Airworthiness Directives; Airbus Model A300 B4-103, B4-203, and B4-2C Airplanes, 33176-33179 [2011-14094]

Download as PDF 33176 Federal Register / Vol. 76, No. 110 / Wednesday, June 8, 2011 / Proposed Rules Note 1: Bombardier Service Bulletin 8–52– 54 refers to Bombardier Series 100/300 Modification Summary (Modsum) 8Q100859 as an additional source of guidance for installing a hinge pin with a two-point attachment. Bombardier Service Bulletin 8– 52–58 refers to Bombardier Series 100/300 Modsum 8Q900267 as an additional source of guidance for reworking and installing the cockpit door, and reworking the lower hinge attachment to provide a downward-facing pin with a two-point attachment. Prior/Concurrent Requirements (h) Prior to or concurrently with the modification in paragraph (g) of this AD, do the applicable actions specified in Table 3 of this AD, according to a method approved by either the Manager, New York Aircraft Certification (ACO), FAA; or Transport Canada Civil Aviation (TCCA) (or its delegated agent). TABLE 3—BOMBARDIER SERVICE BULLETINS FOR REQUIREMENTS OF PARAGRAPH (H) OF THIS AD For airplanes affected by Bombardier Service Bulletin— That have these serial numbers— 8–52–54, Revision A, dated November 5, 2004 003 through 407 inclusive, 409 through 412 inclusive, and 414 through 433 inclusive. .......................................................................... 8–52–58, dated May 12, 2004 ........................... Note 2: Bombardier Service Bulletin 8–52– 54, Revision A, dated November 5, 2004, refers to De Havilland Aircraft of Canada, Limited, Modification 8/2337 as an additional source of guidance for reworking the cockpit door emergency release; and Modification 8/3339 as additional source of guidance for installing a new label regarding alternate release of the door, on airplanes having serial numbers 003 through 407 inclusive, 409 through 412 inclusive, and 414 through 433 inclusive. Note 3: Bombardier Service Bulletin 8–52– 58, dated May 12, 2004; and Revision A, dated November 17, 2006; refer to Bombardier Modsum 8Q200015, as an additional source of guidance for installing the cockpit door, on airplanes having serial numbers 452, 464, 490, 506, and 508 through 557 inclusive. Actions Done In Accordance With Previous Revision of Service Bulletin (i) Actions done before July 18, 2006, in accordance with Bombardier Service Bulletin 8–52–54, dated May 12, 2004, are acceptable for compliance with the corresponding requirements in paragraph (g) of this AD. jlentini on DSK4TPTVN1PROD with PROPOSALS New Requirements of This AD (j) For airplanes having S/N 452, 464, 490, 506, and 508 through 557 inclusive, and on which the requirements in paragraph (g) of this AD have been done as of the effective date of this AD: Within 12 months after the effective date of this AD rework the cockpit door striker plate and replace the latch block, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–52–61, dated October 20, 2006. (k) For airplanes having S/Ns 452, 464, 490, 506, and 508 through 557 inclusive, and on which the requirements in paragraph (g) of this AD have not been done as of the effective date of this AD: Prior to or concurrently with doing the modification required in paragraph (g) of this AD, rework the cockpit door striker plate and replace the latch block, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–52–61, dated October 20, 2006. VerDate Mar<15>2010 17:24 Jun 07, 2011 Jkt 223001 452, 464, 490, 506, and 508 through 557 inclusive. FAA AD Differences Note 4: This AD differs from the MCAI and/or service information as follows: No differences. Do these actions— Rework the cockpit door emergency release. Install a new label regarding alternate release of the door. Install the cockpit door. Issued in Renton, Washington, on May 27, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. Other FAA AD Provisions [FR Doc. 2011–14091 Filed 6–7–11; 8:45 am] (l) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office, ANE–170, 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 ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone 516–228–7300; fax 516–794–5531. 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. BILLING CODE 4910–13–P Related Information (m) Refer to MCAI Canadian Airworthiness Directive CF–2005–34R1, dated August 15, 2007; Bombardier Service Bulletin 8–52–54, Revision A, dated November 5, 2004; Bombardier Service Bulletin 8–52–58, Revision A, dated November 17, 2006; and Bombardier Service Bulletin 8–52–61, dated October 20, 2006; for related information. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0478; Directorate Identifier 2010–NM–138–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B4–103, B4–203, and B4–2C Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the products listed above that would supersede an existing AD. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: SUMMARY: One operator reported a failure of the MLG [main landing gear] retraction actuator sliding rod. This incident occurred at a number of operating flight cycles lower than the limit value imposed by the MLG manufacturer. This condition, if not detected and corrected, results in undampened extension of the MLG, leading to higher than usual loads on the MLG attachment. Higher loads E:\FR\FM\08JNP1.SGM 08JNP1 Federal Register / Vol. 76, No. 110 / Wednesday, June 8, 2011 / Proposed Rules affect the structural integrity of the MLG and could lead to MLG failure. * * * * * The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by July 25, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For Airbus service information identified in this proposed 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; e-mail account.airwortheas@airbus.com; Internet https:// www.airbus.com. For Messier-Dowty service information identified in this proposed AD, contact Messier-Dowty: Messier Services Americas, Customer Support Center, 45360 Severn Way, Sterling, Virginia 20166–8910; telephone 703–450–8233; fax 703–404– 1621; Internet https://techpubs.services/ messier-dowty.com. 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. jlentini on DSK4TPTVN1PROD with PROPOSALS Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, VerDate Mar<15>2010 17:24 Jun 07, 2011 Jkt 223001 Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2011–0478; Directorate Identifier 2010–NM–138–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On November 29, 2007, we issued AD 2007–25–15, Amendment 39–15297 (72 FR 69601, December 10, 2007). That AD required actions intended to address an unsafe condition on all Airbus Model A300 series airplanes and all Airbus Model A300–600 series airplanes. Since we issued AD 2007–25–15, the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2010–0102, dated June 8, 2010 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: One operator reported a failure of the MLG [main landing gear] retraction actuator sliding rod. This incident occurred at a number of operating flight cycles lower than the limit value imposed by the MLG manufacturer. This condition, if not detected and corrected, results in undampened extension of the MLG, leading to higher than usual loads on the MLG attachment. Higher loads affect the structural integrity of the MLG and could lead to MLG failure. To address and correct this unsafe condition, EASA issued AD 2006–0075 (now at Revision 2) [which corresponds to FAA AD 2007–25–15] to require repetitive inspections of the retraction actuator sliding rod as installed on A300, A300–600 and A300–600ST aeroplanes and, depending on findings, repair or replacement of the affected parts. Since this event, studies have been performed by Airbus, the consequences of which are that for A300 aeroplanes, a new PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 33177 inspection program (new threshold and interval) has been established. For the reason described above, this new [EASA] AD retains the requirements of AD 2006–0075R2, which is superseded and requires the accomplishment of the repetitive inspections and associated corrective actions at the new intervals. In addition, the Airbus A300 Aircraft Maintenance Manual (AMM) Chapter 12–22–32 (associated to Maintenance Planning Document (MPD) task 321112–0505–1) has been revised to introduce a greasing action at the level of the pick-up jack fitting. Consequently, this AD also requires the repetitive lubrication task. For A300–600 and A300–600ST aeroplanes, the analyses have shown that, due to design differences, the loads induced on the MLG attachments are within acceptable margins. For that reason, this AD does not apply to those aeroplanes which were previously included in the applicability of EASA AD 2006–0075R2. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued Mandatory Service Bulletin A300–32–0450, including Appendix 1, Revision 02, dated July 28, 2009; and Task 321112–0505–1 of the A300 Maintenance Planning Document, Revision 30, dated April 1, 2010. Messier-Dowty has issued Special Inspection Service Bulletin 470–32–806, dated October 27, 2005. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. E:\FR\FM\08JNP1.SGM 08JNP1 33178 Federal Register / Vol. 76, No. 110 / Wednesday, June 8, 2011 / Proposed Rules We might also have proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a Note within the proposed AD. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 3 products of U.S. registry. We estimate that it would take about 6 work-hours per product to comply with the new basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $1,530, or $510 per product. In addition, we estimate that any necessary follow-on actions would take about 6 work-hours and require parts costing $0, for a cost of $510 per product. We have no way of determining the number of products that may need these actions. 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. jlentini on DSK4TPTVN1PROD with PROPOSALS Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; VerDate Mar<15>2010 17:24 Jun 07, 2011 Jkt 223001 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. 