Airworthiness Directives; Airbus Model A310-203, -204, and -222 Airplanes, and Model A310-300 Series Airplanes, 61924-61927 [05-21428]

Download as PDF 61924 Federal Register / Vol. 70, No. 207 / Thursday, October 27, 2005 / Proposed Rules 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 have 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 that the 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. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, 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 Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2005–22794; Directorate Identifier 2005–NM–097–AD. VerDate Aug<31>2005 14:39 Oct 26, 2005 Jkt 208001 Comments Due Date (a) The FAA must receive comments on this AD action by November 28, 2005. Affected ADs (b) None. Applicability (c) This AD applies to all Airbus Model A318–111 and –112 airplanes, Model A319– 111, –112, –113, –114, –115, –131, –132, and –133 airplanes, Model A320–111 airplanes, Model A320–211, –212, –214, –231, –232, and –233 airplanes, Model A321–111, –112, and –131 airplanes, and Model A321–211 and –231 airplanes, certificated in any category. Unsafe Condition (d) This AD results from a report that during lab testing to verify the performance of the trimmable horizontal stabilizer actuator’s (THSA’s) secondary load path with a simulated failure of the THSA’s primary load path, the secondary load path’s nut did not jam (as it was supposed to do.) We are issuing this AD to ensure the integrity of the THSA’s primary load path, which if failed, could result in latent (undetected) loading and eventual failure of the THSA’s secondary load path and consequent uncontrolled movement of the horizontal stabilizer and loss of control of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Repetitive Inspections and Corrective Action (f) Within 20 months since first flight, or within 600 flight hours after the effective date of this AD, whichever occurs later, do detailed inspections of the THSA attachments for proper clearances and any crack, damage, or metallic particles, and do related corrective actions as applicable, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 27–1164, Revision 02, dated March 30, 2005, except as described in paragraph (g) of this AD. Do corrective actions before further flight. Thereafter, repeat the inspections at intervals not to exceed 20 months. Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ (g) If any metallic particles are detected during the inspection required by paragraph (f) of this AD: Before further flight, repair the damage according to a method approved by either the Manager, International Branch, ANM–116, FAA, Transport Airplane ´ ´ Directorate; or the Direction Generale de l’Aviation Civile (DGAC) (or its delegated agent). PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 Inspection Reports (h) Submit a report of the findings (both positive and negative) of the inspection required by paragraph (f) of this AD to Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane. Under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120–0056. (1) If the inspection was done after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If any inspection was accomplished prior to the effective date of this AD: Submit the report within 30 days after the effective date of this AD. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (j) French airworthiness directive F–2005– 051, dated March 30, 2005, also addresses the subject of this AD. Issued in Renton, Washington, on October 18, 2005. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–21434 Filed 10–26–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22810; Directorate Identifier 2005–NM–143–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A310–203, –204, and –222 Airplanes, and Model A310–300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: E:\FR\FM\27OCP1.SGM 27OCP1 Federal Register / Vol. 70, No. 207 / Thursday, October 27, 2005 / Proposed Rules SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Airbus Model A310–203, –204, and –222 airplanes, and Model A310– 300 series airplanes. This proposed AD would require a one-time rototest inspection for cracking of the frame foot and adjacent frames and skin in the area surrounding the frame foot run-outs from fuselage frames (FR) 43 through FR 46, and repair if necessary. The proposed AD also requires modification of certain fastener holes. This proposed AD results from a structural evaluation of Model A310 airplanes for widespread fatigue damage of the frame foot runouts from FR 43 through FR 46. The evaluation revealed that, on in-service airplanes, undetected cracking in this area can lead to the rupture of the frame foot and subsequent cracking of the adjacent frames and fuselage skin. We are proposing this AD to prevent fatigue cracking of the frame foot run-outs, which could lead to rupture of the frame foot and cracking in adjacent frames and skin, and result in reduced structural integrity of the fuselage. DATES: We must receive comments on this proposed AD by November 28, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments VerDate Aug<31>2005 14:39 Oct 26, 2005 Jkt 208001 regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2005–22810; Directorate Identifier 2005–NM–143–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion ´ ´ The Direction Generale de l’Aviation Civile (DGAC), which is the airworthiness authority for France, notified us that an unsafe condition may exist on certain Airbus Model A310– 203, –204, and –222 airplanes, and Model A310–300 series airplanes. The DGAC advises that a structural evaluation for widespread