Airworthiness Directives; Airbus Airplanes, 68050-68052 [2012-27055]

Download as PDF 68050 Federal Register / Vol. 77, No. 221 / Thursday, November 15, 2012 / Rules and Regulations Although the Agencies generally expect to consult closely on scenario development, they may have different views of risks that should be reflected in the stress test scenarios used by covered institutions for the annual stress test. The OCC may distribute scenarios to covered institutions that differ in certain respects from those distributed by the FDIC and the Board if necessary to better reflect specific OCC concerns. The OCC expects such situations to be extremely rare, however, and anticipates making every effort to avoid differences in the scenarios required by each agency. The OCC anticipates that the stress test scenarios will be revised annually as appropriate to ensure that each scenario remains relevant under prevailing economic and industry conditions. These yearly revisions will enable the scenarios to capture evolving risks and vulnerabilities. The need to ensure that scenarios do not become outdated because of economic and financial developments makes a lengthy process of review and comment concerning scenarios prior to distribution each year impractical. However, the process of consultation with the Board and the FDIC, as well as the ongoing interaction of OCC staff with public and private sector experts to obtain views on salient risks and to obtain suggestions for the behavior of key economic variables, should ensure that the stress conditions reflected in the scenarios are well suited to their purpose. The scenario development process culminates with the distribution of the scenarios to all covered institutions no later than November 15 of each year. The scenario descriptions provided to covered institutions will include values for economic and financial variables depicting the paths those variables follow under the scenarios. The OCC believes that distribution of the scenarios by November 15 aligns with similar processes at the FDIC and the Board. Dated: November 6, 2012. Thomas J. Curry, Comptroller of the Currency. [FR Doc. 2012–27660 Filed 11–14–12; 8:45 am] BILLING CODE 4810–33–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0488; Directorate Identifier 2011–NM–106–AD; Amendment 39–17244; AD 2012–22–08] RIN 2120–AA64 wreier-aviles on DSK5TPTVN1PROD with Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4–600 and A300 SUMMARY: VerDate Mar<15>2010 13:24 Nov 14, 2012 Jkt 229001 B4–600R, Model A300, and Model A310 series airplanes. This AD was prompted by reports of fatigue cracking in the crossbeams at the junction of the actuator beam of the lower deck cargo door. This AD requires repetitive inspections of the crossbeams of certain fuselage frames, and repair if necessary. We are issuing this AD to detect and correct cracking of the crossbeams at the junction of the actuator beam of the lower deck cargo door, which could result in failure to withstand ultimate load conditions, and consequent reduced structural integrity of the airplane. This AD is effective December 20, 2012. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of December 20, 2012. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: DATES: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM published in the Federal Register on May 22, 2012 (77 FR 30228). That NPRM proposed to correct an unsafe condition for the specified products. The Mandatory Continuing Airworthiness Information (MCAI) states: Some operators have reported cracked crossbeams at the junction with the lower deck cargo door actuator beam. The investigation results indicate that these cracks initiated in the fastener hole, propagated in a vertical direction and were due to fatigue. This condition, if not corrected, could lead, in case of cracks propagation in a crossbeam (upper and lower web), to the floor grid being unable to withstand ultimate load condition. For the reasons described above, this [European Aviation Safety Agency (EASA)] AD requires repetitive [high frequency eddy current] inspections [for cracks] of certain crossbeams including those previously repaired by the Structure Repair Manual (SRM) or Repair Approval Sheet (RAS). PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 The required actions include repairing any cracking. As an option, modifying the crossbeams terminates the repetitive inspections. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal (77 FR 30228, May 22, 2012) and the FAA’s response to each comment. Request To Clarify That Freighter Airplanes Are Not Affected UPS stated that the NPRM (77 FR 30228, May 22, 2012) does not apply to its Model A300 F4–622R airplanes. We infer that the commenter is asking for clarification that its airplanes are not affected by the proposed requirements. Freighter airplanes identified as freighters on the initial certificate of airworthiness are excluded from the applicability in this AD. The loads distribution via the main deck cargo loading system onto the floor grid is different from passenger airplanes. In addition, the European Aviation Safety Agency (EASA), which is the aviation authority for the Member States of the European Community, has granted an alternative method of compliance (AMOC) for Airbus airplanes converted from passenger to freighter configuration by EASA supplemental type certificate (STC). We have changed the applicability in paragraph (c) of this AD to exclude airplanes converted by the equivalent FAA STCs ST01431NY, ST00177LA–D, and ST00100NY. Request To Extend Repetitive Inspection