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 proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 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 removing Amendment 39–15297 (72 FR 69601, December 10, 2007) and adding the following new AD: Airbus: Docket No. FAA–2011–0478; Directorate Identifier 2010–NM–138–AD. Comments Due Date (a) We must receive comments by July 25, 2011. Affected ADs (b) This AD supersedes AD 2007–25–15, Amendment 39–15297. Applicability (c) This AD applies to all Airbus Model A300 B4–103, B4–203, and B4–2C airplanes; certificated in any category; equipped with MLG retraction actuator having part number (P/N) C23129 fitted with sliding rod P/N C69029–2 or C69029–3. Subject (d) Air Transport Association (ATA) of America Code 32: Landing gear. Reason (e) The mandatory continuing airworthiness information (MCAI) states: One operator reported a failure of the MLG [main landing gear] retraction actuator sliding rod. This incident occurred at a number of operating flight cycles lower than the limit value imposed by the MLG manufacturer. This condition, if not detected and corrected, results in undampened extension of the MLG, leading to higher than usual loads on the MLG attachment. Higher loads PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 affect the structural integrity of the MLG and could lead to MLG failure. * * * * * Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Revised Compliance Times for Inspection of MLG Retraction Actuator and Corrective Actions (g) At the applicable time specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD: Remove the MLG retraction actuator having P/N C23129 and do a detailed and high frequency eddy current inspection for defects that exceed the criteria defined in MessierDowty Special Inspection Service Bulletin 470–32–806, dated October 27, 2005, of the retraction actuator sliding rods having P/N C69029–2 or C69029–3, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–32–0450, Revision 02, dated July 28, 2009. (1) For airplanes on which the retraction actuator sliding rod has accumulated 12,000 or fewer total flight cycles as of the effective date of this AD: Inspect at the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. (i) Before the accumulation of 12,000 total flight cycles on the retraction actuator sliding rod. (ii) Within 2,000 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (2) For airplanes on which the retraction actuator sliding rod has accumulated more than 12,000 total flight cycles, and 22,000 or fewer total flight cycles, as of the effective date of this AD: Inspect at the earliest of the times specified in paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD. (i) Before the accumulation of 23,000 total flight cycles on the retraction actuator sliding rod. (ii) Within 2,000 flight cycles after the effective date of this AD. (iii) Within 24 months after the effective date of this AD. (3) For airplanes on which the retraction actuator sliding rod has accumulated more than 22,000 total flight cycles as of the effective date of this AD: Inspect within 1,000 flight cycles or 12 months after the effective date of this AD, whichever occurs first. (h) Thereafter, repeat the inspection required by paragraph (g) of this AD at intervals not to exceed 12,000 flight cycles. (i) If, during any inspection required by paragraph (g) or (h) of this AD, any defect is detected that exceeds the criteria defined in Messier-Dowty Special Inspection Service Bulletin 470–32–806, dated October 27, 2005, before further flight, replace the affected sliding rod with a serviceable unit in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–32–0450, Revision 02, dated July 28, 2009. (j) Before the accumulation of 32,000 flight cycles on any retraction actuator sliding rod, it must be replaced with a serviceable unit E:\FR\FM\08JNP1.SGM 08JNP1 Federal Register / Vol. 76, No. 110 / Wednesday, June 8, 2011 / Proposed Rules in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–32–0450, Revision 02, dated July 28, 2009. Parts removed from an airplane as required by this paragraph must be returned to Messier-Dowty within 30 days after removing the part from the airplane. (k) As of the effective date of this AD, any MLG retraction actuator sliding rod having P/ N C69029–2 or C69029–3 that has accumulated less than 32,000 total flight cycles, may be installed on any airplane, provided that the inspections required by paragraphs (g) and (h) of this AD are accomplished at the compliance times specified in paragraphs (g) and (h) of this AD and all applicable replacements required by paragraphs (i) and (j) of this AD are done. Lubrication of the MLG Assembly (l) Within 1,500 flight hours after the effective date of this AD: Clean and lubricate the MLG assembly, in accordance with Task 321112–0505–1 of the Airbus A300 Maintenance Planning Document, Revision 30, dated April 1, 2010. Repeat the cleaning and lubrication thereafter at intervals not to exceed 1,500 