Airworthiness Directives; Aerospatiale Model ATR72 Airplanes, 42003-42005 [05-14393]
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[Federal Register Volume 70, Number 139 (Thursday, July 21, 2005)] [Proposed Rules] [Pages 42003-42005] From the Federal Register Online via the Government Printing Office [www.gpo.gov] [FR Doc No: 05-14393] ======================================================================== Proposed Rules Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. ======================================================================== Federal Register / Vol. 70, No. 139 / Thursday, July 21, 2005 / Proposed Rules [[Page 42003]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2005-21909; Directorate Identifier 2005-NM-059-AD] RIN 2120-AA64 Airworthiness Directives; Aerospatiale Model ATR72 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 Aerospatiale Model ATR72 airplanes. This proposed AD would require a one-time general visual inspection for contamination of the surface of the upper arms of the main landing gear (MLG) secondary side brace assemblies; and repetitive eddy current inspections for cracking of the upper arms, and related specified and corrective actions if necessary. This proposed AD also would mandate eventual replacement of aluminum upper arms with steel upper arms, which would end the repetitive inspections. This proposed AD is prompted by two reports of rupture of the upper arm of the MLG secondary side brace due to fatigue cracking. We are proposing this AD to prevent cracking of the upper arms of the secondary side brace assemblies of the MLG, which could result in collapse of the MLG during takeoff or landing, damage to the airplane, and possible injury to the flightcrew and passengers. DATES: We must receive comments on this proposed AD by August 22, 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. By 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 service information identified in this proposed AD, contact Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. You can examine the contents of this AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, on the plaza level of the Nassif Building, Washington, DC. This docket number is FAA-2005-21909; the directorate identifier for this docket is 2005-NM-059-AD. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-1137; 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 under ADDRESSES. Include ``Docket No. FAA-2005-21909; Directorate Identifier 2005-NM-059-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 submitted 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 our docket 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 can review the DOT's complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477-78), or you can visit https://dms.dot.gov. Examining the Docket You can 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 (DMS) 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 Aerospatiale Model ATR72 airplanes. The DGAC advises that there were two reports of rupture of the upper arm of the main landing gear (MLG) secondary side brace assembly. Fatigue cracking has been determined to be the cause of the ruptures. This cracking, if not corrected, could result in collapse of the MLG during takeoff or landing, damage to the airplane, and possible injury to the flightcrew and passengers. Relevant Service Information Messier-Dowty has issued Special Inspection Service Bulletin 631- 32-178, Revision 1, dated September 30, 2004. The service bulletin describes procedures for, among other things, a one-time general visual inspection for contamination of the surface of the upper arms of the MLG secondary side brace assemblies, and an eddy current inspection for cracking of the upper arms. The service bulletin also recommends sending an inspection report to Messier-Dowty. Aerospatiale has issued Avions de Transport Regional Service Bulletin ATR72-32-1046, Revision 1, dated October 7, 2004. The service bulletin [[Page 42004]] contains no Accomplishment Instructions, but describes procedures for replacing the upper arms of the MLG secondary side brace assemblies. The service bulletin refers to Messier-Dowty Service Bulletin 631-32- 183, dated October 6, 2004, as the source of service information for accomplishing the replacement. Service Bulletin 631-32-183 describes procedures for replacing aluminum upper arms of the MLG secondary side brace assemblies with steel upper arms, and engraving a new suffix on the identification plate on the assembly. 