fatigue damage of the frame foot run-outs from fuselage frame (FR) 43 through FR 46 was done on the subject airplanes. The evaluation revealed that, on in-service airplanes, undetected cracking in this area can lead to the rupture of the frame foot and subsequent cracking of the adjacent frames and fuselage skin. Such cracking would require an extensive repair and could have an impact on pressure loading strength capacity of the PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 61925 structure. These conditions, if not corrected, could result in reduced structural integrity of the fuselage. Relevant Service Information Airbus has issued Service Bulletin A310–53–2124, dated April 4, 2005. The service bulletin describes procedures for performing a one-time rototest inspection to find cracking of the frame foot and adjacent frames and skin in the area surrounding the frame foot run-outs from FR 43 through FR 46, and repair of cracking within certain limits. If the cracking is outside the limits specified in the service bulletin, the service bulletin procedures recommend contacting the manufacturer for repair instructions. The service bulletin also describes procedures for modification of certain fastener holes. The modification includes cold expanding the fastener holes most susceptible to fatigue, which are located between FR 43 and FR 46 on the center box and on the upper fuselage bent sections, and installing new fasteners. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The DGAC mandated the service information and issued French airworthiness directive F–2005– 078, dated May 11, 2005, to ensure the continued airworthiness of these airplanes in France. Section 1.E., Compliance, of the service bulletin specifies compliance times for the actions in the service bulletin. The thresholds for the one-time inspection and modification range from between 22,200 flight cycles or 51,700 flight hours, whichever is first, to 26,800 flight cycles or 77,700 flight hours, whichever is first, depending on the configuration of the airplane. The service bulletin also includes a grace period of 3,000 flight cycles for airplanes that have exceeded certain flight-hour or flight-cycle thresholds, depending on the configuration of the airplane. FAA’s Determination and Requirements of the Proposed AD These airplane models are manufactured in France and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the DGAC has kept the FAA informed of the situation described above. We have examined the DGAC’s findings, evaluated all pertinent information, and determined that we need to issue an AD for airplanes of this E:\FR\FM\27OCP1.SGM 27OCP1 61926 Federal Register / Vol. 70, No. 207 / Thursday, October 27, 2005 / Proposed Rules type design that are certificated for operation in the United States. Therefore, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Among Proposed AD, French Airworthiness Directive, and Service Bulletin.’’ Differences Among Proposed AD, French Airworthiness Directive, and Service Bulletin The applicability of the French Airworthiness Directive excludes airplanes on which Airbus Service Bulletin A310–53–2124 has been accomplished in service. However, we have not excluded those airplanes in the applicability of this proposed AD; rather, this proposed AD would include a requirement to accomplish the actions specified in that service bulletin. This proposed AD would ensure that the actions specified in the service bulletin and required by this proposed AD are accomplished on all affected airplanes. Operators must continue to operate the airplane in the configuration required by this proposed AD unless an alternative method of compliance is approved. The service bulletin specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions using a method that we or the DGAC (or its delegated agent) approve. In light of the type of repair that would be required to address the unsafe condition, and consistent with existing bilateral airworthiness agreements, we have determined that, for this proposed AD, a repair we or the DGAC approve would be acceptable for compliance with this proposed AD. Costs of Compliance This proposed AD would affect about 59 airplanes of U.S. registry. The proposed actions would take about 31 work hours per airplane, at an average labor rate of $65 per work hour. Required parts would cost about $1,730 per kit (two kits per airplane). Based on these figures, the estimated cost of the proposed AD for U.S. operators is $323,025, or $5,475 per airplane. 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 VerDate Aug<31>2005 14:39 Oct 26, 2005 Jkt 208001 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 have 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 that the 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. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, 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 Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 Airbus: Docket No. FAA–2005–22810; Directorate Identifier 2005–NM–143–AD. Comments Due Date (a) The FAA must receive comments on this AD action by November 28, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A310– 203, –204, and –222 airplanes, and Model A310–304, –322, –324, and –325 airplanes; certificated in any category; except those airplanes on which Airbus Modification 13023 has been accomplished in production. Unsafe Condition (d) This AD results from a structural evaluation of Model A310 airplanes for widespread fatigue damage of the frame foot run-outs from frame (FR) 43 through FR 46. We are issuing this AD to prevent fatigue cracking of the frame foot run-outs, which could lead to rupture of the frame foot and cracking in adjacent frames and skin, and result in reduced structural integrity of the fuselage. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspection/Repair/Modification (f) At the later of the times specified in paragraphs (f)(1) and (f)(2) of this AD, perform a one-time rototest inspection for cracking of the frame foot and adjacent frames and skin in the area surrounding the frame foot run-outs from fuselage frame FR 43 through FR46 by doing all the applicable actions specified in the Accomplishment Instructions of the service bulletin. Except as required by paragraph (g) of this AD, repair any cracking before further flight in accordance with the Accomplishment Instructions of the service bulletin. Before further flight after performing the inspection, modify the fastener holes located between FR 43 and FR 46 on the center box and on the upper fuselage bent sections in accordance with the Accomplishment Instructions of the service bulletin. (1) Before the accumulation of the total flight-cycle or flight-hour threshold, whichever is first, specified in the Accomplishment Timescale table in paragraph 1.E.(2), ‘‘Compliance’’ of the service bulletin. (2) At the earlier of the times specified in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD. (i) Before the accumulation of the total flight-cycle or flight-hour threshold, whichever is first, specified in Notes 01, 02, and 03 in paragraph 1.E.(2), ‘‘Compliance’’ of the service bulletin, after the effective date of this AD. (ii) Within 3,000 flight cycles after the effective date of this AD. ´ ´ Repair Per FAA or Direction Generale de l’Aviation Civile (DGAC) (g) For any cracking found during any inspection required by this AD for which the E:\FR\FM\27OCP1.SGM 27OCP1 Federal Register / Vol. 70, No. 207 / Thursday, October 27, 2005 / Proposed Rules service bulletin specifies to contact the manufacturer for an appropriate repair: Before further flight, repair in accordance with a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the DGAC (or its delegated agent). Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, International Branch, ANM–116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (i) French airworthiness directive F–2005– 078, dated May 11, 2005, also addresses the subject of this AD. Issued in Renton, Washington, on October 20, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–21428 Filed 10–26–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22812; Directorate Identifier 2005–NM–134–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330–200, A330–300, A340–200, and A340–300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Airbus Model A330–200, A330– 300, A340–200, and A340–300 series airplanes. This proposed AD would require repetitive detailed inspections for cracking in the aft web of support rib 6 between certain bottom skin stringers on both wings; high frequency eddy current inspections for cracking of the attachment holes of the fuel pipes, and repair if necessary. This proposed AD would also provide for an optional modification, which would extend a certain inspection threshold. This proposed AD results from a report of significant cracking found in the aft web VerDate Aug<31>2005 14:39 Oct 26, 2005 Jkt 208001 of support rib 6 on both wings. We are proposing this AD to prevent cracking in the aft web of support rib 6, which could result in overloading of adjacent ribs and the surrounding wing structure and consequent reduced structural integrity of the wing. DATES: We must receive comments on this proposed AD by November 28, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, Room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for the service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2797; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Include the docket number ‘‘FAA–2005–22812; Directorate Identifier 2005–NM–134– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 61927 including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion ´ ´ The Direction Generale de l’Aviation Civile (DGAC), which is the airworthiness authority for France, notified us that an unsafe condition may exist on certain Airbus Model A330– 200, A330–300, A340–200, and A340– 300 series airplanes. The DGAC advises that a report was received indicating significant cracking in the aft web of support rib 6 on the left and right wings on a Model A330 series airplane. When the cracking was found, during an 8Ccheck, the airplane had accumulated 10,441 total flight cycles and 40,153 total flight hours. The cracking was located in the lower part of the rib 6 aft hole between bottom skin stringers 18 and 20. The cracking extended from the fuel pipe fastener holes to the lower edge of the rib 6 hole and into the refuel pipe hole where the cracking had gone through the full thickness of the rib. Subsequent inspections on several Model A330 and A340 series airplanes revealed similar cracking in the same area. These conditions, if not corrected, could result in overloading of adjacent ribs and the surrounding wing structure and consequent reduced structural integrity of the wing. Relevant Service Information Airbus has issued Service Bulletins A330–57–3085 (for Model A330 series airplanes) and A340–57–4093 (for Model A340 series airplanes), both Revision 01, both dated March 25, 2005. The service bulletins describe procedures for detailed inspections for cracking in the aft web of support rib 6 between bottom skin stringers 18 and 20 on both wings, and high frequency eddy current (HFEC) inspections for cracking E:\FR\FM\27OCP1.SGM 27OCP1

