Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes, 15065-15068 [E6-4409]

Download as PDF Federal Register / Vol. 71, No. 58 / Monday, March 27, 2006 / Proposed Rules Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and are assigned OMB Control Number 2120–0056. Initial Inspections (h) Within 12 months after the effective date of this AD, perform each of the Corrosion Tasks, including re-protection actions, as applicable, specified in Part 3 of the Manual by accomplishing the basic tasks defined in Parts 2 and 3 of the Manual, in accordance with the procedures of the Manual. Repetitive Inspections (i) Except as provided by paragraph (j) of this AD, repeat each of the Corrosion Tasks, and re-protection actions, as applicable, specified in Part 3 of the Manual at intervals not to exceed 3 or 6 years, as specified in Part 3 of the Manual. (j) After accomplishment of each initial Corrosion Task required by paragraph (h) of this AD, the FAA may approve the incorporation into the operator’s approved maintenance/inspection program of the Corrosion Prevention and Control Program (CPCP) specified in the Manual and this AD; or an equivalent program that is approved by the FAA. In all cases, the initial Corrosion Task for each airplane area must be completed at the compliance time specified in paragraph (h) of this AD. (1) Any operator complying with paragraph (j) of this AD may use an alternative recordkeeping method to that otherwise required by Section 91.417 (‘‘Maintenance records’’) or Section 121.380 (‘‘Maintenance recording requirements’’) of the Federal Aviation Regulations (14 CFR 91.417 or 14 CFR 121.380, respectively) for the actions required by this AD, provided that the recordkeeping method is approved by the FAA and is included in a revision to the FAA-approved maintenance/inspection program. For the purposes of this paragraph, the FAA is defined as the cognizant Flight Standards District Office. (2) After the initial accomplishment of the Corrosion Tasks required by paragraph (h) of this AD, any extension of the repetitive intervals specified in the Manual must be approved by the FAA. For the purposes of this paragraph, the FAA is defined as the Manager, New York Aircraft Certification Office (ACO), FAA. sroberts on PROD1PC70 with PROPOSALS Corrective Actions (k) If any corrosion is found during accomplishment of any action required by paragraph (h) or (i) of this AD: Within 30 days after the finding; rework, repair, or replace, as applicable, any subject part, in accordance with Section 4.0 of Part 3 of the Manual. Reporting Requirements and Repetitive Actions for Remainder of Affected Fleet (l) If any Level 3 corrosion, as defined in the Introduction of the Manual, is found during accomplishment of any action required by this AD: Do paragraphs (l)(1), (l)(2), and (l)(3) of this AD. (1) Within 10 days after the finding of Level 3 corrosion, submit a report of the findings to the Manager, New York Aircraft Certification Office (ACO), FAA, 1600 VerDate Aug<31>2005 18:28 Mar 24, 2006 Jkt 208001 Stewart Avenue, suite 410, Westbury, New York 11590; fax (516) 794–5531. The report must follow the format specified in Section 5.0 of Part 3 of the Manual, or be submitted using a Service Difficulty Report, as applicable. (2) Within 10 days after the finding of Level 3 corrosion, submit a plan to the FAA to identify a schedule for accomplishing the applicable Corrosion Task on the remainder of the airplanes in the operator’s fleet that are subject to this AD, or data substantiating that the Level 3 corrosion that was found is an isolated case. The FAA may impose a schedule other than proposed in the plan upon finding that a change to the schedule is needed to ensure that any other Level 3 corrosion is detected in a timely manner. For the purposes of this paragraph, the FAA is defined as the cognizant Principal Maintenance Inspector (PMI) for operators that are assigned a PMI (e.g., part 121, 125, and 135 operators), and the cognizant Flight Standards District Office for other operators (e.g., part 91 operators). (3) Within the time schedule approved in accordance with paragraph (l)(2) of this AD, accomplish the applicable Corrosion Task on the remainder of the airplanes in the operator’s fleet that are subject to this AD. (m) If any Level 2 or 3 corrosion, as defined in the Introduction of the Manual, is found during accomplishment of any action required by this AD: At the applicable time specified in Section 5.0 of Part 3 of the Manual, report these findings to the manufacturer according to Section 5.0 of Part 3 of the Manual. Limiting Future Corrosion Findings (n) If corrosion findings that exceed Level 1 are found in any area during any repeat of any Corrosion Task after the initial accomplishment required by paragraph (h) of this AD: Within 60 days after such finding, implement a means approved by the FAA to reduce future findings of corrosion in that area to Level 1 or better. For the purposes of this paragraph, the FAA is defined as the cognizant Principal Maintenance Inspector (PMI) for operators that are assigned a PMI (e.g., part 121, 125, and 135 operators), and the cognizant Flight Standards