Airworthiness Directives; Airbus Airplanes, 52174-52177 [2014-20259]

Download as PDF 52174 Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Rules and Regulations General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): wreier-aviles on DSK5TPTVN1PROD with RULES ■ 2014–17–08 Pratt & Whitney Canada Corp.: Amendment 39–17961; Docket No. FAA–2013–0766; Directorate Identifier 2013–NE–26–AD. (a) Effective Date This AD becomes effective October 8, 2014. Jkt 232001 This AD applies to all Pratt & Whitney Canada Corp. (P&WC) PT6A–114 and PT6A– 114A turboprop engines. (d) Unsafe Condition This AD was prompted by several incidents of compressor turbine (CT) blade failure, causing power loss, and engine failure. We are issuing this AD to prevent failure of CT blades, which could lead to damage to the engine and damage to the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) For engines that have CT blades installed other than P&WC single crystal CT blades, part numbers (P/Ns) 3072791–01 or 3072791–02, perform the following actions: (i) Within 150 operating hours after the effective date of this AD, perform a borescope inspection (BSI) of CT blades for engines with 500 or more hours time-since-new that have not been previously inspected or timesince-last-inspection (TSLI). (ii) Thereafter, repeat the inspection in paragraph (e)(1)(i) of this AD within 500 flight hours TSLI. (iii) During the next hot section inspection (HSI) after the effective date of this AD, and each HSI thereafter, replace the complete set of CT blades with any of the following: (A) New CT blades; (B) CT blades that have passed a two-blade metallurgical examination in accordance with paragraph 3.B., Accomplishment Instructions, of P&WC Service Bulletin (SB) No. PT6A–72–1669, Revision 9, dated June 28, 2013; or (C) P&WC single crystal CT blades, P/Ns 3072791–01 or 3072791–02. (2) Reserved. (i) Related Information (1) For more information about this AD, contact Robert Morlath, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7154; fax: 781–238–7199; email: robert.c.morlath@faa.gov. (2) Refer to Transport Canada Civil Aviation AD CF–2013–21R1, dated November 13, 2013, for more information. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2013-0766-0008. (j) 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) Pratt & Whitney Canada Service Bulletin No. PT6A–72–1669, Revision 9, dated June 28, 2013. (ii) Reserved. (3) For P&WC service information identified in this AD, contact Pratt & Whitney Canada Corp., 1000 Marie-Victorin, Longueuil, Quebec, Canada, J4G 1A1; phone: 800–268–8000; fax: 450–647–2888; Internet: www.pwc.ca. (4) You may view this service information at FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. (5) You may view this service information 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/ibrlocations.html. Issued in Burlington, Massachusetts, on August18, 2014. Richard P. Warren, Acting Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2014–20453 Filed 9–2–14; 8:45 am] BILLING CODE 4910–13–P (g) Credit for Previous Action ■ 14:42 Sep 02, 2014 (c) Applicability Within 36 months after the effective date of this AD, replace the complete set of CT blades with P&WC single crystal CT blades, P/Ns 3072791–01 or 3072791–02. PART 39—AIRWORTHINESS DIRECTIVES VerDate Mar<15>2010 None. (f) Mandatory Terminating Action Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: § 39.13 (b) Affected ADs If you performed a metallurgical examination of single crystal CT blades before the effective date of this AD in accordance with P&WC SB No. PT6A–72– 1669, Revision 8, dated January 17, 2013, or earlier versions, all of which are not incorporated by reference, you have met the initial inspection requirements of paragraph (e)(1)(i) of this AD. However, you must still comply with the repetitive BSI requirement of paragraph (e)(1)(ii) of this AD. (h) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs to this AD. Use the procedures found in 14 CFR 39.19 to make your request. PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0137; Directorate Identifier 2013–NM–135–AD; Amendment 39–17960; AD 2014–17–07] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). AGENCY: E:\FR\FM\03SER1.SGM 03SER1 Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Rules and Regulations ACTION: Final rule. We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; Model A300 B4–600, B4–600R, and F4– 600R series airplanes; Model A300 C4– 605R Variant F airplanes (collectively called Model A300–600 series airplanes); and Model A310 series airplanes. This AD was prompted by reports of rupture of the uplock springs of the nose landing gear (NLG) and main landing gear (MLG) doors and legs. This AD requires repetitive inspections of the uplock springs of the NLG and MLG doors and legs for broken and damaged springs, and corrective actions if necessary. We are issuing this AD to detect and correct improper free fall extension of the MLG or NLG, which could lead to possible loss of control of the airplane on the ground, and consequent damage to the airplane and injury to occupants. DATES: This AD becomes effective October 8, 2014. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 8, 2014. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0137; 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 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. 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: wreier-aviles on DSK5TPTVN1PROD with RULES SUMMARY: apply to all Airbus Model A300 series airplanes; Model A300 B4–600, B4– 600R, and F4–600R series airplanes; Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes); and Model A310 series airplanes. The NPRM published in the Federal Register on March 7, 2014 (79 FR 13003). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2013–0150, dated July 16, 2013 (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; Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes); and Model A310 series airplanes. The MCAI states: Some cases of Nose Landing Gear (NLG) and Main Landing Gear (MLG) Door and Leg Uplock spring ruptures on A300, A310 or A300–600 aeroplanes have been reported in service. Springs within the uplock are used to either lock the gear or the door in the up position, or to participate in emergency mechanical unlocking. The springs are positioned in pairs, and in case of rupture of one spring the other one remains to fulfill the function, whereas the rupture of both springs will disable the locking function or the emergency unlocking function. This condition, if not detected and corrected, could prevent proper free fall extension of the MLG or NLG, possibly leading to loss of control of the aeroplane on the ground, consequently resulting in damage to the aeroplane and injury to occupants. For the reason described above, this [EASA] AD requires [repetitive] detailed visual inspection[s] of the NLG and MLG Door and Leg Uplock springs [for broken and damaged springs] and, depending of findings, their replacement. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2014-01370002. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (79 FR 13003, March 7, 2014) or on the determination of the cost to the public. Discussion ‘‘Contacting the Manufacturer’’ Paragraph in This AD We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would Since late 2006, we have included a standard paragraph titled ‘‘Airworthy Product’’ in all MCAI ADs in which the VerDate Mar<15>2010 14:42 Sep 02, 2014 Jkt 232001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 52175 FAA develops an AD based on a foreign authority’s AD. We have become aware that some operators have misunderstood or misinterpreted the Airworthy Product paragraph to allow the owner/operator to use messages provided by the manufacturer as approval of deviations during the accomplishment of an ADmandated action. The Airworthy Product paragraph does not approve messages or other information provided by the manufacturer for deviations to the requirements of the AD-mandated actions. The Airworthy Product paragraph only addresses the requirement to contact the manufacturer for corrective actions for the identified unsafe condition and does not cover deviations from other AD requirements. However, deviations to AD-required actions are addressed in 14 CFR 39.17, and anyone may request the approval for an alternative method of compliance to the AD-required actions using the procedures found in 14 CFR 39.19. To address this misunderstanding and misinterpretation of the Airworthy Product paragraph, we have changed the paragraph and retitled it ‘‘Contacting the Manufacturer.’’ This paragraph now clarifies that for any requirement in this AD to obtain corrective actions from a manufacturer, the actions must be accomplished using a method approved by the FAA, the European Aviation Safety Agency (EASA), or Airbus’s EASA Design Organization Approval (DOA). The Contacting the Manufacturer paragraph also clarifies that, if approved by the DOA, the approval must include the DOA-authorized signature. The DOA signature indicates that the data and information contained in the document are EASA-approved, which is also FAAapproved. Messages and other information provided by the manufacturer that do not contain the DOA-authorized signature approval are not EASA-approved, unless EASA directly approves the manufacturer’s message or other information. This clarification does not remove flexibility previously afforded by the Airworthy Product paragraph. Consistent with long-standing FAA policy, such flexibility was never intended for required actions. This is also consistent with the recommendation of the Airworthiness Directive Implementation Aviation Rulemaking Committee to increase flexibility in complying with ADs by identifying those actions in manufacturers’ service instructions that are ‘‘Required for Compliance’’ with ADs. We continue to work with manufacturers to implement this E:\FR\FM\03SER1.SGM 03SER1 52176 Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Rules and Regulations recommendation. But once we determine that an action is required, any deviation from the requirement must be approved as an alternative method of compliance. We also have decided not to include a generic reference to either the ‘‘delegated agent’’ or ‘‘design approval holder (DAH) with State of Design Authority design organization approval,’’ but instead we have provided the specific delegation approval granted by the State of Design Authority for the DAH throughout this AD. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (79 FR 13003, March 7, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 13003, March 7, 2014). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Costs of Compliance We estimate that this AD affects 156 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Repetitive inspections ... 1 work-hour × $85 per hour = $85 per inspection. $0 $85 per inspection ....... $13,260 per inspection. In addition, we estimate that any necessary replacement would take about 9 work-hours for a cost of $765 per product. The cost of parts is minimal. We have no way of determining the number of aircraft that might need this action. 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. wreier-aviles on DSK5TPTVN1PROD with RULES Regulatory Findings 14:42 Sep 02, 2014 Jkt 232001 You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0137; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The 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. Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2014–17–07 Airbus: Amendment 39–17960. Docket No. FAA–2014–0137; Directorate Identifier 2013–NM–135–AD. (a) Effective Date This AD becomes effective October 8, 2014. (b) Affected ADs None. Examining the AD Docket Adoption of the Amendment We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: VerDate Mar<15>2010 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. (c) Applicability This AD applies to the Airbus airplanes specified in paragraphs (c)(1), (c)(2), (c)(3), (c)(4), (c)(5), and (c)(6) of this AD; certificated in any category; all serial numbers. (1) Model A300 B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes. (2) Model A300 B4–601, B4–603, B4–620, and B4–622 airplanes. (3) Model A300 B4–605R and B4–622R airplanes. (4) Model A300 F4–605R and F4–622R airplanes. (5) Model A300 C4–605R Variant F airplanes. (6) Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes. (d) Subject Air Transport Association (ATA) of America Code 32, Landing Gear. (e) Reason This AD was prompted by reports of rupture of the uplock springs of the nose landing gear (NLG) and main landing gear (MLG) doors and legs. We are issuing this AD to detect and correct improper free fall extension of the MLG or NLG, which could lead to possible loss of control of the airplane on the ground, and consequent damage to the airplane and injury to occupants. E:\FR\FM\03SER1.SGM 03SER1 Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Rules and Regulations (f) Compliance Comply with this AD within the compliance times specified, unless already done. wreier-aviles on DSK5TPTVN1PROD with RULES (g) Repetitive Inspections Within 18 months after the effective date of this AD: Perform a detailed inspection of the uplock springs of the MLG and NLG legs and doors for broken and damaged springs, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. Repeat the inspection thereafter at intervals not to exceed 18 months. (1) Airbus Service Bulletin A300–32–0465, Revision 01, dated April 25, 2013 (for Model A300 series airplanes). (2) Airbus Service Bulletin A300–32–6111, Revision 01, dated April 25, 2013 (for Model A300–600 series airplanes). (3) Airbus Service Bulletin A310–32–2147, Revision 01, dated April 25, 2013 (for Model A310 series airplanes). (h) Corrective Actions The corrective actions required by paragraphs (h)(1), (h)(2), and (h)(3) of this AD do not constitute terminating actions for the repetitive inspections required by paragraph (g) of this AD. (1) If, during any inspection required by paragraph (g) of this AD, one spring on the MLG or NLG door uplock is found broken or damaged, within 2 months after the inspection, replace the affected MLG or NLG door uplock, as applicable, with a serviceable part, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. (2) If, during any inspection required by paragraph (g) of this AD, one spring on the MLG or NLG leg uplock is found broken or damaged, repeat the inspection required by paragraph (g) of this AD thereafter at intervals not to exceed 50 flight cycles. Replacement of any affected leg uplock, as required by paragraph (h)(2)(i) or (h)(2)(ii) of this AD, as applicable, constitutes terminating action for the repetitive inspections required by paragraph (h)(2) of this AD. (i) If, during any inspection required by paragraph (h)(2) of this AD, the second free fall spring on the MLG or NLG leg uplock is found broken or damaged, before further flight, replace the affected MLG or NLG leg uplock, as applicable, with a serviceable part, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. (ii) Within 1,000 flight cycles after doing the inspection required by paragraph (g) of this AD during which the spring has been found broken, replace the affected MLG or NLG leg uplock, as applicable, with a serviceable part, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. (3) If, during any inspection required by paragraph (g) of this AD, two free fall springs on the same MLG or NLG leg uplock are VerDate Mar<15>2010 14:42 Sep 02, 2014 Jkt 232001 found broken or damaged, before further flight, replace the affected MLG or NLG leg uplock, as applicable, with a serviceable part, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. (i) Credit for Previous Actions This paragraph provides credit for the applicable actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using the applicable service information identified in paragraph (i)(1), (i)(2), or (i)(3) of this AD. (1) Airbus Service Bulletin A300–32–0465, dated July 20, 2012, which is not incorporated by reference in this AD. (2) Airbus Service Bulletin A300–32–6111, dated July 20, 2012, which is not incorporated by reference in this AD. (3) Airbus Service Bulletin A310–32–2147, dated July 20, 2012, which is not incorporated by reference in this AD. (j) 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-116AMOC-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. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013–0150, dated July 16, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2014-0137-0002. (2) Service information identified in this AD that is not incorporated by reference may be viewed at the addresses specified in paragraphs (l)(3) and (l)(4) of this AD. PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 52177 (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A300–32–0465, Revision 01, dated April 25, 2013. (ii) Airbus Service Bulletin A300–32–6111, Revision 01, dated April 25, 2013. (iii) Airbus Service Bulletin A310–32– 2147, Revision 01, dated April 25, 2013. (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 account.airworth-eas@ airbus.com; 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/ibrlocations.html. Issued in Renton, Washington, on August 15, 2014. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–20259 Filed 9–2–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0617; Directorate Identifier 2014–CE–019–AD; Amendment 39–17962; AD 2014–17–09 RIN 2120–AA64 Airworthiness Directives; Various de Havilland Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for all Harry E. Williams de Havilland Model DH 82A airplanes, all Cliff Robertson de Havilland Model DH 82A airplanes, and all de Havilland Model DH 83 airplanes. This AD requires inspecting the aircraft maintenance records and/or the installed lateral fuselage tie rods and SUMMARY: E:\FR\FM\03SER1.SGM 03SER1