flight hours. Credit for Actions Accomplished in Accordance With Previous Service Information (m) Inspections accomplished before the effective date of this AD, in accordance with Airbus Service Bulletin A300–32–0450, dated December 1, 2005; or Airbus Mandatory Service Bulletin A300–32–0450, Revision 01, dated May 10, 2006; are acceptable for compliance with the corresponding requirements of this AD. AMOCs for the corresponding provisions of 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. Related Information (o) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2010– 0102, dated June 8, 2010; Airbus Mandatory Service Bulletin A300–32–0450, Revision 02, dated July 28, 2009; Messier-Dowty Special Inspection Service Bulletin 470–32–806, dated October 27, 2005; and Task 321112– 0505–1 of the Airbus A300 Maintenance Planning Document, Revision 30, dated April 1, 2010; for related information. Issued in Renton, Washington, on May 27, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–14094 Filed 6–7–11; 8:45 am] BILLING CODE 4910–13–P CONSUMER PRODUCT SAFETY COMMISSION 16 CFR 1460 Petition Requesting Safeguards for Glass Fronts of Gas Vented Fireplaces Note 1 : This AD differs from the MCAI and/or service information as follows: No differences. jlentini on DSK4TPTVN1PROD with PROPOSALS FAA AD Differences AGENCY: Other FAA AD Provisions (n) 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 e-mailed 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. AMOCs approved previously in accordance with AD 2007–25–15, amendment 39–15297, are approved as VerDate Mar<15>2010 17:24 Jun 07, 2011 Jkt 223001 U.S. Consumer Product Safety Commission. ACTION: Notice. The U.S. Consumer Product Safety Commission (‘‘Commission’’ or ‘‘we’’) has received a petition (CP 11–1) requesting that the Commission initiate rulemaking to require safeguards for glass fronts of gas vented fireplaces. We invite written comments concerning the petition. DATES: The Office of the Secretary must receive comments on the petition by August 8, 2011. ADDRESSES: You may submit comments, identified by Docket No. CPSC–2011– 0028, by any of the following methods: SUMMARY: Electronic Submissions Submit electronic comments in the following way: Federal eRulemaking Portal: https:// www.regulations.gov. Follow the instructions for submitting comments. To ensure timely processing of comments, the Commission is no longer accepting comments submitted by electronic mail (e-mail), except through https://www.regulations.gov. PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 33179 Written Submissions Submit written submissions in the following way: Mail/Hand delivery/Courier (for paper, disk, or CD–ROM submissions), preferably in five copies, to: Office of the Secretary, U.S. Consumer Product Safety Commission, Room 820, 4330 East West Highway, Bethesda, MD 20814; telephone (301) 504–7923. Instructions: All submissions received must include the agency name and petition number for this rulemaking. All comments received may be posted without change, including any personal identifiers, contact information, or other personal information provided, to: https://www.regulations.gov. Do not submit confidential business information, trade secret information, or other sensitive or protected information electronically. Such information should be submitted in writing. Docket: For access to the docket to read background documents or comments received, go to: https:// www.regulations.gov. FOR FURTHER INFORMATION CONTACT: Rockelle Hammond, Office of the Secretary, U.S. Consumer Product Safety Commission, Room 820, 4330 East West Highway, Bethesda, MD 20814; telephone (301) 504–6833. SUPPLEMENTARY INFORMATION: The Commission has received correspondence from Carol PollackNelson, Ph.D. (‘‘petitioner’’), dated May 23, 2011, requesting that we initiate rulemaking to require safeguards for glass fronts of gas vented fireplaces. We are docketing this request as a petition under the Consumer Product Safety Act. 15 U.S.C. 2056 and 2058. Petitioner notes that the industry standard for gas vented fireplace heaters allows glass fronts to reach temperatures of 500 degrees Fahrenheit, and that these glass fronts are accessible to children. Petitioner claims that, according to the U.S. Consumer Product Safety Commission’s National Electronic Injury Surveillance System database (NEISS), more than 2,000 children ages 0–5 years suffered burn injuries on gas fireplaces in the period between 1999 and March 2009. Petitioner believes the hazard posed by gas fireplaces is due to a combination of factors, ‘‘including the high surface temperature of the fireplace glass, the accessible location of the glass front, the attractiveness of fire to young children, and the lack of consumer awareness of the hazard.’’ Petitioner states that passive interventions, such as an ‘‘integral safety screen,’’ are needed to protect children. Petitioner asks the Commission to develop a mandatory standard for gas fireplaces that requires E:\FR\FM\08JNP1.SGM 08JNP1