District Office for other operators (e.g., part 91 operators). Scheduling Corrosion Tasks for Transferred Airplanes (o) Before any airplane subject to this AD is transferred and placed into service by an operator: Establish a schedule for accomplishing the Corrosion Tasks required by this AD in accordance with paragraph (o)(1) or (o)(2) of this AD, as applicable. (1) For airplanes on which the Corrosion Tasks required by this AD have been accomplished previously at the schedule established by this AD: Perform the first Corrosion Task in each area in accordance with the previous operator’s schedule, or in accordance with the new operator’s schedule, whichever results in an earlier accomplishment of that Corrosion Task. After the initial accomplishment of each Corrosion Task in each area as required by this paragraph, repeat each Corrosion Task in accordance with the new operator’s schedule. PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 15065 (2) For airplanes on which the Corrosion Tasks required by this AD have not been accomplished previously, or have not been accomplished at the schedule established by this AD: The new operator must perform the initial accomplishment of each Corrosion Task in each area before further flight or in accordance with a schedule approved by the FAA. For the purposes of this paragraph, the FAA is defined as the cognizant Principal Maintenance Inspector (PMI) for operators that are assigned a PMI (e.g., part 121, 125, and 135 operators), and the cognizant Flight Standards District Office for other operators (e.g., part 91 operators). Alternative Methods of Compliance (AMOCs) (p)(1) The Manager, New York ACO, has the authority to approve AMOCs for this AD, if requested using 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 (q) Canadian airworthiness directive CF– 98–03, dated February 27, 1998, also addresses the subject of this AD. Issued in Renton, Washington, on March 10, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–4400 Filed 3–24–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24199; Directorate Identifier 2006–NM–025–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A318, A319, A320, and A321 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 A318, A319, A320, and A321 airplanes. This proposed AD would require revising the Limitations section of the airplane flight manual (AFM); performing a one-time hardness test of certain ribs of the leftand right-hand engine pylons, as applicable, which would terminate the AFM limitations; and performing related corrective actions if necessary. E:\FR\FM\27MRP1.SGM 27MRP1 15066 Federal Register / Vol. 71, No. 58 / Monday, March 27, 2006 / Proposed Rules sroberts on PROD1PC70 with PROPOSALS This proposed AD results from a report that certain stainless steel ribs installed in the engine pylon may not have been heat-treated during manufacture, which could result in significantly reduced structural integrity of the pylon. We are proposing this AD to detect and correct reduced structural integrity of the engine pylon, which could lead to separation of the engine from the airplane. DATES: We must receive comments on this proposed AD by April 26, 2006. 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 AD. FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2141; 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–2006–24199; Directorate Identifier 2006–NM–025–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 VerDate Aug<31>2005 18:28 Mar 24, 2006 Jkt 208001 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 A318, A319, A320, and A321 airplanes. The DGAC advises that certain stainless steel ribs of the engine pylon may not have been heat-treated during manufacture, which could result in significantly reduced structural integrity of those ribs. This condition, if not corrected, could result in reduced structural integrity of the engine pylon, which could lead to separation of the engine from the airplane. Relevant Service Information Airbus has issued All Operators Telex (AOT) A320–54A1015, dated December 14, 2005. The AOT describes procedures for performing a one-time inspection (hardness test) to determine the hardness of stainless steel ribs 7, 8, and 9 of the left- and right-hand engine pylons; and performing corrective actions if necessary. The corrective actions include installing reinforcing components on ribs 8 and 9, as applicable. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The AOT refers to Airbus Repair Instruction 546 12081, Issue B, dated January 3, 2006, as an additional source of service information for accomplishing the instructions of the AOT. PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 The DGAC mandated the service information and issued French airworthiness directive F–2006–011 R1, dated January 18, 2006, to ensure the continued airworthiness of these airplanes in France. French airworthiness directive F– 2006–011 R1 also specifies strict adherence to reduced speed limitations for flight in severe turbulence, as described in Airbus A318/319/320/321 Airplane Flight Manual (AFM) 4.03.00 P 03. FAA’s Determination and Requirements of This 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 products of this type design that are certificated for operation in the United States. Therefore, we are proposing this AD, which would require revising the Limitations section of the AFM to require strict adherence to reduced speed limitations for flight in severe turbulence and accomplishing the actions specified in the AOT described previously, except as discussed under ‘‘Differences Between French Airworthiness Directive, Service Information, and This AD.’’ The proposed AD would also require sending the inspection results to Airbus. Differences Between French Airworthiness Directive, Service Information, and This AD French airworthiness directive F– 2006–011 R1 requires, as of the effective date of that AD, that flightcrews strictly adhere to the requirement for operating at reduced speed in case of flight in severe turbulence, as specified in AFM 4.03.00 P03. This AD requires revising the Limitations section of the AFM to include this provision. To prevent immediate grounding of any airplane, this proposed AD would require revising the limitations of the AFM within 10 days after the effective date of this proposed AD to include this requirement of strict adherence to reduced speeds. AOT A320–54A1015 specifies hardness testing of ribs 7, 8, and 9. However, the AOT states that rib 7 is able to sustain certification loads even E:\FR\FM\27MRP1.SGM 27MRP1 Federal Register / Vol. 71, No. 58 / Monday, March 27, 2006 / Proposed Rules if not heat-treated and no corrective action is available for rib 7. Since rib 7 does not contribute to the unsafe condition, this proposed AD would not require testing of rib 7. Although the AOT and French airworthiness directive refer to an ‘‘inspection’’ of the spar box ribs, for clarity’s sake, this proposed AD would refer to a ‘‘hardness test’’ as described in related Airbus Repair Instruction 546 12081, Issue B. Operators should note that, although the AOT and French airworthiness directive describe procedures for submitting certain findings to the manufacturer, this proposed AD would not require those actions. 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. Costs of Compliance This proposed AD would affect about 112 airplanes of U.S. registry. The proposed hardness test would take about 1 work hour per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the proposed AD for U.S. operators is $7,280, or $65 per airplane. The Proposed Amendment sroberts on PROD1PC70 with PROPOSALS 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; VerDate Aug<31>2005 18:28 Mar 24, 2006 Jkt 208001 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. 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–2006–24199; Directorate Identifier 2006–NM–025–AD. Comments Due Date (a) The FAA must receive comments on this AD action by April 26, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A318, A319, A320, and A321 airplanes, certificated in any category; having a manufacturer serial number as identified in Airbus All Operators Telex (AOT) A320–54A1015, dated December 14, 2005 (referred to after this paragraph as ‘‘the AOT’’). Unsafe Condition (d) This AD results from a report that certain stainless steel ribs installed in the engine pylon may not have been heat-treated during manufacture, which could result in significantly reduced structural integrity of the pylon. We are issuing this AD to detect and correct reduced structural integrity of the engine pylon, which could lead to separation of the engine from 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. PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 15067 Revise Limitations (f) Within 10 days after the effective date of this AD, revise the Limitations section of Airbus A318/319/320/321 Airplane Flight Manual (AFM) to include the following statement. This may be done by inserting a copy of this AD into the AFM. • ‘‘In case of flight in severe turbulence, strictly adhere to reduced speeds as defined in Aircraft Flight Manual 4.03.00 P 03.’’ Note 1: When a statement identical to that specified in paragraph (f) of this AD has been included in the general revisions of the AFM, and the general revisions have been inserted into the AFM, the copy of this AD may be removed from the Limitations section of the AFM unless it has already been removed as specified in paragraph (g) or (h) of this AD. Hardness Test (g) Within the compliance time specified in paragraph (g)(1) or (g)(2) of this AD, as applicable, or before further flight after a hard or overweight landing, whichever occurs first: Perform a one-time hardness test to determine the hardness of ribs 8 and 9 of the left- and right-hand engine pylons, in accordance with the instructions of the AOT. If no discrepant rib is found installed on the airplane, the statement specified in paragraph (f) of this AD may be removed from the Limitations section of the AFM. (1) For airplanes equipped with CFM engines: Within 6 months after the effective date of this AD. (2) For airplanes equipped with IAE engines: Within 9 months after the effective date of this AD. Note 2: Airbus AOT A320–54A1015, dated December 14, 2005, refers to Airbus Repair