Agencies

[Federal Register Volume 70, Number 207 (Thursday, October 27, 2005)]
[Proposed Rules]
[Pages 61924-61927]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-21428]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22810; Directorate Identifier 2005-NM-143-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310-203, -204, and -222 
Airplanes, and Model A310-300 Series Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

[[Page 61925]]

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Airbus Model A310-203, -204, and -222 airplanes, and Model 
A310-300 series airplanes. This proposed AD would require a one-time 
rototest inspection for cracking of the frame foot and adjacent frames 
and skin in the area surrounding the frame foot run-outs from fuselage 
frames (FR) 43 through FR 46, and repair if necessary. The proposed AD 
also requires modification of certain fastener holes. This proposed AD 
results from a structural evaluation of Model A310 airplanes for 
widespread fatigue damage of the frame foot run-outs from FR 43 through 
FR 46. The evaluation revealed that, on in-service airplanes, 
undetected cracking in this area can lead to the rupture of the frame 
foot and subsequent cracking of the adjacent frames and fuselage skin. 
We are proposing this AD to prevent fatigue cracking of the frame foot 
run-outs, which could lead to rupture of the frame foot and cracking in 
adjacent frames and skin, and result in reduced structural integrity of 
the fuselage.

DATES: We must receive comments on this proposed AD by November 28, 
2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``FAA-2005-
22810; Directorate Identifier 2005-NM-143-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit https://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), 
which is the airworthiness authority for France, notified us that an 
unsafe condition may exist on certain Airbus Model A310-203, -204, and 
-222 airplanes, and Model A310-300 series airplanes. The DGAC advises 
that a structural evaluation for widespread fatigue damage of the frame 
foot run-outs from fuselage frame (FR) 43 through FR 46 was done on the 
subject airplanes. The evaluation revealed that, on in-service 
airplanes, undetected cracking in this area can lead to the rupture of 
the frame foot and subsequent cracking of the adjacent frames and 
fuselage skin. Such cracking would require an extensive repair and 
could have an impact on pressure loading strength capacity of the 
structure. These conditions, if not corrected, could result in reduced 
structural integrity of the fuselage.

Relevant Service Information

    Airbus has issued Service Bulletin A310-53-2124, dated April 4, 
2005. The service bulletin describes procedures for performing a one-
time rototest inspection to find cracking of the frame foot and 
adjacent frames and skin in the area surrounding the frame foot run-
outs from FR 43 through FR 46, and repair of cracking within certain 
limits. If the cracking is outside the limits specified in the service 
bulletin, the service bulletin procedures recommend contacting the 
manufacturer for repair instructions. The service bulletin also 
describes procedures for modification of certain fastener holes. The 
modification includes cold expanding the fastener holes most 
susceptible to fatigue, which are located between FR 43 and FR 46 on 
the center box and on the upper fuselage bent sections, and installing 
new fasteners. Accomplishing the actions specified in the service 
information is intended to adequately address the unsafe condition. The 
DGAC mandated the service information and issued French airworthiness 
directive F-2005-078, dated May 11, 2005, to ensure the continued 
airworthiness of these airplanes in France.
    Section 1.E., Compliance, of the service bulletin specifies 
compliance times for the actions in the service bulletin. The 
thresholds for the one-time inspection and modification range from 
between 22,200 flight cycles or 51,700 flight hours, whichever is 
first, to 26,800 flight cycles or 77,700 flight hours, whichever is 
first, depending on the configuration of the airplane. The service 
bulletin also includes a grace period of 3,000 flight cycles for 
airplanes that have exceeded certain flight-hour or flight-cycle 
thresholds, depending on the configuration of the airplane.

FAA's Determination and Requirements of the Proposed AD

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. We have examined the DGAC's findings, 
evaluated all pertinent information, and determined that we need to 
issue an AD for airplanes of this

[[Page 61926]]

type design that are certificated for operation in the United States.
    Therefore, we are proposing this AD, which would require 
accomplishing the actions specified in the service information 
described previously, except as discussed under ``Differences Among 
Proposed AD, French Airworthiness Directive, and Service Bulletin.''

