Airworthiness Directives; Airbus Model A310-200 and -300 Series Airplanes, 70048-70052 [05-22971]
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[Federal Register Volume 70, Number 223 (Monday, November 21, 2005)] [Proposed Rules] [Pages 70048-70052] From the Federal Register Online via the Government Printing Office [www.gpo.gov] [FR Doc No: 05-22971] ======================================================================== 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. 223 / Monday, November 21, 2005 / Proposed Rules [[Page 70048]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2005-23007; Directorate Identifier 2005-NM-013-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Model A310-200 and -300 Series 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 A310-200 and -300 series airplanes. This proposed AD would require repetitive inspections for cracks and corrosion of the areas behind the scuff plates below the passenger/crew doors and bulk cargo door, and repair of any cracked or corroded part. This proposed AD also would require repetitive inspections for cracks of the holes of the corner doublers, the fail-safe ring, and the door frames of the passenger/crew door structures. This proposed AD is prompted by reports of corrosion behind the scuff plates at passenger/ crew doors and the bulk cargo door and fatigue cracks on the corner doublers of the forward and aft passenger/crew door frames. We are proposing this AD to prevent such corrosion and fatigue cracking, which could result in reduced structural integrity of the door surroundings. DATES: We must receive comments on this proposed AD by December 21, 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 Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 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-2005-23007; the directorate identifier for this docket is 2005-NM-013-AD. FOR FURTHER INFORMATION CONTACT: Rosanne Ryburn, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2139; 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-2005-23007; Directorate Identifier 2005-NM-013-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 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 Airbus Model A310-200 and -300 series airplanes. The DGAC advises that it received reports indicating that corrosion was found behind the scuff plates at passenger/crew doors and the bulk cargo door. The DGAC also advises that results of structural fatigue testing have revealed that cracks were found on the corner doublers of the forward and aft passenger/crew door frames; and, after various simulated flights, on the fail-safe ring and frames 14 and 16A of the forward passenger/crew door. After 50,000 simulated flights, cracks measuring between 8.0 millimeters (mm) and 109.0 mm were found on the forward door frames and fail-safe ring. After 60,493 simulated flights, a 53.0 mm crack was found on the mid door frame. After 106,000 simulated flights, a 32.0 mm crack was found on the aft door frame. In all cases, the cracks originated at the fastener holes. In addition, cracks originating from corner doubler edges were found at the aft passenger/crew doors. Such corrosion and fatigue cracking, if not detected and corrected, could result in reduced structural integrity of the door surroundings. [[Page 70049]] Other Relevant Rulemaking We have previously issued AD 97-11-03, amendment 39-10032 (62 FR 28325, May 23, 1997), applicable to all Airbus Model A300 series airplanes. That AD requires inspections of the lower door surrounding structure to detect cracks and corrosion; inspections to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the door structures; and repair if necessary. That AD also requires modification of the passenger/crew door frames, which terminates certain inspections. We also previously issued AD 98-16-05, amendment 39-10680 (63 FR 40812, July 31, 1998), applicable to all Airbus Model A300-600 series airplanes. That AD requires inspections of the areas behind the scuff plates below the passenger/crew doors and bulk cargo door to detect cracks and corrosion; inspections to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the door structures; and repair if necessary. In addition, that AD provides for an optional terminating action for certain inspections. We are considering further rulemaking to mandate the optional terminating action. Relevant Service Information Airbus has issued the service bulletins in the following table: Service Bulletins ------------------------------------------------------------------------ Airbus Service Bulletin-- Describes procedures for-- ------------------------------------------------------------------------ A310-53-2030, Revision 06, dated July Doing initial inspections for 2, 1996. cracks and corrosion of the areas behind the scuff plates below the passenger/crew doors and bulk cargo door, and repairing any cracked or corroded part. A310-53-2041, Revision 02, dated July Doing repetitive