Agencies

[Federal Register Volume 79, Number 170 (Wednesday, September 3, 2014)]
[Rules and Regulations]
[Pages 52174-52177]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-20259]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0137; Directorate Identifier 2013-NM-135-AD; 
Amendment 39-17960; AD 2014-17-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

[[Page 52175]]


ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-
600R series airplanes; Model A300 C4-605R Variant F airplanes 
(collectively called Model A300-600 series airplanes); and Model A310 
series airplanes. This AD was prompted by reports of rupture of the 
uplock springs of the nose landing gear (NLG) and main landing gear 
(MLG) doors and legs. This AD requires repetitive inspections of the 
uplock springs of the NLG and MLG doors and legs for broken and damaged 
springs, and corrective actions if necessary. We are issuing this AD to 
detect and correct improper free fall extension of the MLG or NLG, 
which could lead to possible loss of control of the airplane on the 
ground, and consequent damage to the airplane and injury to occupants.

DATES: This AD becomes effective October 8, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 8, 
2014.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0137; 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 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.

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 A300 
series airplanes; Model A300 B4-600, B4-600R, and F4-600R series 
airplanes; Model A300 C4-605R Variant F airplanes (collectively called 
Model A300-600 series airplanes); and Model A310 series airplanes. The 
NPRM published in the Federal Register on March 7, 2014 (79 FR 13003).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2013-0150, dated July 16, 2013 (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; Model A300 C4-605R Variant F airplanes (collectively called 
Model A300-600 series airplanes); and Model A310 series airplanes. The 
MCAI states:

Some cases of Nose Landing Gear (NLG) and Main Landing Gear (MLG) 
Door and Leg Uplock spring ruptures on A300, A310 or A300-600 
aeroplanes have been reported in service.
    Springs within the uplock are used to either lock the gear or 
the door in the up position, or to participate in emergency 
mechanical unlocking.
    The springs are positioned in pairs, and in case of rupture of 
one spring the other one remains to fulfill the function, whereas 
the rupture of both springs will disable the locking function or the 
emergency unlocking function.
    This condition, if not detected and corrected, could prevent 
proper free fall extension of the MLG or NLG, possibly leading to 
loss of control of the aeroplane on the ground, consequently 
resulting in damage to the aeroplane and injury to occupants.
    For the reason described above, this [EASA] AD requires 
[repetitive] detailed visual inspection[s] of the NLG and MLG Door 
and Leg Uplock springs [for broken and damaged springs] and, 
depending of findings, their replacement.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0137-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (79 FR 13003, March 7, 
2014) or on the determination of the cost to the public.

