Airworthiness Directives; Airbus Airplanes, 37797-37799 [2012-14730]

Download as PDF Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations Upon display of HYD:BACKUP PUMP HI TEMP (Abnormal procedure 3–250–15), set off the pump and if the backup pump is still rotating (green) in hydraulic synoptic, descend to a safe altitude or below 15,000 ft Caution: These temporary amendments take precedence over the same procedures displayed through the Electronic Check List (ECL) in the aeroplane. Note 1 to paragraph (g) of this AD: When a statement identical to that in paragraph (g) of this AD has been included in the Limitations section and Abnormal Procedures section in the general revisions of the AFM, the general revisions may be inserted into the AFM, and the copy of this AD may be removed. (h) New Requirements of This AD: Test the PDCU and GCU Cards For airplanes identified in Dassault Mandatory Service Bulletin 7X–133, dated December 4, 2009: Within 9 months after the effective date of this AD, perform a test of the PDCU and GCU cards to detect faulty components, in accordance with the Accomplishment Instructions of Dassault Mandatory Service Bulletin 7X–133, dated December 4, 2009. If any faulty components are found, before further flight, replace any affected PDCU or GCU card, in accordance with the Accomplishment Instructions of Dassault Mandatory Service Bulletin 7X–133, dated December 4, 2009. erowe on DSK2VPTVN1PROD with RULES (i) Optional Method of Compliance For airplanes identified in Dassault Mandatory Service Bulletin 7X–133, dated December 4, 2009: Accomplishing the actions specified in paragraph (h) of this AD, within 9 months after the effective date of this AD, in accordance with the service information specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD, is acceptable for compliance with the actions specified in paragraph (h) of this AD. (1) Goodrich Service Bulletin 80232190– 24–01, dated August 13, 2009. (2) Goodrich Service Bulletin 80232191– 24–01, dated August 13, 2009. (3) Goodrich Service Bulletin 80232192– 24–01, dated August 13, 2009. (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, 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: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone (425) 227–1137; 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 VerDate Mar<15>2010 14:43 Jun 22, 2012 Jkt 226001 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 MCAI European Aviation Safety Agency Airworthiness Directive 2010–0073, dated April 15, 2010, and the service bulletins specified in paragraphs (k)(1) through (k)(4) of this AD, for related information. (1) Dassault Mandatory Service Bulletin 7X–133, dated December 4, 2009. (2) Goodrich Service Bulletin 80232190– 24–01, dated August 13, 2009. (3) Goodrich Service Bulletin 80232191– 24–01, dated August 13, 2009. (4) Goodrich Service Bulletin 80232192– 24–01, dated August 13, 2009. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the following service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. (i) Dassault Mandatory Service Bulletin 7X–133, dated December 4, 2009. (3) If you accomplish the optional actions specified by this AD, you must use the following service information to perform those actions, unless the AD specifies otherwise. (i) Goodrich Service Bulletin 80232190– 24–01, dated August 13, 2009. (ii) Goodrich Service Bulletin 80232191– 24–01, dated August 13, 2009. (iii) Goodrich Service Bulletin 80232192– 24–01, dated August 13, 2009. (4) For Dassault service information identified in this AD, contact Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey 07606; telephone 201–440–6700; Internet http://www.dassaultfalcon.com. For Goodrich service information identified in this AD, contact Goodrich Corporation, Power Systems, 1555 Corporate Woods Parkway, Uniontown, Ohio 44685–8799; telephone 330–487–2007; fax 330–487–1902; email twinsburg.techpubs@goodrich.com; Internet http://www.goodrich.com/TechPubs. (5) You may review copies of the 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. (6) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at an NARA facility, call 202–741– PO 00000 Frm 00047 Fmt 4700 Sfmt 4700 37797 6030, or go to http://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on June 11, 2012. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–15066 Filed 6–22–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0152; Directorate Identifier 2011–NM–059–AD; Amendment 39–17092; AD 2012–12–12] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus Model A330–200 series airplanes; Airbus Model A330–200 Freighter series airplanes; Airbus Model A330–300 series airplanes; Airbus Model A340–200 series airplanes; and Airbus Model A340–300 series airplanes. This AD was prompted by reports of sheared fasteners located on the outside skin of the forward cargo door and cracks on the frame fork ends, as well as cracks of the aft cargo door frame 64A. This AD requires performing a detailed inspection of the outer skin rivets at the frame fork ends of the forward and aft cargo door for sheared, loose, and missing rivets; repairing the outer skin rivets, if necessary; and performing repetitive inspections. We are issuing this AD to detect and correct sheared, loose, or missing fasteners on the forward and aft cargo door frame, which could result in the loss of structural integrity of the forward and aft cargo door. DATES: This AD becomes effective July 30, 2012. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of July 30, 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, SUMMARY: E:\FR\FM\25JNR1.SGM 25JNR1 37798 Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 1200 New Jersey Avenue SE., Washington, DC. received no comments on the NPRM (77 FR 10691, February 23, 2012) or on the determination of the cost to the public. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–1138; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: erowe on DSK2VPTVN1PROD with RULES 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 was published in the Federal Register on February 23, 2012 (77 FR 10691). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Two operators have reported cases of some sheared fasteners on the outside skin of the forward cargo door, detected during walk around checks. Further inspections revealed crack findings on the frame (FR) fork ends. In addition, during a scheduled maintenance check, the aft cargo door frame 64A of an aeroplane has been found cracked for a length of more than 3 inches. Outer skin rivets were also found sheared. At time of findings the aeroplane had accumulated 10564 flight cycles (FC), i.e. below the 12000 FC threshold defined in DGAC [Direction ´ ´ Generale de l’Aviation Civile] France AD F– 2001–124(B) and DGAC France AD F–2001– 126(B) [which corresponds with FAA AD 2001–16–01, Amendment 39–12369 (66 FR 40874, August 6, 2001], which require a special detailed inspection of the aft cargo compartment door. In case of cracked or ruptured (forward or aft) cargo door frame, the loads will be transferred to the remaining structural elements. Such second load path is able to sustain the loads for a limited number of flight cycles only. Rupture of two vertical frames could result in the loss of the structural integrity of the forward or aft cargo door. For the above described reasons, this [EASA] AD requires repetitive detailed visual inspections of the aft and forward cargo doors outer skin for sheared, loose or missing rivets at all frame fork ends and the accomplishment of the applicable corrective actions [repair if necessary]. This [EASA] AD is considered to be an interim action, further actions might be required to revise/supersede the above mentioned DGAC France ADs. This [EASA] AD is revised in order to recognize that aeroplanes on which Airbus modification 44852 has been embodied in production are not affected by the repetitive inspection requirements of this [EASA] AD on the Aft Cargo Compartment Door. 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. We VerDate Mar<15>2010 14:43 Jun 22, 2012 Jkt 226001 Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Clarification of the Repetitive Inspections For clarification purposes, we changed the interval for the repetitive inspections in paragraph (g) of this AD to the following: ‘‘* * * at intervals not to exceed 800 flight cycles.’’ The repetitive interval was stated incorrectly in the NPRM (77 FR 10691, February 23, 2012) as 800 ‘‘total’’ flight cycles. Costs of Compliance We estimate that this AD will affect 55 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. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $4,675, 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 proposed 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 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 PO 00000 Frm 00048 Fmt 4700 Sfmt 4700 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. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM (77 FR 10691, February 23, 2012), the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. 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 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 AD: ■ 2012–12–12 Airbus: Amendment 39–17092. Docket No. FAA–2012–0152; Directorate Identifier 2011–NM–059–AD. (a) Effective Date This airworthiness directive (AD) becomes effective July 30, 2012. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A330– 201, –202, –203, –223, –223F, –243, –243F, E:\FR\FM\25JNR1.SGM 25JNR1 Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; and Model A340– 211, –212, –213, –311, –312, and –313 airplanes; certificated in any category; all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 52: Doors. (e) Reason This AD was prompted by reports of sheared fasteners located on the outside skin of the forward cargo door and cracks on the frame fork ends, as well as cracks of the aft cargo door frame 64A. We are issuing this AD to detect and correct sheared, loose or missing fasteners on the forward and aft cargo door frame, which could result in the loss of structural integrity of the forward and aft cargo door. (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. erowe on DSK2VPTVN1PROD with RULES (g) Forward Cargo Compartment Door Before the accumulation of 6,000 total flight cycles since first flight of the airplane or within 400 flight cycles after the effective date of this AD, whichever occurs later: Perform a detailed inspection of the outer skin rivets at the frame fork ends between FR20B and FR25 of the forward cargo door for sheared, loose, and missing rivets, in accordance with the instructions of Airbus All Operators Telex (AOT) A330–52A3085, dated December 20, 2010 (for Model A330– 200 and A330–300 series airplanes); or Airbus AOT A340–52A4092, dated December 20, 2010 (for Model A340–200 and A340–300 series airplanes). Thereafter repeat the inspection at intervals not to exceed 800 flight cycles. (h) Aft Cargo Compartment Door For all airplanes, except those on which Airbus Modification 44854 or Modification 44852 has been embodied in production, or Airbus Service Bulletin A330–52–3044 or Airbus Service Bulletin A340–52–4054 has been embodied in service: Before the accumulation of 4,000 total flight cycles since first flight of the airplane, or within 400 flight cycles after the effective date of this AD, whichever occurs later, perform a detailed inspection of outer skin rivets at the frame fork ends between FR60 and FR64A of the aft cargo door for sheared, loose or missing rivets, in accordance with the instructions of Airbus AOT A330–52A3084, dated December 20, 2010 (for Model A330– 200 and A330–300 series airplanes); or Airbus AOT A340–52A4091, dated December 20, 2010 (for Model A340–200 and A340–300 series airplanes). Thereafter repeat the inspection at intervals not to exceed 400 flight cycles. (i) Corrective Action If any sheared, loose, or missing rivets are found during any inspection required by paragraph (g) or (h) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM–116, VerDate Mar<15>2010 17:07 Jun 22, 2012 Jkt 226001 FAA; or European Aviation Safety Agency (EASA) (or its delegated agent). (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, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone (425) 227–1138; fax (425) 227–1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) 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 MCAI European Aviation Safety Agency Airworthiness Directive 2011– 0007R1, dated February 14, 2011, and the service information specified in paragraphs (k)(1) through (k)(4) of this AD, for related information. (1) Airbus AOT A330–52A3085, dated December 20, 2010. (2) Airbus AOT A340–52A4092, dated December 20, 2010. (3) Airbus AOT A330–52A3084, dated December 20, 2010. (4) Airbus AOT A340–52A4091, dated December 20, 2010. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the following service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use the following service information to do the actions required by this AD, as applicable, unless the AD specifies otherwise. (i) Airbus AOT A330–52A3085, dated December 20, 2010. The document number and date are identified only on the first page of this document. (ii) Airbus AOT A340–52A4092, dated December 20, 2010. The document number and date are identified only on the first page of this document. (iii) Airbus AOT A330–52A3084, dated December 20, 2010. The document number and date are identified only on the first page of this document. PO 00000 Frm 00049 Fmt 4700 Sfmt 4700 37799 (iv) Airbus AOT A340–52A4091, dated December 20, 2010. The document number and date are identified only on the first page of this document. (3) For Airbus service information identified in this AD, contact Airbus SAS— Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330A340@airbus.com; Internet http:// www.airbus.com. (4) You may review copies of the 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 also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at an NARA facility, call 202–741– 6030, or go to http://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on June 7, 2012. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–14730 Filed 6–22–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 97 [Docket No. 30847; Amdt. No. 3483] Standard Instrument Approach Procedures, and Takeoff Minimums and Obstacle Departure Procedures; Miscellaneous Amendments Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: This rule establishes, amends, suspends, or revokes Standard Instrument Approach Procedures (SIAPs) and associated Takeoff Minimums and Obstacle Departure Procedures for operations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, adding new obstacles, or changing air traffic requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports. SUMMARY: E:\FR\FM\25JNR1.SGM 25JNR1