Interval/Eliminate Compliance Time for Corrective Action FedEx asked that the repetitive inspection interval specified in paragraph (g) of the NPRM (77 FR 30228, May 22, 2012), be extended from 600 flight cycles to within 1,500 flight cycles or 24 months after the effective date of the AD, whichever occurs first. FedEx stated that the current repetitive inspection interval is ten times more frequent than the 6,000-flight-cycle interval in the existing airworthiness limitations items and maintenance review board requirements. FedEx added that these maintenance program items have been performed regularly at FedEx and have yielded few findings. FedEx noted that this extension will coincide with its regular maintenance check schedule. FedEx also stated that paragraph (g)(2) of the NPRM (77 FR 30228, May 22, 2012) specifies that, if a prior repair has E:\FR\FM\15NOR1.SGM 15NOR1 Federal Register / Vol. 77, No. 221 / Thursday, November 15, 2012 / Rules and Regulations been done on the crossbeam, the corrective action requires accomplishing a repair within 600 flight cycles after the effective date of the AD. This places an additional burden on operators by mandating replacement of the crossbeam. We disagree with the requests to extend the compliance time for the repetitive inspections and to eliminate the compliance time for the corrective action. Based on the data provided by Airbus, we determined that repetitive intervals of 600 flight hours and doing the repair before the accumulation of 10,000 total flight cycles since first flight of the airplane, or within 600 flight cycles after the effective date of this AD, whichever occurs later, is appropriate to address the identified unsafe condition. In developing an appropriate compliance time for these actions, we considered the urgency associated with the subject unsafe condition, the manufacturer’s recommendations, and the practical aspect of accomplishing the required actions within a period of time that corresponds to the normal scheduled maintenance for most affected operators. In addition, our compliance time corresponds with the compliance time of the parallel AD issued by EASA. Under the provisions of paragraph (j)(1) of this AD, we will consider requests for approval of an extension of the compliance time if sufficient data are submitted to substantiate that the new compliance time would provide an acceptable level of safety. We have not changed the AD in this regard. Product Identification Correction We have changed the product identification in this AD to specify ‘‘Airbus.’’ We inadvertently listed ‘‘The Boeing Company’’ in the product identification section of the NPRM (77 FR 30228, May 22, 2012). wreier-aviles on DSK5TPTVN1PROD with Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We also determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. Costs of Compliance Based on the service information, we estimate that this AD affects about 152 products of U.S. registry. We also estimate that it will take about 1 workhour per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. VerDate Mar<15>2010 13:24 Nov 14, 2012 Jkt 229001 Based on these figures, we estimate the cost of the AD on U.S. operators to be $12,920, or $85 per product. We have received no definitive data that would enable us to provide cost estimates 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. List of Subjects in 14 CFR Part 39 68051 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2012–22–08 Airbus: Amendment 39–17244; Docket No. FAA–2012–0488; Directorate Identifier 2011–NM–106–AD. (a) Effective Date This AD is effective December 20, 2012. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A300 B2– 1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes; Model A300 B4–601, B4–603, B4–620, and B4–622 airplanes; Model A300 B4–605R and B4–622R airplanes; and Model A310–203, -204, -221, -222, -304, -322, -324, and -325 airplanes; certificated in any category; except those airplanes identified in paragraph (c)(1), (c)(2), (c)(3), and (c)(4) of this AD. (1) Airplanes on which Airbus Service Bulletin A300–53–6166 (Airbus Modification 13434) has been embodied in service (for Model A300 B4–600 and A300 B4–600R series airplanes). (2) Airplanes on which Airbus Service Bulletin A300–53–0389 (Airbus Modification 13434) has been embodied in service (for Model A300 series airplanes). (3) Airplanes on which Airbus Service Bulletin A310–53–2133 (Airbus Modification 13434) has been embodied in service (for Model A310 series airplanes). (4) Airplanes modified by FAA Supplemental Type Certificate (STC) ST01431NY, ST00177LA–D, or ST00100NY, as applicable. (d) Subject Air Transport Association (ATA) of America Code 53: Fuselage. (e) Reason This AD was prompted by reports of fatigue cracking in the crossbeams at the junction of the actuator beam of the lower deck cargo door. We are issuing this AD to detect and correct cracking of the crossbeams at the junction of the actuator beam of the lower deck cargo door, which could result in failure to withstand ultimate load conditions, and consequent reduced structural integrity of the airplane. Adoption of the Amendment (f) Compliance You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: (g) Repetitive High Frequency Eddy Current Inspections (1) For airplanes on which the crossbeams at frames (FR) 22/23 and FR 61/62 have not Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 E:\FR\FM\15NOR1.SGM 15NOR1 68052 Federal Register / Vol. 77, No. 221 / Thursday, November 15, 2012 / Rules and Regulations been repaired as specified in an Airbus structural