2002-14-28: Front Fuselage Struts

2002-14-28 de Havilland Inc.: Amendment 39-12828; Docket No. 98-CE-124-AD. (a) What airplanes are affected by this AD? This AD affects all serial numbers of Models DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. III airplanes that are certificated in any category. (b) Who must comply with this AD? Anyone who wishes to operate any of the airplanes identified in paragraph (a) of this AD must comply with this AD. (c) What problem does this AD address? The actions specified by this AD are intended to prevent structural failure of the front fuselage caused by corrosion or fatigue damage to the struts that develops over time, which could result in reduced or loss of control of the airplane. (d) What actions must I accomplish to address this problem? To address this problem, you must accomplish the following: Actions Compliance Procedures (1) Replace each front fuselage strut with a new strut. Part numbers for existing and replacement front fuselage struts parts are presented in paragraph (e) of this AD. Initially replace upon accumulating 15 years on each front fuselage strut or within the next 12 calendar months after September 6, 2002 (the effective date of this AD), whichever occurs later. Repetitively replace thereafter upon accumulating 15 years on each front fuselage strut. In accordance with the applicable maintenance manual, as specified in de Havilland Parts Service Manual 1-2-2, Part 5, Temporary Revision 2-22; and de Havilland Parts Service Manual 1-2T-2, Part 5, Temporary Revision 2T-6, both dated August 3, 1998. (2) As an alternative method of compliance to the replacements in paragraph (d)(1) of this AD, you may repetitively inspect each front fuselage strut, as follows:. (i) perform a detailed inspection of each front fuselage strut and all fittings attached to the frame for damage (corrosion, cracks, dents). When fatigue damage is found, you must replace the damaged strut. After each inspection, clean the drain holes aroundthe bottom end fitting and protect the tube with an appropriate corrosion preventive spray. Part numbers for existing and replacement front fuselage struts parts are presented in paragraph (e) of this AD. (ii) perform an ultrasonic thickness measurement of all surface on each front fuselage strut. When minimum thickness is below 0.030 inches, you must replace the affected strut. Part numbers for existing and replacement front fuselage struts parts are presented in paragraph (e) of this AD. Initially inspect upon accumulating 15 years on each front fuselage strut or within the next 12 calendar months after September 6, 2002 (the effective date of this AD), whichever occurs later. Accomplish the repetitive detailed inspection thereafter at intervals not to exceed 12 months and the ultrasonic thickness measurement at intervals not to exceed 5 years. Accomplish the corrosion prevention work prior to further flight after each inspection. Accomplish the replacement prior to further flight after damage is found or the thickness is found below 0.030 inches. Then, after replacement either replace with a new strut at 15-year intervals thereafter or repetitively inspect as prescribed above beginning at 15 years after each replacement. For the detailed inspection, use an inspection light, inspection mirror, and 10X magnifying glass. For the ultrasonic inspection, use FAA-approved procedures that follow a similar calibration and measures strut thickness to that detailed in Bombardier Service Bulletin 2/49, Revision C. (3) Do not install, on any affected airplane, any front fuselage strut unless it has a part number specified in the Replacement Part Number column of the chart presented in paragraph (e) of this AD. As of September 6, 2002 (the effective date of this AD. Not Applicable. (e) What part number front fuselage struts should I use for replacements? The following charts presents the part numbers for existing parts and replacement parts for the front fuselagestrut replacements: Installed part No. Replacement part No. Description C2FS209 or C2FS3281A C2FS3281A Strut Assembly Front Fuselage, Left. C2FS210 or C2FS3282A C2FS3282A Strut Assembly Front Fuselage, Right. (f) Can I comply with this AD in any other way? You may use an alternative method of compliance or adjust the compliance time if: (1) Your alternative method of compliance provides an equivalent level of safety; and (2) The Manager, New York Aircraft Certification Office (ACO), approves your alternative. Submit your request through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. Note 1: This AD applies to each airplane identified in paragraph (a) of this AD, 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 (f) 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 you have not eliminated the unsafe condition, specific actions you propose to address it. (g) Where can I get information about any already-approved alternative methods of compliance? Contact Jon Hjelm, Aerospace Engineer, FAA, New York Aircraft Certification Office, 10 Fifth Street, Third Floor, Valley Stream, New York 11581; telephone: (516) 256-7523; facsimile: (516) 256-2716. (h) What if I need to fly the airplane to another location to comply with this AD? The FAA can issue a special flight permit under sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate your airplane to a location where you can accomplish the requirements of this AD.(i) How do I get copies of the documents referenced in this AD? You may direct technical questions to or get copies of the documents referenced in this AD from Bombardier Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario, Canada M3K 1Y5; telephone: (416) 633-7310. You may view these documents at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106. Note 2: The subject of this AD is addressed in Canadian AD CF-98-37R1, dated August 20, 1999. (j) When does this amendment become effective? This amendment becomes effective on September 6, 2002.