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- 2004-164, dated October 13, 2004, to ensure the continued airworthiness of these airplanes in France. The French airworthiness directive refers to Messier-Bugatti Service Bulletin 631-32-085, dated August 21, 1992, as the source of service information for replacing the press-fitted ball cages of the lower and upper arms of the MLG secondary side brace assemblies with ball cages that are shrink-fitted and bonded with adhesive. For airplanes on which this replacement has been accomplished, the compliance time for the replacement of the aluminum upper arms is extended. FAA's Determination and Requirements of the Proposed AD This airplane model is manufactured in France and is 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 accomplishing the actions specified in Avions de Transport Regional Service Bulletin ATR72-32-1046, Revision 1; Messier-Dowty Special Inspection Service Bulletin 631-32-178, Revision 1; and Messier-Dowty Service Bulletin 631-32-183; described previously; except as discussed under ``Differences Between the Proposed AD and Messier-Dowty Special Inspection Service Bulletin 631-32-178.'' In addition, this proposed AD would require, for replacement of aluminum upper arms, an eddy current inspection and investigative or corrective actions. Replacement with steel arms would end the repetitive inspections, and replacement with aluminum arms would require repeating the eddy current inspections. Differences Among Proposed AD, French Airworthiness Directive, and Messier-Dowty Service Information Although the French airworthiness directive requires replacing any defective upper arm of the MLG secondary side brace assemblies with a new or serviceable aluminum arm, or a new steel arm, there are no procedures specified in Service Bulletin 631-32-183 for replacing the defective arm with an aluminum arm. The service bulletin does reference the ATR Component Maintenance Manual (CMM), Chapter 32-18-41, Revision 3, dated September 30, 2002, for procedures for replacing the affected arm with a new steel arm. Therefore, this proposed AD will reference the CMM for procedures for replacement of any defective aluminum upper arm with a new or serviceable aluminum upper arm. Chapter 32-18-41 provides procedures for replacement of affected upper arms with either steel or aluminum upper arms. This difference has been coordinated with the DGAC. Special Inspection Service Bulletin 631-32-178, Revision 1, recommends sending an inspection report to Messier-Dowty, but this proposed AD does not contain that requirement. Special Inspection Service Bulletin 631-32-178, Revision 1, refers only to a ``visual inspection'' for contamination of the surface. We have determined that the procedures in the service bulletin should be described as a ``general visual inspection.'' A note has been included in this AD to define this type of inspection. Costs of Compliance This proposed AD would affect about 18 airplanes of U.S. registry. The proposed initial and repetitive inspections 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 inspections for U.S. operators is $1,170, or $65 per airplane, per inspection cycle. The proposed replacement would take about 4 work hours per airplane (2 work hours per upper arm), at an average labor rate of $65 per work hour. Required parts would cost about $4,948 per airplane ($2,474 per upper arm). Based on these figures, the estimated cost of the proposed replacement for U.S. operators is $93,744, or $5,208 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. 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: [[Page 42005]] 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 adding the following new airworthiness directive (AD): Aerospatiale: Docket No. FAA-2005-21909; Directorate Identifier 2005-NM-059-AD. Comments Due Date (a) The Federal Aviation Administration must receive comments on this AD action by August 22, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Aerospatiale Model ATR72-101, -102, -201, -202, -211, -212, and -212A airplanes, certificated in any category; except airplanes that have received ATR Modification 5522 in production. Unsafe Condition (d) This AD was prompted by two reports of rupture of the upper arm of the main landing gear (MLG) secondary side brace assembly due to fatigue cracking. We are issuing this AD to prevent cracking of the upper arms of the secondary side brace assemblies of the MLG, which could result in collapse of the MLG during takeoff or landing, damage to the airplane, and possible injury to the flightcrew and passengers. 