repair manual or repair approval sheet as of the effective date of this AD: Before the accumulation of 10,000 total flight cycles since first flight of the airplane, or within 600 flight cycles after the effective date of this AD, whichever occurs later, perform a high frequency eddy current (HFEC) inspection for cracking of the crossbeam fuselage frame stations FR 22/23 and FR 61/62, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of this AD. Repeat the inspection thereafter at intervals not to exceed 600 flight cycles until the modification specified in paragraph (i) of this AD has been done. (i) Airbus Mandatory Service Bulletin A300–53–0390, dated January 15, 2010 (for Model A300 series airplanes). (ii) Airbus Mandatory Service Bulletin A310–53–2134, dated January 15, 2010 (for Model A310 series airplanes). (iii) Airbus Mandatory Service Bulletin A300–53–6168, dated January 15, 2010 (for Model A300–600 series airplanes). (2) For airplanes on which the crossbeams at FR 22/23 and FR 61/62 have been repaired as specified in an Airbus structural repair manual or repair approval sheet as of the effective date of this AD: Before the accumulation of 10,000 total flight cycles since first flight of the airplane, or within 600 flight cycles after the effective date of this AD, whichever occurs later, repair in accordance with a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). wreier-aviles on DSK5TPTVN1PROD with (h) Corrective Action If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, repair any crack using a method approved by the Manager, International Branch, ANM–116; or EASA (or its delegated agent). (i) Optional Terminating Action Modifying the crossbeam fuselage frame stations FR 22/23 and FR 61/62, including doing rotating probe inspections for cracks of fastener holes, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (i)(1), (i)(2), or (i)(3) of this AD, and repairing any crack using a method approved by the Manager, International Branch, ANM–116; or EASA (or its delegated agent); terminates the repetitive inspections required by paragraph (g)(1) of this AD. (1) Airbus Service Bulletin A300–53–0389, Revision 02, dated April 27, 2011 (for Model A300 series airplanes). (2) Airbus Service Bulletin A310–53–2133, Revision 02, dated April 27, 2011 (for Model A310 series airplanes). (3) Airbus Service Bulletin A300–53–6166, Revision 01, dated May 21, 2010 (for Model A300–600 series airplanes). (j) Other FAA AD Provisions The following provisions also apply to this AD: VerDate Mar<15>2010 13:24 Nov 14, 2012 Jkt 229001 (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, Washington 98057– 3356; telephone (425) 227–2125; fax (425) 227–1149. Information may be emailed to: 9ANM-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) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (k) Related Information Refer to EASA Airworthiness Directive 2011–0086, dated May 12, 2011; and the service information identified in paragraphs (k)(1), (k)(2), (k)(3), (k)(4), (k)(5), and (k)(6) of this AD, for related information. (1) Airbus Mandatory Service Bulletin A300–53–0390, dated January 15, 2010. (2) Airbus Mandatory Service Bulletin A300–53–6168, dated January 15, 2010. (3) Airbus Mandatory Service Bulletin A310–53–2134, dated January 15, 2010. (4) Airbus Service Bulletin A300–53–0389, Revision 02, dated April 27, 2011. (5) Airbus Service Bulletin A300–53–6166, Revision 01, dated May 21, 2010. (6) Airbus Service Bulletin A310–53–2133, Revision 02, dated April 27, 2011. (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 the AD specifies otherwise. (i) Airbus Mandatory Service Bulletin A300–53–0390, dated January 15, 2010. (ii) Airbus Mandatory Service Bulletin A300–53–6168, dated January 15, 2010. (iii) Airbus Mandatory Service Bulletin A310–53–2134, dated January 15, 2010. (iv) Airbus Service Bulletin A300–53– 0389, Revision 02, dated April 27, 2011. (v) Airbus Service Bulletin A300–53–6166, Revision 01, dated May 21, 2010. (vi) Airbus Service Bulletin A310–53– 2133, Revision 02, dated April 27, 2011. (3) For service information identified in this AD, contact Airbus SAS—EAW PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 (Airworthiness Office), 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.airwortheas@airbus.com; Internet http:// www.airbus.com. (4) You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. 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 October 24, 2012. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–27055 Filed 11–14–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0643; Directorate Identifier 2011–NM–190–AD; Amendment 39–17241; AD 2012–22–05] RIN 2120–AA64 Airworthiness Directives; Fokker Services B.V. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding an existing airworthiness directive (AD) for certain Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. That AD currently requires performing a detailed visual inspection for cracks of the pistons on the main landing gear (MLG), and replacing the affected pistons if necessary. This new AD also requires modifying the MLG by installing a piston containing a certain part number, and revising the airplane maintenance program. This AD was prompted by a new modification developed to safeguard the integrity of the MLG assembly and improve surface protection of the affected area of the MLG piston. We are issuing this AD to prevent MLG failure, possibly resulting in loss of control of the airplane during the landing roll-out. DATES: This AD becomes effective December 20, 2012. SUMMARY: E:\FR\FM\15NOR1.SGM 15NOR1