inspections 2, 1996. for cracks and corrosion of the areas behind the scuff plates below the passenger/ crew doors and bulk cargo door, and repairing any cracked or corroded part. A310-53-2037, Revision 02, dated Doing repetitive inspections November 27, 2000. for cracks of the holes of the corner doublers, the fail-safe ring, and the door frames of the passenger/crew door structures, and repairing any cracked part. A310-53-2017, Revision 09, dated May Modifying the passenger/crew 17, 2004. door structures, which ends the repetitive inspections of the holes of the corner doublers, fail-safe ring, and the door frames for certain airplanes. The modification includes cold expansion of fastener holes; a ROTO test; installation of new oversize fasteners and modified brackets; and installation of an additional steel doubler. ------------------------------------------------------------------------ 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 directives 1991-132-124(B) R1, issued November 29, 2000, and F-2004-103, issued July 7, 2004, to ensure the continued airworthiness of these airplanes in France. 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 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 applicable actions specified in the service information described previously, except as discussed under ``Differences Between the Proposed AD, French Airworthiness Directive, and Service Bulletins.'' Differences Between the Proposed AD, French Airworthiness Directive, and Service Bulletins Airbus Service Bulletin A310-53-2030 also does not list a grace period for certain compliance times. This proposed AD adds a grace period to certain compliance times. We find that a grace period will keep airplanes from being grounded unnecessarily. Airbus Service Bulletins A310-53-2041 and A310-53-2037 specify repetitive inspections at ``every'' specified interval; however, this proposed AD would require compliance ``at intervals not to exceed'' the time specified in the service bulletin. These service bulletins also specify compliance times in ``flights.'' This proposed AD would specify those times as flight cycles. In addition, Airbus Service Bulletin A310-53-2037 does not specify a starting date for the threshold for the initial inspections. This proposed AD would require compliance before the specified compliance time after the effective date of this AD. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this proposed AD. The average labor rate per hour is $65. Estimated Costs ---------------------------------------------------------------------------------------------------------------- Number of U.S.- Action Work hours Parts Cost per registered Fleet cost airplane airplanes ---------------------------------------------------------------------------------------------------------------- Initial inspections behind 26............. None........... $1,690......... 46 $77,740. scuff plates (for all airplanes). Repetitive inspections 26............. None........... $1,690......... 46 $77,740, per behind scuff plates, per inspection inspection cycle (for all cycle. airplanes). [[Page 70050]] Inspections of corner Between 4 and None........... Between $260 46 Between doublers, fail-safe ring, 50 depending and $3,250. $11,960, and and door frames, per on kit $149,500 per inspection cycle. purchased. inspection cycle. Terminating modification for Between 8 and Between $506 Between $1,026 46 Between $47,196 repetitive inspection of 55 depending and $6,098 and $9,673. and $444,958. corner doublers, fail-safe on kit depending on ring, and door frames. purchased. kit purchased. ---------------------------------------------------------------------------------------------------------------- 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 0130132. 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: PART 39--AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 401013, 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-2005-23007; Directorate Identifier 2005-NM- 013-AD. Comments Due Date (a) The FAA must receive comments on this AD action by December 21, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A310-203, -204, -221, and - 222 airplanes; and Airbus Model A310-304, -322, -324, and -325 airplanes; certificated in any category; excluding those airplanes on which Airbus Modification 5068, 7201, and 7298 have been incorporated in production. Unsafe Condition (d) This AD was prompted by reports of corrosion behind the scuff plates at passenger/crew doors and the bulk cargo door and fatigue cracks on the corner doublers of the forward and aft passenger/crew door frames. We are issuing this AD to prevent such corrosion and fatigue cracking, which could result in reduced structural integrity of the door surroundings. 