Instruction 546 12081, Issue B, dated January 3, 2006, as an additional source of service information for accomplishing the actions specified by the AOT. Corrective Actions (h) Within the compliance time specified in paragraph (h)(1) or (h)(2) of this AD, as applicable: Perform applicable corrective actions in accordance with the instructions of the AOT. When corrective actions have been applied to any discrepant rib found on the airplane, the statement specified in paragraph (f) of this AD may be removed from the Limitations section of the AFM. (1) For airplanes equipped with CFM engines: Within 14 days after accomplishing the hardness test required by paragraph (g) of this AD. (2) For airplanes equipped with IAE engines: Within 28 days after accomplishing the hardness test required by paragraph (g) of this AD. No Reporting Requirement (i) Although the service bulletin referenced in this AD specifies to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs E:\FR\FM\27MRP1.SGM 27MRP1 15068 Federal Register / Vol. 71, No. 58 / Monday, March 27, 2006 / Proposed Rules 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 (k) French airworthiness directive F–2006– 011 R1, dated January 18, 2006, also addresses the subject of this AD. Issued in Renton, Washington, on March 13, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–4409 Filed 3–24–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2004–19002; Directorate Identifier 2003–NM–27–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series Airplanes; A300 B4–600, B4–600R, and F4–600R Series Airplanes; and Model C4–605R Variant F Airplanes (Collectively Called A300–600 Series Airplanes) Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. sroberts on PROD1PC70 with PROPOSALS AGENCY: SUMMARY: The FAA is revising an earlier NPRM for an airworthiness directive (AD) that applies to certain Airbus Model A300 B2 and A300 B4 series airplanes, and A300–600 series airplanes. The original NPRM would have superseded an existing AD that currently requires repetitive inspections to detect cracks in Gear Rib 5 of the main landing gear (MLG) attachment fittings at the lower flange, and repair, if necessary. That AD also requires modification of Gear Rib 5 of the MLG attachment fittings, which constitutes terminating action for the repetitive inspections. The original NPRM proposed to reduce the compliance times for all inspections, and require doing the inspections in accordance with new revisions of the service bulletins. The original NPRM resulted from new service information that was issued by the manufacturer and mandated by the French airworthiness authority. This new action revises the VerDate Aug<31>2005 18:28 Mar 24, 2006 Jkt 208001 original NPRM by proposing new repetitive inspections of certain areas of the attachment fittings that were repaired in accordance with the actions specified in both the existing AD and the original NPRM. We are proposing this supplemental NPRM to prevent fatigue cracking of the MLG attachment fittings, which could result in reduced structural integrity of the airplane. DATES: We must receive comments on this supplemental NPRM by April 21, 2006. 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. For Model A300 B2 and A300 B4 series airplanes, contact Jacques Leborgne, Airbus Customer Service Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, fax (+33) 5 61 93 36 14, for service information identified in this proposed AD. For Model A300 600 series airplanes, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for 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 proposal. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘Docket No. FAA–2004–19002; Directorate Identifier 2003–NM–27–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this supplemental NPRM. We will PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 consider all comments received by the closing date and may amend this supplemental NPRM in light of those comments. We will post all comments submitted, 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 ADDRESSES. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion We proposed to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) with a notice of proposed rulemaking (the original NPRM) for an AD for certain Airbus Model A300 B2 and A300 B4 series airplanes; and Model A300–600 series airplanes. The original NPRM proposed to supersede AD 2000–05–07, amendment 39–11616 (65 FR 12077, March 8, 2000), which applies to certain Airbus Model A300 and A300–600 series airplanes. The original NPRM was published in the Federal Register on September 7, 2004 (69 FR 54063). The original NPRM proposed to reduce the compliance times for all inspections required by AD 2000–05–07, and to require inspections in accordance with new revisions of the service bulletins. The original NPRM resulted from new service information that was issued by the manufacturer and mandated by the French airworthiness authority. We proposed the original NPRM to prevent fatigue cracking of the main landing gear (MLG) attachment fittings, which could result in reduced structural integrity of the airplane. E:\FR\FM\27MRP1.SGM 27MRP1