Agencies

[Federal Register Volume 77, Number 221 (Thursday, November 15, 2012)]
[Rules and Regulations]
[Pages 68050-68052]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-27055]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0488; Directorate Identifier 2011-NM-106-AD; 
Amendment 39-17244; AD 2012-22-08]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A300 B4-600 and A300 B4-600R, Model A300, and Model A310 
series airplanes. This AD was prompted by reports of fatigue cracking 
in the crossbeams at the junction of the actuator beam of the lower 
deck cargo door. This AD requires repetitive inspections of the 
crossbeams of certain fuselage frames, and repair if necessary. We are 
issuing this AD to detect and correct cracking of the crossbeams at the 
junction of the actuator beam of the lower deck cargo door, which could 
result in failure to withstand ultimate load conditions, and consequent 
reduced structural integrity of the airplane.

DATES: This AD is effective December 20, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of December 20, 
2012.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 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 to include an AD that would apply to the specified products. 
That NPRM published in the Federal Register on May 22, 2012 (77 FR 
30228). That NPRM proposed to correct an unsafe condition for the 
specified products. The Mandatory Continuing Airworthiness Information 
(MCAI) states:

    Some operators have reported cracked crossbeams at the junction 
with the lower deck cargo door actuator beam. The investigation 
results indicate that these cracks initiated in the fastener hole, 
propagated in a vertical direction and were due to fatigue.
    This condition, if not corrected, could lead, in case of cracks 
propagation in a crossbeam (upper and lower web), to the floor grid 
being unable to withstand ultimate load condition.
For the reasons described above, this [European Aviation Safety 
Agency (EASA)] AD requires repetitive [high frequency eddy current] 
inspections [for cracks] of certain crossbeams including those 
previously repaired by the Structure Repair Manual (SRM) or Repair 
Approval Sheet (RAS).

The required actions include repairing any cracking. As an option, 
modifying the crossbeams terminates the repetitive inspections. You may 
obtain further information by examining the MCAI in the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(77 FR 30228, May 22, 2012) and the FAA's response to each comment.

Request To Clarify That Freighter Airplanes Are Not Affected

    UPS stated that the NPRM (77 FR 30228, May 22, 2012) does not apply 
to its Model A300 F4-622R airplanes.
    We infer that the commenter is asking for clarification that its 
airplanes are not affected by the proposed requirements. Freighter 
airplanes identified as freighters on the initial certificate of 
airworthiness are excluded from the applicability in this AD. The loads 
distribution via the main deck cargo loading system onto the floor grid 
is different from passenger airplanes. In addition, the European 
Aviation Safety Agency (EASA), which is the aviation authority for the 
Member States of the European Community, has granted an alternative 
method of compliance (AMOC) for Airbus airplanes converted from 
passenger to freighter configuration by EASA supplemental type 
certificate (STC). We have changed the applicability in paragraph (c) 
of this AD to exclude airplanes converted by the equivalent FAA STCs 
ST01431NY, ST00177LA-D, and ST00100NY.