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. Initial Inspections Behind Scuff Plates (f) Do initial inspections (i.e., non-destructive tests) for cracks and corrosion of the areas behind the scuff plates below the passenger/crew doors and bulk cargo door, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-53-2030, Revision 06, dated July 2, 1996. Do the inspections at the applicable time specified in paragraphs (f)(1) and (f)(2) of Table 1 of this AD. If a records check cannot positively identify if the applicable modification or service information specified in paragraphs (f)(1) and (f)(2) of this AD has been done, assume that it has not. Table 1.--Compliance Time Requirements for Initial Inspections Behind Scuff Plates ------------------------------------------------------------------------ For airplanes on which Modification 5382S6526 for the forward doors and And-- Inspect-- Modification 5382D4741 for all other doors-- ------------------------------------------------------------------------ (1) Have been incorporated None................ Within 108 months in production. after first flight. (2) Have not been (i) Airbus Service Within 48 months incorporated in production. Information Letter since the date of (SIL) A300-53-033, issuance of the Revision 2, dated original standard November 23, 1984, Airworthiness for all doors, was Certificate or the not followed; or date of issuance of Airbus Service the original Export Bulletin A310-53- Certificate of 2004, Revision 2, Airworthiness, or March 9, 1984 (only within 12 months applicable for the after the effective forward doors), was date of this AD, not done. whichever occurs later. [[Page 70051]] (ii) Airbus SIL A300- Within 60 months 53-033, Revision 2, since the date of dated November 23, issuance of the 1984, for all original doors, was Airworthiness followed; or Airbus Certificate or the Service Bulletin date of issuance of A310-53-2004, the original Export Revision 2, dated Certificate of March 9, 1984 (only Airworthiness, or applicable for the within 12 months forward doors), was after the effective done. date of this AD, whichever occurs later. (iii) Airbus SIL Within 12 months A300-53-033, after the effective Revision 2, dated date of this AD. November 23, 1984, for all doors, was followed; or Airbus Service Bulletin A310-53-2004, Revision 2, dated March 9, 1984 (only applicable for the forward doors), was done more than 48 months ago as of the effective date of this AD. ------------------------------------------------------------------------ Repetitive Inspections Behind Scuff Plates (g) Following the initial inspection required by paragraph (f) of this AD, do repetitive inspections (i.e., non-destructive tests) for cracks and corrosion of the areas behind the scuff plates below the passenger/crew doors and bulk cargo door, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-53-2041, Revision 02, dated July 2, 1996. Repeat the inspections at the applicable times specified in paragraphs (g)(1) through (g)(4) of Table 2 of this AD. Table 2.--Compliance Time Requirements for Repetitive Inspections Behind Scuff Plates ---------------------------------------------------------------------------------------------------------------- Unless in case of corrosion removal, For-- At-- Inspect at intervals then inspect at not to exceed-- intervals not to exceed-- ---------------------------------------------------------------------------------------------------------------- (1) All airplanes.................. The forward passenger/crew 60 months............. None. doors and the bulk cargo door. (2) All airplanes.................. The aft passenger/crew 60 months............. None. doors, except the upper and lower edges of the door frame panel cutout. (3) Model A310-203, -204, -221, and The aft passenger/crew 60 months or 12,000 60 months or 9,600 -222 airplanes. doors, the upper and lower flight cycles, flight cycles, edges of the door frame whichever occurs whichever occurs panel cutout. first. first. (4) Model A310-304, -322, -324, and The aft passenger/crew 60 months or 7,000 60 months or 5,600 -325 airplanes. doors, the upper and lower flight cycles, flight cycles, edges of the door frame whichever occurs whichever occurs panel cutout. first. first. ---------------------------------------------------------------------------------------------------------------- Repetitive Inspections of Corner Doublers, Fail-Safe Ring, and Door Frames (h) Do inspections (i.e., rotating probe, x-ray, and general visual, as applicable) for cracks of the holes of the corner doublers, the fail-safe ring, and the door frames of the passenger/ crew door structures, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-53-2037, Revision 02, dated November 27, 2000. Do the inspections at the applicable times specified in paragraphs (h)(1) through (h)(3) of Table 3 of this AD, until the modification required by paragraph (k) of this AD is done. Table 3.