Agencies

[Federal Register Volume 71, Number 58 (Monday, March 27, 2006)]
[Proposed Rules]
[Pages 15065-15068]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-4409]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24199; Directorate Identifier 2006-NM-025-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A318, A319, A320, and A321 
Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Airbus Model A318, A319, A320, and A321 airplanes. This 
proposed AD would require revising the Limitations section of the 
airplane flight manual (AFM); performing a one-time hardness test of 
certain ribs of the left- and right-hand engine pylons, as applicable, 
which would terminate the AFM limitations; and performing related 
corrective actions if necessary.

[[Page 15066]]

This proposed AD results from a report that certain stainless steel 
ribs installed in the engine pylon may not have been heat-treated 
during manufacture, which could result in significantly reduced 
structural integrity of the pylon. We are proposing this AD to detect 
and correct reduced structural integrity of the engine pylon, which 
could lead to separation of the engine from the airplane.

DATES: We must receive comments on this proposed AD by April 26, 2006.

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 AD.

FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2141; 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-2006-
24199; Directorate Identifier 2006-NM-025-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 A318, A319, A320, 
and A321 airplanes. The DGAC advises that certain stainless steel ribs 
of the engine pylon may not have been heat-treated during manufacture, 
which could result in significantly reduced structural integrity of 
those ribs. This condition, if not corrected, could result in reduced 
structural integrity of the engine pylon, which could lead to 
separation of the engine from the airplane.

Relevant Service Information

    Airbus has issued All Operators Telex (AOT) A320-54A1015, dated 
December 14, 2005. The AOT describes procedures for performing a one-
time inspection (hardness test) to determine the hardness of stainless 
steel ribs 7, 8, and 9 of the left- and right-hand engine pylons; and 
performing corrective actions if necessary. The corrective actions 
include installing reinforcing components on ribs 8 and 9, as 
applicable. Accomplishing the actions specified in the service 
information is intended to adequately address the unsafe condition.
    The AOT refers to Airbus Repair Instruction 546 12081, Issue B, 
dated January 3, 2006, as an additional source of service information 
for accomplishing the instructions of the AOT.
    The DGAC mandated the service information and issued French 
airworthiness directive F-2006-011 R1, dated January 18, 2006, to 
ensure the continued airworthiness of these airplanes in France.
    French airworthiness directive F-2006-011 R1 also specifies strict 
adherence to reduced speed limitations for flight in severe turbulence, 
as described in Airbus A318/319/320/321 Airplane Flight Manual (AFM) 
4.03.00 P 03.

FAA's Determination and Requirements of This 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 products of this type design that are certificated for 
operation in the United States.
    Therefore, we are proposing this AD, which would require revising 
the Limitations section of the AFM to require strict adherence to 
reduced speed limitations for flight in severe turbulence and 
accomplishing the actions specified in the AOT described previously, 
except as discussed under ``Differences Between French Airworthiness 
Directive, Service Information, and This AD.'' The proposed AD would 
also require sending the inspection results to Airbus.

Differences Between French Airworthiness Directive, Service 
Information, and This AD

    French airworthiness directive F-2006-011 R1 requires, as of the 
effective date of that AD, that flightcrews strictly adhere to the 
requirement for operating at reduced speed in case of flight in severe 
turbulence, as specified in AFM 4.03.00 P03. This AD requires revising 
the Limitations section of the AFM to include this provision. To 
prevent immediate grounding of any airplane, this proposed AD would 
require revising the limitations of the AFM within 10 days after the 
effective date of this proposed AD to include this requirement of 
strict adherence to reduced speeds.
    AOT A320-54A1015 specifies hardness testing of ribs 7, 8, and 9. 
However, the AOT states that rib 7 is able to sustain certification 
loads even

[[Page 15067]]

if not heat-treated and no corrective action is available for rib 7. 
Since rib 7 does not contribute to the unsafe condition, this proposed 
AD would not require testing of rib 7.
    Although the AOT and French airworthiness directive refer to an 
``inspection'' of the spar box ribs, for clarity's sake, this proposed 
AD would refer to a ``hardness test'' as described in related Airbus 
Repair Instruction 546 12081, Issue B.
    Operators should note that, although the AOT and French 
airworthiness directive describe procedures for submitting certain 
findings to the manufacturer, this proposed AD would not require those 
actions.

