AD 2005-25-02 Airworthiness Directives; Aerospatiale Model ATR42-200, ATR42-300, and ATR42-320 Airplanes

Models named: ATR42-200, ATR42-300, ATR-320. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to all Aerospatiale Model ATR42-200, ATR42-300, and ATR-320 airplanes, certificated in any category.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Restatement of the Requirements of AD 2000-05-26 Frame 25 and 27 Inspection (f) For airplanes having serial numbers 005 through 016 inclusive, 018 through 030 inclusive, 032 through 036 inclusive, 038, 040, 042, 043, 048 through 062 inclusive, 064 through 090 inclusive, 092 through 094 inclusive, and 096 through 228 inclusive: Prior to the accumulation of 36,000 total flight cycles, or within 180 days after April 26, 2000, (the effective date of AD 2000-05-26) whichever occurs later, conduct a general visual inspection of fuselage frames 25 and 27 to verify the proper installation of a rivet in each of the key holes, in accordance with Avions de Transport Regionale (ATR) Service Bulletin ATR42-53-0070, Revision 2, dated March 22, 1993; or Revision 3, dated February 19, 1999. 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.” Note 2: Inspection of fuselage frames 25 and 27 accomplished prior to April 26, 2000, in accordance with ATR Service Bulletin ATR42-53-0070, dated June 10, 1991; or Revision 1, dated June 12, 1992; is considered acceptable for compliance with the requirements of paragraph (f) of this AD. (1) If a rivet is installed in each of the key holes, no further action is required by this paragraph. (2) If a rivet is not installed in each of the key holes, prior to further flight, perform an eddy current inspection of each open key hole to detect cracks, in accordance with the service bulletin. (i) If no crack is found during the eddy current inspection, prior to further flight, install a rivet in the open key hole in accordance with the service bulletin. After such installation, no further action is required by this paragraph for that key hole. (ii) If any crack is found during the eddy current inspection, prior to further flight, repair the crack in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent). For a repair method to be approved by the Manager, International Branch, ANM-116, as required by this paragraph, the Manager's approval letter must specifically reference this AD. Inspection and Modification of Cargo Door Structure (g) For airplanes equipped with a cargo compartment door on which Aerospatiale Modification 3191 has not been accomplished: Prior to the accumulation of 27,000 total flight cycles, or within 180 days after April 26, 2000, whichever occurs later, except as provided by paragraph (h) of this AD, replace the hinges on the cargo compartment door and fuselage (including inspections for fastener type and tolerances, hole diameters, or cracking, and repair; as applicable) with new improved hinges, in accordance with paragraph 2. of the Accomplishment Instructions of ATR Service Bulletin ATR42-52-0058, Revision 1, dated March 1, 1995; or ATR42-52-0058, Revision 2, dated June 22, 2000. (h) Where the instructions in ATR Service Bulletin ATR42-52-0058, Revision 1, dated March 1, 1995; or ATR42-52-0058, Revision 2, dated June 22, 2000, specify that ATR is to be contacted for a repair, prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, or the DGAC (or its delegated agent). Frame Inspection (i) For airplanes having serial numbers 003 through 208 inclusive: Prior to the accumulation of 36,000 total flight cycles, or within 180 days after April 26, 2000, whichever occurs later, conduct a general visual inspection of the identified fuselage frames for proper installation of a rivet in each of the tooling and key holes, in accordance with ATR Service Bulletin ATR42-53-0076, Revision 2, dated October 15, 1996; or Revision 3, dated February 19, 1999. (1) If a rivet is installed in each of the tooling or key holes, no further action is required by this paragraph. (2) If a rivet is not installed in each of the tooling and key holes, prior to further flight, perform a detailed inspection of each open tooling or key hole to detect cracks, in accordance with the service bulletin. Note 3: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.” (i) If no crack is found during the detailed inspection required by paragraph (i)(2) of this AD, prior to further flight, install a rivet in the open hole in accordance with the service bulletin. (ii) If any crack is found during the inspection required by paragraph (i)(2) of this AD, prior to further flight, repair the crack in accordance with a method approved by the Manager, International Branch, ANM-116; or the DGAC (or its delegated agent). Inspection and/or Replacement of Entry Door Structure (j) For Model ATR42-300 airplanes having serial numbers listed in ATR Service Bulletin ATR42-52-0052, Revision 1, dated March 2, 1993: Except as provided by paragraph (f) of this AD, prior to the accumulation of 10,000 total flight cycles, or within 90 days after April 26, 2000, whichever occurs later, accomplish the requirements of paragraphs (j)(1) and (j)(2) of this AD. (1) Perform