Agencies

[Federal Register Volume 76, Number 110 (Wednesday, June 8, 2011)]
[Proposed Rules]
[Pages 33176-33179]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-14094]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0478; Directorate Identifier 2010-NM-138-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B4-103, B4-203, and 
B4-2C Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above that would supersede an existing AD. This 
proposed AD results from mandatory continuing airworthiness information 
(MCAI) originated by an aviation authority of another country to 
identify and correct an unsafe condition on an aviation product. The 
MCAI describes the unsafe condition as:

    One operator reported a failure of the MLG [main landing gear] 
retraction actuator sliding rod. This incident occurred at a number 
of operating flight cycles lower than the limit value imposed by the 
MLG manufacturer.
    This condition, if not detected and corrected, results in 
undampened extension of the MLG, leading to higher than usual loads 
on the MLG attachment. Higher loads

[[Page 33177]]

affect the structural integrity of the MLG and could lead to MLG 
failure.
* * * * *
    The proposed AD would require actions that are intended to address 
the unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by July 25, 2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New 
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For Airbus service information identified in this proposed 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; e-mail account.airworth-eas@airbus.com; Internet 
https://www.airbus.com. For Messier-Dowty service information identified 
in this proposed AD, contact Messier-Dowty: Messier Services Americas, 
Customer Support Center, 45360 Severn Way, Sterling, Virginia 20166-
8910; telephone 703-450-8233; fax 703-404-1621; Internet https://techpubs.services/messier-dowty.com. 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://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 this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
in the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2011-0478; 
Directorate Identifier 2010-NM-138-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On November 29, 2007, we issued AD 2007-25-15, Amendment 39-15297 
(72 FR 69601, December 10, 2007). That AD required actions intended to 
address an unsafe condition on all Airbus Model A300 series airplanes 
and all Airbus Model A300-600 series airplanes.
    Since we issued AD 2007-25-15, the European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Community, has issued EASA Airworthiness Directive 2010-0102, 
dated June 8, 2010 (referred to after this as ``the MCAI''), to correct 
an unsafe condition for the specified products. The MCAI states:

    One operator reported a failure of the MLG [main landing gear] 
retraction actuator sliding rod. This incident occurred at a number 
of operating flight cycles lower than the limit value imposed by the 
MLG manufacturer.
    This condition, if not detected and corrected, results in 
undampened extension of the MLG, leading to higher than usual loads 
on the MLG attachment. Higher loads affect the structural integrity 
of the MLG and could lead to MLG failure.
    To address and correct this unsafe condition, EASA issued AD 
2006-0075 (now at Revision 2) [which corresponds to FAA AD 2007-25-
15] to require repetitive inspections of the retraction actuator 
sliding rod as installed on A300, A300-600 and A300-600ST aeroplanes 
and, depending on findings, repair or replacement of the affected 
parts.
    Since this event, studies have been performed by Airbus, the 
consequences of which are that for A300 aeroplanes, a new inspection 
program (new threshold and interval) has been established.
    For the reason described above, this new [EASA] AD retains the 
requirements of AD 2006-0075R2, which is superseded and requires the 
accomplishment of the repetitive inspections and associated 
corrective actions at the new intervals. In addition, the Airbus 
A300 Aircraft Maintenance Manual (AMM) Chapter 12-22-32 (associated 
to Maintenance Planning Document (MPD) task 321112-0505-1) has been 
revised to introduce a greasing action at the level of the pick-up 
jack fitting. Consequently, this AD also requires the repetitive 
lubrication task.
    For A300-600 and A300-600ST aeroplanes, the analyses have shown 
that, due to design differences, the loads induced on the MLG 
attachments are within acceptable margins. For that reason, this AD 
does not apply to those aeroplanes which were previously included in 
the applicability of EASA AD 2006-0075R2.

You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Airbus has issued Mandatory Service Bulletin A300-32-0450, 
including Appendix 1, Revision 02, dated July 28, 2009; and Task 
321112-0505-1 of the A300 Maintenance Planning Document, Revision 30, 
dated April 1, 2010. Messier-Dowty has issued Special Inspection 
Service Bulletin 470-32-806, dated October 27, 2005. The actions 
described in this service information are intended to correct the 
unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.

[[Page 33178]]

    We might also have proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a Note within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 3 products of U.S. registry.
    We estimate that it would take about 6 work-hours per product to 
comply with the new basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of the proposed AD on U.S. operators to be $1,530, or $510 per 
product.
    In addition, we estimate that any necessary follow-on actions would 
take about 6 work-hours and require parts costing $0, for a cost of 
$510 per product. We have no way of determining the number of products 
that may need these actions.

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. 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 proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    2. The FAA amends Sec.  39.13 by removing Amendment 39-15297 (72 FR 
69601, December 10, 2007) and adding the following new AD:

Airbus: Docket No. FAA-2011-0478; Directorate Identifier 2010-NM-
138-AD.

Comments Due Date

    (a) We must receive comments by July 25, 2011.

Affected ADs

    (b) This AD supersedes AD 2007-25-15, Amendment 39-15297.

Applicability

    (c) This AD applies to all Airbus Model A300 B4-103, B4-203, and 
B4-2C airplanes; certificated in any category; equipped with MLG 
retraction actuator having part number (P/N) C23129 fitted with 
sliding rod P/N C69029-2 or C69029-3.

Subject

    (d) Air Transport Association (ATA) of America Code 32: Landing 
gear.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    One operator reported a failure of the MLG [main landing gear] 
retraction actuator sliding rod. This incident occurred at a number 
of operating flight cycles lower than the limit value imposed by the 
MLG manufacturer.
    This condition, if not detected and corrected, results in 
undampened extension of the MLG, leading to higher than usual loads 
on the MLG attachment. Higher loads affect the structural integrity 
of the MLG and could lead to MLG failure.
* * * * *

Compliance

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

Revised Compliance Times for Inspection of MLG Retraction Actuator and 
Corrective Actions