Differences Among Proposed AD, French Airworthiness Directive, and 
Service Bulletin

    The applicability of the French Airworthiness Directive excludes 
airplanes on which Airbus Service Bulletin A310-53-2124 has been 
accomplished in service. However, we have not excluded those airplanes 
in the applicability of this proposed AD; rather, this proposed AD 
would include a requirement to accomplish the actions specified in that 
service bulletin. This proposed AD would ensure that the actions 
specified in the service bulletin and required by this proposed AD are 
accomplished on all affected airplanes. Operators must continue to 
operate the airplane in the configuration required by this proposed AD 
unless an alternative method of compliance is approved.
    The service bulletin specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing those conditions using a method that we or the 
DGAC (or its delegated agent) approve. In light of the type of repair 
that would be required to address the unsafe condition, and consistent 
with existing bilateral airworthiness agreements, we have determined 
that, for this proposed AD, a repair we or the DGAC approve would be 
acceptable for compliance with this proposed AD.

Costs of Compliance

    This proposed AD would affect about 59 airplanes of U.S. registry. 
The proposed actions would take about 31 work hours per airplane, at an 
average labor rate of $65 per work hour. Required parts would cost 
about $1,730 per kit (two kits per airplane). Based on these figures, 
the estimated cost of the proposed AD for U.S. operators is $323,025, 
or $5,475 per airplane.

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 have 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 that the 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. See the 
ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2005-22810; Directorate Identifier 2005-NM-
143-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by November 
28, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A310-203, -204, and -222 
airplanes, and Model A310-304, -322, -324, and -325 airplanes; 
certificated in any category; except those airplanes on which Airbus 
Modification 13023 has been accomplished in production.

Unsafe Condition

    (d) This AD results from a structural evaluation of Model A310 
airplanes for widespread fatigue damage of the frame foot run-outs 
from frame (FR) 43 through FR 46. We are issuing this AD to prevent 
fatigue cracking of the frame foot run-outs, which could lead to 
rupture of the frame foot and cracking in adjacent frames and skin, 
and result in reduced structural integrity of the fuselage.

Compliance

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

Inspection/Repair/Modification

    (f) At the later of the times specified in paragraphs (f)(1) and 
(f)(2) of this AD, perform a one-time rototest inspection for 
cracking of the frame foot and adjacent frames and skin in the area 
surrounding the frame foot run-outs from fuselage frame FR 43 
through FR46 by doing all the applicable actions specified in the 
Accomplishment Instructions of the service bulletin. Except as 
required by paragraph (g) of this AD, repair any cracking before 
further flight in accordance with the Accomplishment Instructions of 
the service bulletin. Before further flight after performing the 
inspection, modify the fastener holes located between FR 43 and FR 
46 on the center box and on the upper fuselage bent sections in 
accordance with the Accomplishment Instructions of the service 
bulletin.
    (1) Before the accumulation of the total flight-cycle or flight-
hour threshold, whichever is first, specified in the Accomplishment 
Timescale table in paragraph 1.E.(2), ``Compliance'' of the service 
bulletin.
    (2) At the earlier of the times specified in paragraphs 
(f)(2)(i) and (f)(2)(ii) of this AD.
    (i) Before the accumulation of the total flight-cycle or flight-
hour threshold, whichever is first, specified in Notes 01, 02, and 
03 in paragraph 1.E.(2), ``Compliance'' of the service bulletin, 
after the effective date of this AD.
    (ii) Within 3,000 flight cycles after the effective date of this 
AD.

Repair Per FAA or Direction G[eacute]n[eacute]rale de l'Aviation Civile 
(DGAC)

    (g) For any cracking found during any inspection required by 
this AD for which the

[[Page 61927]]

service bulletin specifies to contact the manufacturer for an 
appropriate repair: Before further flight, repair in accordance with 
a method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or the DGAC (or its delegated 
agent).

Alternative Methods of Compliance (AMOCs)

    (h)(1) The Manager, International Branch, ANM-116, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with 14 CFR 
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (i) French airworthiness directive F-2005-078, dated May 11, 
2005, also addresses the subject of this AD.


    Issued in Renton, Washington, on October 20, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-21428 Filed 10-26-05; 8:45 am]
BILLING CODE 4910-13-P

This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.