 ``Contacting the Manufacturer'' Paragraph in This AD

    Since late 2006, we have included a standard paragraph titled 
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD 
based on a foreign authority's AD.
    We have become aware that some operators have misunderstood or 
misinterpreted the Airworthy Product paragraph to allow the owner/
operator to use messages provided by the manufacturer as approval of 
deviations during the accomplishment of an AD-mandated action. The 
Airworthy Product paragraph does not approve messages or other 
information provided by the manufacturer for deviations to the 
requirements of the AD-mandated actions. The Airworthy Product 
paragraph only addresses the requirement to contact the manufacturer 
for corrective actions for the identified unsafe condition and does not 
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request 
the approval for an alternative method of compliance to the AD-required 
actions using the procedures found in 14 CFR 39.19.
    To address this misunderstanding and misinterpretation of the 
Airworthy Product paragraph, we have changed the paragraph and retitled 
it ``Contacting the Manufacturer.'' This paragraph now clarifies that 
for any requirement in this AD to obtain corrective actions from a 
manufacturer, the actions must be accomplished using a method approved 
by the FAA, the European Aviation Safety Agency (EASA), or Airbus's 
EASA Design Organization Approval (DOA).
    The Contacting the Manufacturer paragraph also clarifies that, if 
approved by the DOA, the approval must include the DOA-authorized 
signature. The DOA signature indicates that the data and information 
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer 
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or 
other information.
    This clarification does not remove flexibility previously afforded 
by the Airworthy Product paragraph. Consistent with long-standing FAA 
policy, such flexibility was never intended for required actions. This 
is also consistent with the recommendation of the Airworthiness 
Directive Implementation Aviation Rulemaking Committee to increase 
flexibility in complying with ADs by identifying those actions in 
manufacturers' service instructions that are ``Required for 
Compliance'' with ADs. We continue to work with manufacturers to 
implement this

[[Page 52176]]

recommendation. But once we determine that an action is required, any 
deviation from the requirement must be approved as an alternative 
method of compliance.
    We also have decided not to include a generic reference to either 
the ``delegated agent'' or ``design approval holder (DAH) with State of 
Design Authority design organization approval,'' but instead we have 
provided the specific delegation approval granted by the State of 
Design Authority for the DAH throughout this AD.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD with the changes described 
previously and minor editorial changes. We have determined that these 
minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR 13003, March 7, 2014) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 13003, March 7, 2014).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 156 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                  Cost on U.S.
             Action                     Labor cost           Parts cost     Cost per product       operators
----------------------------------------------------------------------------------------------------------------
Repetitive inspections.........  1 work-hour x $85 per                $0   $85 per inspection  $13,260 per
                                  hour = $85 per                                                inspection.
                                  inspection.
----------------------------------------------------------------------------------------------------------------

    In addition, we estimate that any necessary replacement would take 
about 9 work-hours for a cost of $765 per product. The cost of parts is 
minimal. We have no way of determining the number of aircraft that 
might need this action.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0137; or in person at the 
Docket Management Facility between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The AD docket contains this AD, the 
regulatory evaluation, any comments received, and other information. 
The 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):

2014-17-07 Airbus: Amendment 39-17960. Docket No. FAA-2014-0137; 
Directorate Identifier 2013-NM-135-AD.

(a) Effective Date

    This AD becomes effective October 8, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes specified in paragraphs 
(c)(1), (c)(2), (c)(3), (c)(4), (c)(5), and (c)(6) of this AD; 
certificated in any category; all serial numbers.
    (1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and 
B4-203 airplanes.
    (2) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
    (3) Model A300 B4-605R and B4-622R airplanes.
    (4) Model A300 F4-605R and F4-622R airplanes.
    (5) Model A300 C4-605R Variant F airplanes.
    (6) Model A310-203, -204, -221, -222, -304, -322, -324, and -325 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
Gear.

(e) Reason

    This AD was prompted by reports of rupture of the uplock springs 
of the nose landing gear (NLG) and main landing gear (MLG) doors and 
legs. We are issuing this AD to detect and correct improper free 
fall extension of the MLG or NLG, which could lead to possible loss 
of control of the airplane on the ground, and consequent damage to 
the airplane and injury to occupants.