    (g) At the applicable time specified in paragraphs (g)(1), 
(g)(2), and (g)(3) of this AD: Remove the MLG retraction actuator 
having P/N C23129 and do a detailed and high frequency eddy current 
inspection for defects that exceed the criteria defined in Messier-
Dowty Special Inspection Service Bulletin 470-32-806, dated October 
27, 2005, of the retraction actuator sliding rods having P/N C69029-
2 or C69029-3, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A300-32-0450, Revision 02, dated 
July 28, 2009.
    (1) For airplanes on which the retraction actuator sliding rod 
has accumulated 12,000 or fewer total flight cycles as of the 
effective date of this AD: Inspect at the later of the times 
specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.
    (i) Before the accumulation of 12,000 total flight cycles on the 
retraction actuator sliding rod.
    (ii) Within 2,000 flight cycles or 24 months after the effective 
date of this AD, whichever occurs first.
    (2) For airplanes on which the retraction actuator sliding rod 
has accumulated more than 12,000 total flight cycles, and 22,000 or 
fewer total flight cycles, as of the effective date of this AD: 
Inspect at the earliest of the times specified in paragraphs 
(g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD.
    (i) Before the accumulation of 23,000 total flight cycles on the 
retraction actuator sliding rod.
    (ii) Within 2,000 flight cycles after the effective date of this 
AD.
    (iii) Within 24 months after the effective date of this AD.
    (3) For airplanes on which the retraction actuator sliding rod 
has accumulated more than 22,000 total flight cycles as of the 
effective date of this AD: Inspect within 1,000 flight cycles or 12 
months after the effective date of this AD, whichever occurs first.
    (h) Thereafter, repeat the inspection required by paragraph (g) 
of this AD at intervals not to exceed 12,000 flight cycles.
    (i) If, during any inspection required by paragraph (g) or (h) 
of this AD, any defect is detected that exceeds the criteria defined 
in Messier-Dowty Special Inspection Service Bulletin 470-32-806, 
dated October 27, 2005, before further flight, replace the affected 
sliding rod with a serviceable unit in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-32-0450, Revision 02, dated July 28, 2009.
    (j) Before the accumulation of 32,000 flight cycles on any 
retraction actuator sliding rod, it must be replaced with a 
serviceable unit

[[Page 33179]]

in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A300-32-0450, Revision 02, dated July 28, 
2009. Parts removed from an airplane as required by this paragraph 
must be returned to Messier-Dowty within 30 days after removing the 
part from the airplane.
    (k) As of the effective date of this AD, any MLG retraction 
actuator sliding rod having P/N C69029-2 or C69029-3 that has 
accumulated less than 32,000 total flight cycles, may be installed 
on any airplane, provided that the inspections required by 
paragraphs (g) and (h) of this AD are accomplished at the compliance 
times specified in paragraphs (g) and (h) of this AD and all 
applicable replacements required by paragraphs (i) and (j) of this 
AD are done.

Lubrication of the MLG Assembly

    (l) Within 1,500 flight hours after the effective date of this 
AD: Clean and lubricate the MLG assembly, in accordance with Task 
321112-0505-1 of the Airbus A300 Maintenance Planning Document, 
Revision 30, dated April 1, 2010. Repeat the cleaning and 
lubrication thereafter at intervals not to exceed 1,500 flight 
hours.

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (m) Inspections accomplished before the effective date of this 
AD, in accordance with Airbus Service Bulletin A300-32-0450, dated 
December 1, 2005; or Airbus Mandatory Service Bulletin A300-32-0450, 
Revision 01, dated May 10, 2006; are acceptable for compliance with 
the corresponding requirements of this AD.

FAA AD Differences

    Note 1 : This AD differs from the MCAI and/or service 
information as follows: No differences.

Other FAA AD Provisions

    (n) 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 e-mailed 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. AMOCs approved previously in accordance with AD 2007-25-15, 
amendment 39-15297, are approved as AMOCs for the corresponding 
provisions of 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.

Related Information

    (o) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2010-0102, dated June 8, 2010; Airbus Mandatory Service 
Bulletin A300-32-0450, Revision 02, dated July 28, 2009; Messier-
Dowty Special Inspection Service Bulletin 470-32-806, dated October 
27, 2005; and Task 321112-0505-1 of the Airbus A300 Maintenance 
Planning Document, Revision 30, dated April 1, 2010; for related 
information.

    Issued in Renton, Washington, on May 27, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-14094 Filed 6-7-11; 8:45 am]
BILLING CODE 4910-13-P
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