Agencies

[Federal Register Volume 77, Number 122 (Monday, June 25, 2012)]
[Rules and Regulations]
[Pages 37797-37799]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-14730]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0152; Directorate Identifier 2011-NM-059-AD; 
Amendment 39-17092; AD 2012-12-12]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A330-200 series airplanes; Airbus Model A330-200 Freighter 
series airplanes; Airbus Model A330-300 series airplanes; Airbus Model 
A340-200 series airplanes; and Airbus Model A340-300 series airplanes. 
This AD was prompted by reports of sheared fasteners located on the 
outside skin of the forward cargo door and cracks on the frame fork 
ends, as well as cracks of the aft cargo door frame 64A. This AD 
requires performing a detailed inspection of the outer skin rivets at 
the frame fork ends of the forward and aft cargo door for sheared, 
loose, and missing rivets; repairing the outer skin rivets, if 
necessary; and performing repetitive inspections. We are issuing this 
AD to detect and correct sheared, loose, or missing fasteners on the 
forward and aft cargo door frame, which could result in the loss of 
structural integrity of the forward and aft cargo door.

DATES: This AD becomes effective July 30, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of July 30, 
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,

[[Page 37798]]

1200 New Jersey Avenue SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-1138; 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 was published in the Federal Register on February 23, 2012 
(77 FR 10691). That NPRM proposed to correct an unsafe condition for 
the specified products. The MCAI states:

    Two operators have reported cases of some sheared fasteners on 
the outside skin of the forward cargo door, detected during walk 
around checks. Further inspections revealed crack findings on the 
frame (FR) fork ends.
    In addition, during a scheduled maintenance check, the aft cargo 
door frame 64A of an aeroplane has been found cracked for a length 
of more than 3 inches. Outer skin rivets were also found sheared. At 
time of findings the aeroplane had accumulated 10564 flight cycles 
(FC), i.e. below the 12000 FC threshold defined in DGAC [Direction 
G[eacute]n[eacute]rale de l'Aviation Civile] France AD F-2001-124(B) 
and DGAC France AD F-2001-126(B) [which corresponds with FAA AD 
2001-16-01, Amendment 39-12369 (66 FR 40874, August 6, 2001], which 
require a special detailed inspection of the aft cargo compartment 
door.
    In case of cracked or ruptured (forward or aft) cargo door 
frame, the loads will be transferred to the remaining structural 
elements. Such second load path is able to sustain the loads for a 
limited number of flight cycles only. Rupture of two vertical frames 
could result in the loss of the structural integrity of the forward 
or aft cargo door.
    For the above described reasons, this [EASA] AD requires 
repetitive detailed visual inspections of the aft and forward cargo 
doors outer skin for sheared, loose or missing rivets at all frame 
fork ends and the accomplishment of the applicable corrective 
actions [repair if necessary].
    This [EASA] AD is considered to be an interim action, further 
actions might be required to revise/supersede the above mentioned 
DGAC France ADs.
    This [EASA] AD is revised in order to recognize that aeroplanes 
on which Airbus modification 44852 has been embodied in production 
are not affected by the repetitive inspection requirements of this 
[EASA] AD on the Aft Cargo Compartment Door.

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. We received no comments on the NPRM (77 FR 10691, February 23, 
2012) or on the determination of the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

Clarification of the Repetitive Inspections

    For clarification purposes, we changed the interval for the 
repetitive inspections in paragraph (g) of this AD to the following: 
``* * * at intervals not to exceed 800 flight cycles.'' The repetitive 
interval was stated incorrectly in the NPRM (77 FR 10691, February 23, 
2012) as 800 ``total'' flight cycles.

Costs of Compliance

    We estimate that this AD will affect 55 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 
this AD to the U.S. operators to be $4,675, 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 proposed 
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

    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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains the NPRM (77 FR 10691, February 23, 
2012), the regulatory evaluation, any comments received, and other 
information. The street address for the Docket Operations office 
(telephone (800) 647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

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 AD:

2012-12-12 Airbus: Amendment 39-17092. Docket No. FAA-2012-0152; 
Directorate Identifier 2011-NM-059-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective July 30, 
2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A330-201, -202, -203, -223, -
223F, -243, -243F,

[[Page 37799]]

-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; 
and Model A340-211, -212, -213, -311, -312, and -313 airplanes; 
certificated in any category; all manufacturer serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 52: Doors.