--Compliance Time Requirements for Repetitive Inspections of Corner Doublers, Fail-Safe Ring, and Door Frames ------------------------------------------------------------------------ For-- Inspect-- And-- ------------------------------------------------------------------------ (1) The upper corners of the Before the Do rotating probe forward doors. accumulation of inspections at 20,000 total flight intervals not to cycles, or within exceed 6,000 flight 2,000 flight cycles cycles. after the effective date of this AD, whichever occurs later. (2) The lower corners of the Before the Do rotating probe forward doors. accumulation of inspections at 20,000 total flight intervals not to cycles, or within exceed 10,000 4,000 flight cycles flight cycles. after the effective date of this AD, whichever occurs later. (3) The upper and lower Before the Do rotating probe corners and parts accumulation of inspections at underneath the corners of 20,000 total flight intervals not to the upper door frames of cycles, or within exceed 8,000 flight the aft doors. 4,000 flight cycles cycles or do x-ray after the effective inspections at date of this AD, intervals not to whichever occurs exceed 3,500 flight later. cycles; and do general visual inspections of areas around fasteners in vicinity of stringer 12 of the upper door frames at intervals not to exceed 6,900 flight cycles. ------------------------------------------------------------------------ [[Page 70052]] 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 ensure visual access to all 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.'' Corrective Actions (i) If any crack or corrosion is found during any inspection required by this AD, before further flight, do the applicable corrective action in paragraph (i)(1) through (i)(3) of Table 4 of this AD, except as provided by paragraph (j) of this AD. Table 4.--Corrective Actions ------------------------------------------------------------------------ In accordance with If-- Then-- the accomplishment instructions of-- ------------------------------------------------------------------------ (1) Any crack or corrosion Repair the cracked Airbus Service is found during any or corroded part. Bulletin A310-53- inspection required by 2030, Revision 06, paragraph (f) of this AD. dated July 2, 1996. (2) Any crack or corrosion Repair the cracked Airbus Service is found during any or corroded part. Bulletin A310-53- repetitive inspection 2041, Revision 02, required by paragraph (g) dated July 2, 1996. of this AD. (3) Any crack is found Repair the cracked Airbus Service during any inspection part. Bulletin A310-53- required by paragraph (h) 2037, Revision 02, of this AD. dated November 27, 2000. ------------------------------------------------------------------------ (j) If any crack or corrosion is found during any inspection required by this AD, and the service bulletin recommends contacting Airbus for appropriate action: Before further flight, repair the cracked or corroded part in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated agent). Terminating Modification for Repetitive Inspection of Corner Doublers, Fail-Safe Ring, and Door Frames (k) Modify the passenger/crew door structures in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-53- 2017, Revision 09, dated May 17, 2004. Do the modification at the applicable time in paragraph (k)(1) or (k)(2) of Table 5 of this AD. Accomplishment of this modification constitutes terminating action for the repetitive inspections required by paragraph (h) of this AD. The inspections required by paragraph (f) of this AD must be done before accomplishing this modification. Table 5.--Compliance Time for Terminating Modification ------------------------------------------------------------------------ For model-- Compliance time ------------------------------------------------------------------------ (1) A310-203, -204, -221, and -222 Before the accumulation of airplanes. 40,000 flight cycles since the date of issuance of the original standard Airworthiness Certificate or the date of issuance of the original Export Certificate of Airworthiness, or during the next inspection required by paragraph (h) of this AD, whichever occurs later. (2) A310-304, -322, -324, and -325 Before the accumulation of airplanes. 35,000 flight cycles since the date of issuance of the original standard Airworthiness Certificate or the date of issuance of the original Export Certificate of Airworthiness, or during the next inspection required by paragraph (h) of this AD, whichever occurs later. ------------------------------------------------------------------------ Alternative Methods of Compliance (AMOCs) (l)(1) The Manager, International Branch, ANM-116, 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 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 (m) French airworthiness directives 1991-132-124(B) R1, issued November 29, 2000, and F-2004-103, issued July 7, 2004, also address the subject of this AD. Issued in Renton, Washington, on November 9, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-22971 Filed 11-18-05; 8:45 am] BILLING CODE 4910-13-P
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