an eddy current inspection of the forward entry door stop holes to detect cracking, in accordance with the service bulletin. If any cracking is detected, prior to further flight, replace any cracked forward entry door stop fitting with a new fitting, in accordance with the service bulletin. (2) Perform a detailed inspection of the forward entry door friction plates for wear, in accordance with the service bulletin. If wear is found on any friction plate, and the wear has a depth equal to or greater than 0.8mm (0.0315 in.), prior to further flight, replace the friction plate with a new or serviceable part in accordance with the service bulletin. (k) For Model ATR42-300 airplanes listed in ATR Service Bulletin ATR42-52-0052, Revision 1, dated March 2, 1993, accomplishment of the requirements of paragraph (l) of this AD at the time specified in paragraph (j) of this AD constitutes terminating action for the requirements of paragraph (j) of this AD. (l) For Model ATR42-300 airplanes listed in ATR Service Bulletin ATR42-52-0059, dated February 16, 1995: Prior to the accumulation of 18,000 total flight cycles, or within 180 days after April 26, 2000, whichever occurs later, accomplish the requirements of paragraphs (l)(1), (l)(2), and (l)(3) of this AD in accordance with the service bulletin. (1) Replace the forward entry door friction plates with improved friction plates. (2) Replace the upper corners of the forward entry door surround structure with improved door surround corners. (3) Replace the forward entry door stop fittings and bolts with improved fittings and bolts. New Requirements of This AD Replacing Hinges on the Cargo Compartment Door and Fuselage (m) For airplanes identified as having main serial numbers (MSNs) 317, 319, 321, 323, 325, 327, 329 through 335 inclusive, 360, and 368, that are equipped with a cargo compartment door on which Aerospatiale Modification 3191 has not been accomplished: Prior to the accumulation of 27,000 total flight hours, or within 180 days after the effective date of this AD, whichever occurs later, replace the hinges on the cargo compartment door and fuselage (including inspections for fastener type and tolerances, hole diameters, or cracking, and repair; as applicable) with new improved hinges, in accordance with the Accomplishment Instructions of Avions de Transport Regional (ATR) Service Bulletin ATR42-52-0058, Revision 2, dated June 22, 2000. (n) Where the instructions in ATR Service Bulletin ATR42-52-0058, Revision 2, dated June 22, 2000, specify that ATR is to be contacted for a repair, prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116; or the DGAC (or its delegated agent). Alternative Methods of Compliance (AMOCs) (o)(1) The Manager, International Branch, ANM-116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 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 (p) French airworthiness directive 2000-337-079(B), dated July 26, 2000, also addresses the subject of this AD. Material Incorporated by Reference (q) You must use the service bulletins listed in Table 1 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. Table 1.—Material Incorporated by Reference Avions de Transport regional service bulletin Revision level Date ATR42-52-0052 1 March 2, 1993. ATR42-52-0058 1 March 1, 1995. ATR42-52-0058 2 June 22, 2000. ATR42-52-0059 Original February 16, 1995. ATR42-53-0070 2 March 22, 1993. ATR42-53-0070 3 February 19, 1999. ATR42-53-0076 2 October 15, 1996. ATR42-53-0076 3 February 19, 1999. (1) The Director of the Federal Register approved the incorporation by reference of Avions de Transport Regional Service Bulletin ATR42-52-0058, Revision 2, dated June 22, 2000, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On April 26, 2000 (65 FR 15226, March 22, 2000), the Director of the Federal Register approved the incorporation by reference of the Avions de Transport Regionale service information as listed in Table 2 of this AD. Table 2.—Previous Material Incorporated by Reference Avions de Transport regionale service bulletin Revision level Date ATR42-52-0052 1 March 2, 1993. ATR42-52-0058 1 March 1, 1995. ATR42-52-0059 Original February 16, 1995. ATR42-53-0070 3 February 19, 1999. ATR42-53-0076 2 October 15, 1996. ATR42-53-0076 3 February 19, 1999. (3) On November 18, 1993, (58 FR 53853, October 19, 1993), the Director of the Federal Register approved the incorporation by reference of Avions de Transport Regionale Service Bulletin ATR42-53-0070, Revision 2, dated March 22, 1993. (4) Contact Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France, for copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov ; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html . Issued in Renton, Washington, on November 25, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-23556 Filed 12-2-05; 8:45 am] BILLING CODE 4910-13-P

This AD results from discovery of cracks around key holes on certain fuselage frames where rivets were missing. We are issuing this AD to prevent fatigue cracks of the cargo door skin, certain frames, and entry door stop fittings and friction plates, which could result in reduced structural integrity of the airplane.