Costs of Compliance

    This proposed AD would affect about 112 airplanes of U.S. registry. 
The proposed hardness test would take about 1 work hour per airplane, 
at an average labor rate of $65 per work hour. Based on these figures, 
the estimated cost of the proposed AD for U.S. operators is $7,280, or 
$65 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-2006-24199; Directorate Identifier 2006-NM-
025-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by April 26, 
2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A318, A319, A320, and A321 
airplanes, certificated in any category; having a manufacturer 
serial number as identified in Airbus All Operators Telex (AOT) 
A320-54A1015, dated December 14, 2005 (referred to after this 
paragraph as ``the AOT'').

Unsafe Condition

    (d) This AD results from a report that certain stainless steel 
ribs installed in the engine pylon may not have been heat-treated 
during manufacture, which could result in significantly reduced 
structural integrity of the pylon. We are issuing this AD to detect 
and correct reduced structural integrity of the engine pylon, which 
could lead to separation of the engine from 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.

Revise Limitations

    (f) Within 10 days after the effective date of this AD, revise 
the Limitations section of Airbus A318/319/320/321 Airplane Flight 
Manual (AFM) to include the following statement. This may be done by 
inserting a copy of this AD into the AFM.
     ``In case of flight in severe turbulence, strictly 
adhere to reduced speeds as defined in Aircraft Flight Manual 
4.03.00 P 03.''

    Note 1:  When a statement identical to that specified in 
paragraph (f) of this AD has been included in the general revisions 
of the AFM, and the general revisions have been inserted into the 
AFM, the copy of this AD may be removed from the Limitations section 
of the AFM unless it has already been removed as specified in 
paragraph (g) or (h) of this AD.

Hardness Test

    (g) Within the compliance time specified in paragraph (g)(1) or 
(g)(2) of this AD, as applicable, or before further flight after a 
hard or overweight landing, whichever occurs first: Perform a one-
time hardness test to determine the hardness of ribs 8 and 9 of the 
left- and right-hand engine pylons, in accordance with the 
instructions of the AOT. If no discrepant rib is found installed on 
the airplane, the statement specified in paragraph (f) of this AD 
may be removed from the Limitations section of the AFM.
    (1) For airplanes equipped with CFM engines: Within 6 months 
after the effective date of this AD.
    (2) For airplanes equipped with IAE engines: Within 9 months 
after the effective date of this AD.

    Note 2:  Airbus AOT A320-54A1015, dated December 14, 2005, 
refers to Airbus Repair Instruction 546 12081, Issue B, dated 
January 3, 2006, as an additional source of service information for 
accomplishing the actions specified by the AOT.

Corrective Actions

    (h) Within the compliance time specified in paragraph (h)(1) or 
(h)(2) of this AD, as applicable: Perform applicable corrective 
actions in accordance with the instructions of the AOT. When 
corrective actions have been applied to any discrepant rib found on 
the airplane, the statement specified in paragraph (f) of this AD 
may be removed from the Limitations section of the AFM.
    (1) For airplanes equipped with CFM engines: Within 14 days 
after accomplishing the hardness test required by paragraph (g) of 
this AD.
    (2) For airplanes equipped with IAE engines: Within 28 days 
after accomplishing the hardness test required by paragraph (g) of 
this AD.

No Reporting Requirement

    (i) Although the service bulletin referenced in this AD 
specifies to submit certain information to the manufacturer, this AD 
does not include that requirement.

Alternative Methods of Compliance (AMOCs)

    (j)(1) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, has the authority to approve AMOCs

[[Page 15068]]

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 Sec.  
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

    (k) French airworthiness directive F-2006-011 R1, dated January 
18, 2006, also addresses the subject of this AD.

    Issued in Renton, Washington, on March 13, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-4409 Filed 3-24-06; 8:45 am]
BILLING CODE 4910-13-P
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