet at http://
Airbus Model A310 and Airbus Model apply to all Airbus Model A310 and www.regulations.gov/
A300 B4–600, B4–600R, and F4–600R Airbus Model A300 B4–600, B4–600R, #!documentDetail;D=FAA-2014-1045-
series airplanes; and Model A300 C4– and F4–600R series airplanes, and 0002.
605R Variant F airplanes (collectively Model A300 C4–605R Variant F
called Model A300–600 series airplanes (collectively called Model Comments
airplanes). This AD was prompted by a A300–600 series airplanes) series We gave the public the opportunity to
report of skin disbonding and damage airplanes. The NPRM published in the participate in developing this AD. The
found on the composite side panel of Federal Register on January 23, 2015 following presents the comments
the rudder, located between the rudder (80 FR 3525). received on the NPRM (80 FR 3525,
core and skin of a previously repaired The European Aviation Safety Agency January 23, 2015) and the FAA’s
area. This AD requires an inspection for (EASA), which is the Technical Agent response to each comment.
disbonding or damage of certain for the Member States of the European
rudders, and related investigative Union, has issued EASA Airworthiness No Justification for Issuing NPRM (80
actions and corrective actions if Directive 2014–0026, dated January 28, FR 3525, January 23, 2015)
necessary. We are issuing this AD to 2014 (referred to after this as the FedEx stated that Airbus has not
jstallworth on DSK7TPTVN1PROD with RULES
detect and correct disbonding and Mandatory Continuing Airworthiness provided any data or analysis showing
damage of the rudder, which could Information, or ‘‘the MCAI’’), to correct the de-validated SRM procedures in the
result in reduced structural integrity of an unsafe condition for all Airbus proposed AD (80 FR 3525, January 23,
the rudder and consequent reduced Model A310 and Airbus Model A300 2015) as inadequate. FedEx noted that
controllability of the airplane. B4–600, B4–600R, and F4–600R series one finding on a Model A310 airplane
DATES: This AD is effective February 25, airplanes; and Model A300 C4–605R with skin disbonding and damage found
2016. Variant F airplanes (collectively called on the composite side panel of the
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holidays. The AD docket contains this maintenance records to determine if any (Sheet 01 and 02) or Figure A–GBCAA (Sheet
AD, the regulatory evaluation, any composite side shell panel repair has been 02) of Airbus Service Bulletin A310–55–
comments received, and other done since first installation of the rudder, 2051; or Figure A–GBBAA (Sheet 01, 02, or
and do the applicable actions specified in 03) or Figure A–GBCAA (Sheet 02 or 04) of
information. The street address for the Airbus Service Bulletin A300–55–6050; as
paragraph (g)(1) or (g)(2) of this AD at the
Docket Operations office (telephone time specified in paragraph 1.E., applicable.
800–647–5527) is in the ADDRESSES ‘‘Compliance,’’ of Airbus Service Bulletin
section. (j) Exceptions to Service Information
A300–55–6050, or A310–55–2051, both
Revision 01, both dated August 20, 2014; as (1) Where Airbus Service Bulletins A300–
List of Subjects in 14 CFR Part 39 55–6050; and A310–55–2051; both Revision
applicable, except as provided by paragraph
Air transportation, Aircraft, Aviation (j)(3) of this AD. 01, both dated August 20, 2014; specify a
safety, Incorporation by reference, (1) If a repair is identified based on the compliance time ‘‘from original service
Safety. maintenance records: Perform a rudder bulletin issue date,’’ this AD requires
thermography inspection of the repaired area compliance within the specified compliance
Adoption of the Amendment only for disbonding or damage, in accordance time after the effective date of this AD.
with the Accomplishment Instructions of (2) Where Airbus Service Bulletins A300–
Accordingly, under the authority 55–6050; and A310–55–2051 both Revision
delegated to me by the Administrator, Airbus Service Bulletin A300–55–6050, or
A310–55–2051, both Revision 01, both dated 01, both dated August 20, 2014; specify to
the FAA amends 14 CFR part 39 as contact Airbus for appropriate action: Before
August 20, 2014; as applicable.
follows: (2) If the rudder maintenance records are further flight, repair using a method
unavailable or incomplete: Perform a rudder approved by the Manager, International
PART 39—AIRWORTHINESS thermography inspection of the complete Branch, ANM–116, Transport Airplane
DIRECTIVES side shell panels to identify and mark the Directorate, FAA; or the European Aviation
repair locations for disbonding or damage, in Safety Agency (EASA); or Airbus’s EASA
■ 1. The authority citation for part 39 accordance with the Accomplishment Design Organization Approval (DOA).
continues to read as follows: Instructions of Airbus Service Bulletin A300– (3) Airplanes on which a rudder is
55–6050, or A310–55–2051, both Revision installed having a serial number that is not
Authority: 49 U.S.C. 106(g), 40113, 44701.
