Airworthiness Directive · Amendment 39-11636 · Aerospatiale Model ATR42-200, ATR42-300, and ATR42-320 Series Airplanes
Aerospatiale Model ATR42-200, ATR42-300, and ATR42-320 Series Airplanes
Superseded. A later AD replaced this one: AD 2005-25-02. Comply with the one in force.
All Model ATR42-200, ATR42-300, and ATR42-320 series airplanes; certificated in any category.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (h) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-300 and ATR42-320 series airplanes, that currently requires inspections to determine the proper installation of rivets in certain key holes and to detect cracks in the area of the key holes where rivets are missing; and correction of discrepancies. This amendment increases the compliance time for the existing requirements and expands the applicability of the existing AD to include additional airplanes. This action also requires various inspections of the subject area for discrepancies, and corrective actions, if necessary; and replacement of certain cargo door hinges with new hinges. For certain airplanes, this action also requires replacement of friction plates, stop fittings, and bolts with new parts. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended 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.
To prevent fatigue cracks of the cargo door skin, certain frames, entry door stop fittings, or friction plates, which could result in reduced structural integrity of the airplane, accomplish the following:
(a) 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 the effective date of this AD, 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 Regional (ATR) Service Bulletin ATR42-53-0070, Revision 2, dated March 22, 1993, or Revision 3, dated February 19, 1999.
Note 2: For the purposes of this AD, a general visual inspection is defined as “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 under normally available lighting conditions such as daylight, hangar lighting, flashlight, or drop-light, 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 check.”
Note 3: Inspection of fuselage frames 25 and 27 accomplished prior to the effective date of this AD 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 (a) 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, FAA, Transport Airplane Directorate, or the Direction Ge ne rale 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.
(b) 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 the effective date of this AD, whichever occurs later, except as provided by paragraph (c) 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.
(c) Where the instructions in ATR Service Bulletin ATR42-52-0058, Revision 1, dated March 1, 1995, 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).
(d) For airplanes having serial numbers 003 through 208 inclusive: Prior to the accumulation of 36,000 total flight cycles, or within 180 days after the effective date of this AD, 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 visual inspection of each open tooling or key hole to detect cracks, in accordance with the service bulletin.
Note 4: For the purposes of this AD, a detailed visual inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc. may be used. Surface cleaning and elaborate access procedures may be required.”
(i) If no crack is found during the detailed visual inspection required by paragraph (d)(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 visual inspection required by paragraph (d)(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).
(e) For Model ATR42-300 series 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 the effective date of this AD, whichever occurs later, accomplish the requirements of paragraphs (e)(1) and (e)(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 visual 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.
(f) For Model ATR42-300 series airplanes listed in ATR Service Bulletin ATR42-52-0052, Revision 1, dated March 2, 1993, accomplishment of the requirements of paragraph (g) of this AD at the time specified in paragraph (e) of this AD constitutes terminating action for the requirements of paragraph (e) of this AD.
(g) For Model ATR42-300 series 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 the effective date of this AD, whichever occurs later, accomplish the requirements of paragraphs (g)(1), (g)(2), and (g)(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.