[[Page 52177]]

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Repetitive Inspections

    Within 18 months after the effective date of this AD: Perform a 
detailed inspection of the uplock springs of the MLG and NLG legs 
and doors for broken and damaged springs, in accordance with the 
Accomplishment Instructions of the applicable service information 
identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. Repeat 
the inspection thereafter at intervals not to exceed 18 months.
    (1) Airbus Service Bulletin A300-32-0465, Revision 01, dated 
April 25, 2013 (for Model A300 series airplanes).
    (2) Airbus Service Bulletin A300-32-6111, Revision 01, dated 
April 25, 2013 (for Model A300-600 series airplanes).
    (3) Airbus Service Bulletin A310-32-2147, Revision 01, dated 
April 25, 2013 (for Model A310 series airplanes).

(h) Corrective Actions

    The corrective actions required by paragraphs (h)(1), (h)(2), 
and (h)(3) of this AD do not constitute terminating actions for the 
repetitive inspections required by paragraph (g) of this AD.
    (1) If, during any inspection required by paragraph (g) of this 
AD, one spring on the MLG or NLG door uplock is found broken or 
damaged, within 2 months after the inspection, replace the affected 
MLG or NLG door uplock, as applicable, with a serviceable part, in 
accordance with the Accomplishment Instructions of the applicable 
service bulletin identified in paragraph (g)(1), (g)(2), or (g)(3) 
of this AD.
    (2) If, during any inspection required by paragraph (g) of this 
AD, one spring on the MLG or NLG leg uplock is found broken or 
damaged, repeat the inspection required by paragraph (g) of this AD 
thereafter at intervals not to exceed 50 flight cycles. Replacement 
of any affected leg uplock, as required by paragraph (h)(2)(i) or 
(h)(2)(ii) of this AD, as applicable, constitutes terminating action 
for the repetitive inspections required by paragraph (h)(2) of this 
AD.
    (i) If, during any inspection required by paragraph (h)(2) of 
this AD, the second free fall spring on the MLG or NLG leg uplock is 
found broken or damaged, before further flight, replace the affected 
MLG or NLG leg uplock, as applicable, with a serviceable part, in 
accordance with the Accomplishment Instructions of the applicable 
service bulletin identified in paragraph (g)(1), (g)(2), or (g)(3) 
of this AD.
    (ii) Within 1,000 flight cycles after doing the inspection 
required by paragraph (g) of this AD during which the spring has 
been found broken, replace the affected MLG or NLG leg uplock, as 
applicable, with a serviceable part, in accordance with the 
Accomplishment Instructions of the applicable service bulletin 
identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD.
    (3) If, during any inspection required by paragraph (g) of this 
AD, two free fall springs on the same MLG or NLG leg uplock are 
found broken or damaged, before further flight, replace the affected 
MLG or NLG leg uplock, as applicable, with a serviceable part, in 
accordance with the Accomplishment Instructions of the applicable 
service bulletin identified in paragraph (g)(1), (g)(2), or (g)(3) 
of this AD.

(i) Credit for Previous Actions

    This paragraph provides credit for the applicable actions 
required by paragraphs (g) and (h) of this AD, if those actions were 
performed before the effective date of this AD using the applicable 
service information identified in paragraph (i)(1), (i)(2), or 
(i)(3) of this AD.
    (1) Airbus Service Bulletin A300-32-0465, dated July 20, 2012, 
which is not incorporated by reference in this AD.
    (2) Airbus Service Bulletin A300-32-6111, dated July 20, 2012, 
which is not incorporated by reference in this AD.
    (3) Airbus Service Bulletin A310-32-2147, dated July 20, 2012, 
which is not incorporated by reference in this AD.

(j) 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.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2013-0150, dated July 16, 2013, 
for related information. This MCAI may be found in the AD docket on 
the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-
2014-0137-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference may be viewed at the addresses specified 
in paragraphs (l)(3) and (l)(4) of this AD.

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A300-32-0465, Revision 01, dated 
April 25, 2013.
    (ii) Airbus Service Bulletin A300-32-6111, Revision 01, dated 
April 25, 2013.
    (iii) Airbus Service Bulletin A310-32-2147, Revision 01, dated 
April 25, 2013.
    (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 account.airworth-eas@airbus.com; 
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 August 15, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-20259 Filed 9-2-14; 8:45 am]
BILLING CODE 4910-13-P