01, both dated August 20, 2014; as in the range HF–1005 through HF–1323,
§ 39.13 [Amended] applicable. inclusive; HF–1325, HF–1327, HF–1329, HF–
1331, HF–1332, HF–1340, TS–1324, TS–
■ 2. The FAA amends § 39.13 by adding (h) Related Investigative Actions/Repair or 1326, TS–1328, TS–1330, TS–1333 through
the following new airworthiness Replace TS–1339, inclusive; TS–1341 through TS–
directive (AD): If any disbonding or damage is found 1420, inclusive; or TS–2001 through TS–
during any inspection required by paragraph 2197, inclusive; are not affected by the
2016–01–13 Airbus: Amendment 39–18372;
(g)(1) or (g)(2) of this AD: Do the actions requirements of paragraphs (g) and (h) of this
Docket No. FAA–2014–1045; Directorate
required by paragraphs (h)(1) and (h)(2) of AD, provided that no repairs have been done
Identifier 2014–NM–031–AD.
this AD, as applicable. in accordance with the applicable SRM
(a) Effective Date (1) At the time specified in paragraph 1.E., specified in paragraph (i) of this AD on the
This AD is effective February 25, 2016. ‘‘Compliance,’’ of Airbus Service Bulletin composite side shell panel of that rudder
A300–55–6050, or A310–55–2051, both since installation.
(b) Affected ADs (4) The compliance time for the initial
Revision 01, both dated August 20, 2014; as
None. detailed inspection of the restored area for
applicable, except as required by paragraph
loose or lost tape identified in Tables 3 and
(c) Applicability (j)(1) of this AD; do the applicable related
4 of paragraph 1.E., ‘‘Compliance,’’ of Airbus
investigative actions identified in Tables 3,
This AD applies to all Airbus Model A310– Service Bulletins A300–55–6050 and A310–
4A, 4B, 4C, 4D, and 5 of paragraph 1.E.,
203, –204, –221, –222, –304, –322, –324, and 55–2051, both Revision 01, both dated
‘‘Compliance,’’ of Airbus Service Bulletin
–325 airplanes; Model A300 B4–601, B4–603, August 20, 2014; specifies ‘‘within 500 FH or
A300–55–6050, or A310–55–2051, both
B4–620, and B4–622 airplanes; Model A300 4 months after closing holes.’’ This AD
Revision 01, both dated August 20, 2014; as
B4–605R and B4–622R airplanes; and Model requires this action within 500 flight hours
applicable, to determine the type and extent
A300 F4–605R, F4–622R, and A300 C4–605R or 4 months, whichever occurs later, after the
of the disbonding or damage, in accordance holes are closed.
Variant F airplanes; certificated in any with the Accomplishment Instructions of
category. Airbus Service Bulletin A300–55–6050, or (k) Credit for Previous Actions
(d) Subject A310–55–2051, both Revision 01, both dated This paragraph provides credit for actions
Air Transport Association (ATA) of August 20, 2014; as applicable. Repeat the required by paragraphs (g) and (h) of this AD,
America Code 55, Stabilizers. applicable inspection at the time specified in if those actions were performed before the
paragraph 1.E., ‘‘Compliance’’ of Airbus effective date of this AD using Airbus Service
(e) Reason Service Bulletin A300–55–6050, or A310–55– Bulletin A300–55–6050, or A310–55–2051,
This AD was prompted by a report of skin 2051, both Revision 01, both dated August both dated September 11, 2012; as
disbonding and damage found on the 20, 2014; as applicable. applicable; which are not incorporated by
composite side panel of the rudder, located (2) Before further flight: Repair any reference in this AD.
between the rudder core and skin of a disbonding or damage found during any
inspection required by paragraph (h)(1) of (l) Parts Installation Limitations
previously repaired area. We are issuing this
AD to detect and correct disbonding and this AD, or replace any affected rudder, as As of the effective date of this AD, no
damage of the rudder, which could result in applicable, in accordance with the person may install any affected rudder on
reduced structural integrity of the rudder, Accomplishment Instructions of Airbus any airplane, unless the actions required by
and consequent reduced controllability of the Service Bulletin A300–55–6050, or A310–55– paragraphs (g) and (h) of this AD have been
airplane. 2051, both Revision 01, both dated August accomplished.