Request To Extend Repetitive Inspection Interval/Eliminate Compliance 
Time for Corrective Action

    FedEx asked that the repetitive inspection interval specified in 
paragraph (g) of the NPRM (77 FR 30228, May 22, 2012), be extended from 
600 flight cycles to within 1,500 flight cycles or 24 months after the 
effective date of the AD, whichever occurs first. FedEx stated that the 
current repetitive inspection interval is ten times more frequent than 
the 6,000-flight-cycle interval in the existing airworthiness 
limitations items and maintenance review board requirements. FedEx 
added that these maintenance program items have been performed 
regularly at FedEx and have yielded few findings. FedEx noted that this 
extension will coincide with its regular maintenance check schedule.
    FedEx also stated that paragraph (g)(2) of the NPRM (77 FR 30228, 
May 22, 2012) specifies that, if a prior repair has

[[Page 68051]]

been done on the crossbeam, the corrective action requires 
accomplishing a repair within 600 flight cycles after the effective 
date of the AD. This places an additional burden on operators by 
mandating replacement of the crossbeam.
    We disagree with the requests to extend the compliance time for the 
repetitive inspections and to eliminate the compliance time for the 
corrective action. Based on the data provided by Airbus, we determined 
that repetitive intervals of 600 flight hours and doing the repair 
before the accumulation of 10,000 total flight cycles since first 
flight of the airplane, or within 600 flight cycles after the effective 
date of this AD, whichever occurs later, is appropriate to address the 
identified unsafe condition. In developing an appropriate compliance 
time for these actions, we considered the urgency associated with the 
subject unsafe condition, the manufacturer's recommendations, and the 
practical aspect of accomplishing the required actions within a period 
of time that corresponds to the normal scheduled maintenance for most 
affected operators. In addition, our compliance time corresponds with 
the compliance time of the parallel AD issued by EASA. Under the 
provisions of paragraph (j)(1) of this AD, we will consider requests 
for approval of an extension of the compliance time if sufficient data 
are submitted to substantiate that the new compliance time would 
provide an acceptable level of safety. We have not changed the AD in 
this regard.

Product Identification Correction

    We have changed the product identification in this AD to specify 
``Airbus.'' We inadvertently listed ``The Boeing Company'' in the 
product identification section of the NPRM (77 FR 30228, May 22, 2012).

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously. We also determined that 
these changes will not increase the economic burden on any operator or 
increase the scope of the AD.

Costs of Compliance

    Based on the service information, we estimate that this AD affects 
about 152 products of U.S. registry. We also estimate that it will take 
about 1 work-hour per product to comply with the basic requirements of 
this AD. The average labor rate is $85 per work-hour. Based on these 
figures, we estimate the cost of the AD on U.S. operators to be 
$12,920, or $85 per product.
    We have received no definitive data that would enable us to provide 
cost estimates 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.

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):

2012-22-08 Airbus: Amendment 39-17244; Docket No. FAA-2012-0488; 
Directorate Identifier 2011-NM-106-AD.

(a) Effective Date

    This AD is effective December 20, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-
203, B4-2C, B4-103, and B4-203 airplanes; Model A300 B4-601, B4-603, 
B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R 
airplanes; and Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes; certificated in any category; except those 
airplanes identified in paragraph (c)(1), (c)(2), (c)(3), and (c)(4) 
of this AD.
    (1) Airplanes on which Airbus Service Bulletin A300-53-6166 
(Airbus Modification 13434) has been embodied in service (for Model 
A300 B4-600 and A300 B4-600R series airplanes).
    (2) Airplanes on which Airbus Service Bulletin A300-53-0389 
(Airbus Modification 13434) has been embodied in service (for Model 
A300 series airplanes).
    (3) Airplanes on which Airbus Service Bulletin A310-53-2133 
(Airbus Modification 13434) has been embodied in service (for Model 
A310 series airplanes).
    (4) Airplanes modified by FAA Supplemental Type Certificate 
(STC) ST01431NY, ST00177LA-D, or ST00100NY, as applicable.

(d) Subject

    Air Transport Association (ATA) of America Code 53: Fuselage.