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. Inspections (f) At the latest of the times specified in paragraphs (f)(1), (f)(2), and (f)(3) of this AD: Accomplish a general visual inspection for contamination of the surface of the upper arms of the MLG secondary side brace assemblies, and an eddy current inspection for cracking of the upper arms by doing all the actions specified in Parts A and B of the Accomplishment Instructions of Messier-Dowty Special Inspection Service Bulletin 631-32-178, Revision 1, dated September 30, 2004. Repeat the eddy current inspection at intervals not to exceed 800 flight cycles until accomplishment of paragraph (h) of this AD. (1) Before the accumulation of 4,000 total flight cycles on the secondary side brace. (2) Before the accumulation of 800 flight cycles on the secondary side brace since overhauled. (3) Within 200 flight cycles after the effective date of this AD. Note 1: For the purposes of this AD, a general visual inspection is: ``A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.'' Related Specified and Corrective Actions (g) If any cracking is found during any inspection required by paragraph (f) of this AD: Before further flight, replace the affected upper arm of the MLG secondary side brace assembly as specified in paragraph (g)(1) or (g)(2) of this AD. (1) Replace the aluminum upper arm of the MLG secondary side brace assembly with a steel upper arm by doing the applicable actions specified in the Accomplishment Instructions of Messier- Dowty Service Bulletin 631-32-183, dated October 6, 2004. This replacement ends the repetitive inspections required by paragraph (f) of this AD for that side brace only. (2) Replace the aluminum upper arm of the MLG secondary side brace assembly with a new or serviceable aluminum upper arm in accordance with a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction G[eacute]n[eacute]rale de l'Aviation Civile (or its delegated agent). ATR Component Maintenance Manual, Chapter 32-18- 41, Revision 3, dated September 30, 2002, is one approved method. Accomplish a general visual inspection for contamination of the surface of the upper arm before the accumulation of 4,000 total flight cycles on the upper arm, and if cracks are found, before further flight, replace the upper arm with a steel upper arm as required by paragraph (g)(1) of this AD. If no cracks are found, repeat the eddy current inspection thereafter at intervals not to exceed 800 flight cycles until accomplishment of paragraph (h) of this AD. Terminating Action (h) Replace all aluminum upper arms of the MLG secondary side brace assembly with steel upper arms by doing all the applicable actions in accordance with the Accomplishment Instructions of Messier-Dowty Service Bulletin 631-32-183, dated October 6, 2004; at the applicable time specified in paragraph (h)(1), (h)(2), (h)(3), or (h)(4) of this AD. Accomplishing this replacement ends the repetitive inspections required by paragraph (f) of this AD. (1) For airplanes on which any upper arm has been overhauled before the effective date of this AD and on which Messier-Bugatti Service Bulletin 631-32-085, dated August 21, 1992, has not been accomplished, as of the effective date of this AD: Within 15,000 flight cycles or 96 months, whichever is first, since overhaul on the affected upper arm. (2) For airplanes on which any upper arm has been overhauled before the effective date of this AD and on which Messier-Bugatti Service Bulletin 631-32-085, dated August 21, 1992, has been accomplished, as of the effective date of this AD: Within 18,000 flight cycles or 96 months, whichever is first, since overhaul on the affected upper arm. (3) For airplanes on which any upper arm has not been overhauled and on which Messier-Bugatti Service Bulletin 631-32-085, dated August 21, 1992, has not been accomplished, as of the effective date of this AD: Before the accumulation of 15,000 total flight cycles on an upper arm since new, or within 96 months on an upper arm since new, whichever is first. (4) For airplanes on which any upper arm has not been overhauled and on which Messier-Bugatti Service Bulletin 631-32-085, dated August 21, 1992, has been accomplished, as of the effective date of this AD: Before the accumulation of 18,000 total flight cycles on an upper arm since new, or within 96 months on an upper arm since new, whichever is first. No Report Required (i) Messier-Dowty Special Inspection Service Bulletin 631-32- 178, Revision 1, dated September 30, 2004, recommends sending an inspection report to Messier-Dowty, but this AD does not contain that requirement. Parts Installation (j) As of the effective date of this AD, no person may install, on any airplane, an aluminum upper arm of the MLG secondary side brace assembly, unless the applicable requirements specified in paragraphs (f) and (g) of this AD have been accomplished. Alternative Methods of Compliance (AMOCs) (k) The Manager, 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. Related Information (l) French airworthiness directive F-2004-164, dated October 13, 2004, also addresses the subject of this AD. Issued in Renton, Washington, on July 14, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-14393 Filed 7-20-05; 8:45 am] BILLING CODE 4910-13-P
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