20, 2014; as applicable, except as required by
(m) Other FAA AD Provisions
jstallworth on DSK7TPTVN1PROD with RULES
(f) Compliance paragraph (j)(4) of this AD.
Comply with this AD within the The following provisions also apply to this
(i) Repair Using Structural Repair Manual AD:
compliance times specified, unless already
(SRM) Procedure Not Allowed (1) Alternative Methods of Compliance
done.
As of the effective date of this AD, do not (AMOCs): The Manager, International
(g) Rudder Assembly Identification accomplish a composite side shell panel Branch, ANM–116, Transport Airplane
Within 4 months after the effective date of repair on any rudder using an SRM Directorate, FAA, has the authority to
this AD: Check the applicable rudder procedure identified in Figure A–GBBAA approve AMOCs for this AD, if requested
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![3304 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations
using the procedures found in 14 CFR 39.19. Issued in Renton, Washington, on Renton, WA. For information on the
In accordance with 14 CFR 39.19, send your December 31, 2015. availability of this material at the FAA,
request to your principal inspector or local Phil Forde, call 425–227–1221. It is also available
Flight Standards District Office, as Acting Manager, Transport Airplane on the Internet at http://
appropriate. If sending information directly Directorate, Aircraft Certification Service. www.regulations.gov by searching for
to the International Branch, send it to ATTN:
Dan Rodina, Aerospace Engineer,
[FR Doc. 2016–00376 Filed 1–20–16; 8:45 am] and locating Docket No. FAA–2015–
International Branch, ANM–116, Transport BILLING CODE 4910–13–P 0081.
Airplane Directorate, FAA 1601 Lind Avenue FOR FURTHER INFORMATION CONTACT:
SW., Renton, WA 98057–3356; telephone Cesar Gomez, Aerospace Engineer,
425–227–2125; fax 425–227–1149. DEPARTMENT OF TRANSPORTATION
Airframe and Mechanical Systems
Information may be emailed to: 9-ANM-116-
Federal Aviation Administration Branch, ANE–171, FAA, New York
AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate Aircraft Certification Office (ACO), 1600
principal inspector, or lacking a principal 14 CFR Part 39 Stewart Avenue, Suite 410, Westbury,
inspector, the manager of the local flight NY 11590; telephone 516–228–7318; fax
[Docket No. FAA–2015–0081; Directorate 516–794–5531.
standards district office/certificate holding
Identifier 2014–NM–170–AD; Amendment
district office. SUPPLEMENTARY INFORMATION:
39–18371; AD 2016–01–12]
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective RIN 2120–AA64 Discussion
actions from a manufacturer, the action must
We issued a notice of proposed
be accomplished using a method approved Airworthiness Directives; Bombardier,
by the Manager, International Branch, ANM– rulemaking (NPRM) to amend 14 CFR
Inc. Airplanes
116, Transport Airplane Directorate, FAA; or part 39 by adding an AD that would
EASA; or Airbus’s EASA DOA. If approved AGENCY: Federal Aviation apply to certain Bombardier, Inc. Model
by the DOA, the approval must include the Administration (FAA), Department of BD–700–1A10 and BD–700–1A11
DOA-authorized signature. Transportation (DOT). airplanes. The NPRM published in the
(n) Related Information ACTION: Final rule. Federal Register on January 26, 2015
(80 FR 3924). The NPRM was prompted
(1) Refer to Mandatory Continuing by reports of fluid entry and
SUMMARY: We are adopting a new
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0026, dated airworthiness directive (AD) for certain accumulation in the aft equipment bay.