(e) Reason

    This AD was prompted by reports of fatigue cracking in the 
crossbeams at the junction of the actuator beam of the lower deck 
cargo door. We are issuing this AD to detect and correct cracking of 
the crossbeams at the junction of the actuator beam of the lower 
deck cargo door, which could result in failure to withstand ultimate 
load conditions, and consequent reduced structural integrity of the 
airplane.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Repetitive High Frequency Eddy Current Inspections

    (1) For airplanes on which the crossbeams at frames (FR) 22/23 
and FR 61/62 have not

[[Page 68052]]

been repaired as specified in an Airbus structural repair manual or 
repair approval sheet as of the effective date of this AD: Before 
the accumulation of 10,000 total flight cycles since first flight of 
the airplane, or within 600 flight cycles after the effective date 
of this AD, whichever occurs later, perform a high frequency eddy 
current (HFEC) inspection for cracking of the crossbeam fuselage 
frame stations FR 22/23 and FR 61/62, in accordance with the 
Accomplishment Instructions of the applicable service bulletin 
identified in paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of 
this AD. Repeat the inspection thereafter at intervals not to exceed 
600 flight cycles until the modification specified in paragraph (i) 
of this AD has been done.
    (i) Airbus Mandatory Service Bulletin A300-53-0390, dated 
January 15, 2010 (for Model A300 series airplanes).
    (ii) Airbus Mandatory Service Bulletin A310-53-2134, dated 
January 15, 2010 (for Model A310 series airplanes).
    (iii) Airbus Mandatory Service Bulletin A300-53-6168, dated 
January 15, 2010 (for Model A300-600 series airplanes).
    (2) For airplanes on which the crossbeams at FR 22/23 and FR 61/
62 have been repaired as specified in an Airbus structural repair 
manual or repair approval sheet as of the effective date of this AD: 
Before the accumulation of 10,000 total flight cycles since first 
flight of the airplane, or within 600 flight cycles after the 
effective date of this AD, whichever occurs later, repair in 
accordance with a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA) (or its delegated agent).

(h) Corrective Action

    If any crack is found during any inspection required by 
paragraph (g) of this AD: Before further flight, repair any crack 
using a method approved by the Manager, International Branch, ANM-
116; or EASA (or its delegated agent).

(i) Optional Terminating Action

    Modifying the crossbeam fuselage frame stations FR 22/23 and FR 
61/62, including doing rotating probe inspections for cracks of 
fastener holes, in accordance with the Accomplishment Instructions 
of the applicable service bulletin identified in paragraph (i)(1), 
(i)(2), or (i)(3) of this AD, and repairing any crack using a method 
approved by the Manager, International Branch, ANM-116; or EASA (or 
its delegated agent); terminates the repetitive inspections required 
by paragraph (g)(1) of this AD.
    (1) Airbus Service Bulletin A300-53-0389, Revision 02, dated 
April 27, 2011 (for Model A300 series airplanes).
    (2) Airbus Service Bulletin A310-53-2133, Revision 02, dated 
April 27, 2011 (for Model A310 series airplanes).
    (3) Airbus Service Bulletin A300-53-6166, Revision 01, dated May 
21, 2010 (for Model A300-600 series airplanes).

(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, Washington 
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) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

(k) Related Information

    Refer to EASA Airworthiness Directive 2011-0086, dated May 12, 
2011; and the service information identified in paragraphs (k)(1), 
(k)(2), (k)(3), (k)(4), (k)(5), and (k)(6) of this AD, for related 
information.
    (1) Airbus Mandatory Service Bulletin A300-53-0390, dated 
January 15, 2010.
    (2) Airbus Mandatory Service Bulletin A300-53-6168, dated 
January 15, 2010.
    (3) Airbus Mandatory Service Bulletin A310-53-2134, dated 
January 15, 2010.
    (4) Airbus Service Bulletin A300-53-0389, Revision 02, dated 
April 27, 2011.
    (5) Airbus Service Bulletin A300-53-6166, Revision 01, dated May 
21, 2010.
    (6) Airbus Service Bulletin A310-53-2133, Revision 02, dated 
April 27, 2011.

(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 the AD specifies otherwise.
    (i) Airbus Mandatory Service Bulletin A300-53-0390, dated 
January 15, 2010.
    (ii) Airbus Mandatory Service Bulletin A300-53-6168, dated 
January 15, 2010.
    (iii) Airbus Mandatory Service Bulletin A310-53-2134, dated 
January 15, 2010.
    (iv) Airbus Service Bulletin A300-53-0389, Revision 02, dated 
April 27, 2011.
    (v) Airbus Service Bulletin A300-53-6166, Revision 01, dated May 
21, 2010.
    (vi) Airbus Service Bulletin A310-53-2133, Revision 02, dated 
April 27, 2011.
    (3) For service information identified in this AD, contact 
Airbus SAS--EAW (Airworthiness Office), 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 review copies of the referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, Washington. 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 October 24, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-27055 Filed 11-14-12; 8:45 am]
BILLING CODE 4910-13-P