(e) Reason

    This AD was prompted by reports of sheared fasteners located on 
the outside skin of the forward cargo door and cracks on the frame 
fork ends, as well as cracks of the aft cargo door frame 64A. We are 
issuing this AD to detect and correct sheared, loose or missing 
fasteners on the forward and aft cargo door frame, which could 
result in the loss of structural integrity of the forward and aft 
cargo door.

(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) Forward Cargo Compartment Door

    Before the accumulation of 6,000 total flight cycles since first 
flight of the airplane or within 400 flight cycles after the 
effective date of this AD, whichever occurs later: Perform a 
detailed inspection of the outer skin rivets at the frame fork ends 
between FR20B and FR25 of the forward cargo door for sheared, loose, 
and missing rivets, in accordance with the instructions of Airbus 
All Operators Telex (AOT) A330-52A3085, dated December 20, 2010 (for 
Model A330-200 and A330-300 series airplanes); or Airbus AOT A340-
52A4092, dated December 20, 2010 (for Model A340-200 and A340-300 
series airplanes). Thereafter repeat the inspection at intervals not 
to exceed 800 flight cycles.

(h) Aft Cargo Compartment Door

    For all airplanes, except those on which Airbus Modification 
44854 or Modification 44852 has been embodied in production, or 
Airbus Service Bulletin A330-52-3044 or Airbus Service Bulletin 
A340-52-4054 has been embodied in service: Before the accumulation 
of 4,000 total flight cycles since first flight of the airplane, or 
within 400 flight cycles after the effective date of this AD, 
whichever occurs later, perform a detailed inspection of outer skin 
rivets at the frame fork ends between FR60 and FR64A of the aft 
cargo door for sheared, loose or missing rivets, in accordance with 
the instructions of Airbus AOT A330-52A3084, dated December 20, 2010 
(for Model A330-200 and A330-300 series airplanes); or Airbus AOT 
A340-52A4091, dated December 20, 2010 (for Model A340-200 and A340-
300 series airplanes). Thereafter repeat the inspection at intervals 
not to exceed 400 flight cycles.

(i) Corrective Action

    If any sheared, loose, or missing rivets are found during any 
inspection required by paragraph (g) or (h) of this AD: Before 
further flight, repair using a method approved by the Manager, 
International Branch, ANM-116, FAA; or European Aviation Safety 
Agency (EASA) (or its delegated agent).

(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, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or local Flight Standards District Office, as 
appropriate. If sending information directly to the International 
Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-1138; fax (425) 227-1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify 
your appropriate principal inspector, or lacking a principal 
inspector, the manager of the local flight standards district 
office/certificate holding district office. The AMOC approval letter 
must specifically reference this AD.
    (2) 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 MCAI European Aviation Safety Agency Airworthiness 
Directive 2011-0007R1, dated February 14, 2011, and the service 
information specified in paragraphs (k)(1) through (k)(4) of this 
AD, for related information.
    (1) Airbus AOT A330-52A3085, dated December 20, 2010.
    (2) Airbus AOT A340-52A4092, dated December 20, 2010.
    (3) Airbus AOT A330-52A3084, dated December 20, 2010.
    (4) Airbus AOT A340-52A4091, dated December 20, 2010.

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the following service 
information under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use the following service information to do the 
actions required by this AD, as applicable, unless the AD specifies 
otherwise.
    (i) Airbus AOT A330-52A3085, dated December 20, 2010. The 
document number and date are identified only on the first page of 
this document.
    (ii) Airbus AOT A340-52A4092, dated December 20, 2010. The 
document number and date are identified only on the first page of 
this document.
    (iii) Airbus AOT A330-52A3084, dated December 20, 2010. The 
document number and date are identified only on the first page of 
this document.
    (iv) Airbus AOT A340-52A4091, dated December 20, 2010. The 
document number and date are identified only on the first page of 
this document.
    (3) For Airbus service information identified in this AD, 
contact Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; 
Internet http://www.airbus.com.
    (4) You may review copies of the 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 also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at an NARA facility, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on June 7, 2012.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-14730 Filed 6-22-12; 8:45 am]
BILLING CODE 4910-13-P