January 28, 2014, for related information. Bombardier, Inc. Model BD–700–1A10 The NPRM proposed to require
This MCAI may be found in the AD docket and BD–700–1A11 airplanes. This AD modifying the aft equipment bay. We
on the Internet at http:// was prompted by reports of fluid entry are issuing this AD to prevent excessive
www.regulations.gov/ and accumulation in the aft equipment quantities of flammable fluid
#!documentDetail;D=FAA-2014-1045-0002. bay. This AD requires modifying the aft accumulation in the aft equipment bay.
(2) Service information identified in this equipment bay. We are issuing this AD Flammable fluid entry and
AD that is not incorporated by reference is to prevent excessive quantities of accumulation in the aft equipment bay,
available at the addresses specified in flammable fluid accumulation in the aft in excessive quantities, could exceed
paragraphs (o)(3) and (o)(4) of this AD. safe levels maintained by the drainage
equipment bay. Flammable fluid entry
(o) Material Incorporated by Reference and accumulation in the aft equipment and ventilation system.
(1) The Director of the Federal Register bay, in excessive quantities, could Transport Canada Civil Aviation,
approved the incorporation by reference exceed safe levels maintained by the which is the aviation authority for
(IBR) of the service information listed in this drainage and ventilation system. Canada, has issued Canadian
paragraph under 5 U.S.C. 552(a) and 1 CFR DATES: This AD becomes effective Airworthiness Directive CF–2014–25,
part 51. February 25, 2016. dated August 7, 2014 (referred to after
(2) You must use this service information this as the Mandatory Continuing
as applicable to do the actions required by
The Director of the Federal Register
approved the incorporation by reference Airworthiness Information, or ‘‘the
this AD, unless the AD specifies otherwise.
of certain publications listed in this AD MCAI’’), to correct an unsafe condition
(i) Airbus Service Bulletin A300–55–6050,
Revision 01, dated August 20, 2014. as of February 25, 2016. for certain Bombardier, Inc. Model BD–
(ii) Airbus Service Bulletin A310–55–2051, ADDRESSES: You may examine the AD
700–1A10 and BD–700–1A11 airplanes.
Revision 01, dated August 20, 2014. docket on the Internet at http:// The MCAI states:
(3) For service information identified in www.regulations.gov/ There have been two reports of fluid entry
this AD, contact Airbus SAS, Airworthiness #!docketDetail;D=FAA-2015-0081; or in and accumulation in the aft equipment bay.
Office—EAW, 1 Rond Point Maurice The leaked fluid in the first incident was fuel
Bellonte, 31707 Blagnac Cedex, France;
person at the Docket Management
Facility, U.S. Department of and the fluid in the second incident was test
telephone +33 5 61 93 36 96; fax +33 5 61 dye. Further investigation revealed that
93 44 51; email account.airworth-eas@ Transportation, Docket Operations, M– leaked fluid from the aft fuel tank drain
airbus.com; Internet http://www.airbus.com. 30, West Building Ground Floor, Room entered the bay through the slot in the door
(4) You may view this service information W12–140, 1200 New Jersey Avenue SE., latch mechanism.
at the FAA, Transport Airplane Directorate, Washington, DC. Flammable fluid entry and accumulation
1601 Lind Avenue SW., Renton, WA. For For service information identified in in the aft equipment bay, in excessive
information on the availability of this this final rule, contact Bombardier, Inc., quantities, could exceed safe levels
material at the FAA, call 425–227–1221. 400 Côte-Vertu Road West, Dorval, maintained by the drainage and ventilation
jstallworth on DSK7TPTVN1PROD with RULES
(5) You may view this service information Québec H4S 1Y9, Canada; telephone system.
that is incorporated by reference at the Bombardier Inc. has issued several Service
National Archives and Records
514–855–5000; fax 514–855–7401; email
Bulletins (SB) to modify the Aft Equipment
Administration (NARA). For information on thd.crj@aero.bombardier.com; Internet Bay by installing a cover to the door latch
the availability of this material at NARA, call http://www.bombardier.com. You may mechanism in order to reduce the risk of fuel
202–741–6030, or go to: http:// view this referenced service information entry into it. This [Canadian] AD mandates
www.archives.gov/federal-register/cfr/ibr- at the FAA, Transport Airplane the incorporation of the applicable
locations.html. Directorate, 1601 Lind Avenue SW., Bombardier Inc. SBs to rectify this problem.
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Document Created: 2018-02-02 12:33:27
Document Modified: 2018-02-02 12:33:27
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective February 25, 2016. | |
| 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 | 81 FR 3301 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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