Airworthiness directives › 2016-08-08
AD 2016-08-08 Airworthiness Directives; SOCATA Airplanes
Makes named: socata. Models named: MS 880B, MS 885, MS 892A-150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS 894E, Rallye 100S, Rallye 150ST. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to SOCATA Models MS 880B, MS 885, MS 892A-150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS 894E, Rallye 100S, Rallye 150ST, Rallye 150T, Rallye 235E, and Rallye 235C airplanes, all serial numbers, certificated in any category.
Compliance
Do the actions in paragraphs (f)(1) through (f)(5) of this AD, including all subparagraphs. If the initial actions of paragraphs (f)(1), (f)(2), (f)(3), and (f)(4) of this AD have already been done before the effective date of this AD, then do the repetitive actions of these paragraphs at the specified times. (1) Do a detailed visual inspection of the intersection between the axle radius and the nose landing gear fork area for chafing at whichever occurs later in paragraph (f)(1)(i) or (f)(1)(ii) of this AD and repetitively thereafter at intervals not to exceed 200 hours time-in-service (TIS) following Daher-Socata Mandatory Service Bulletin SB 150-32, Revision 3, dated September 2015: (i) Upon accumulating 200 hours TIS since the airplane's first flight or 200 hours TIS since the last inspection required by AD 92-06-10; or (ii) Within the next 50 hours TIS after May 18, 2016 (the effective date of this AD) or within 500 hours TIS since the last inspection required by AD 92-06-10, whichever occurs first. (2) Do a dye penetrant inspection on the nose wheel axle for cracks, distortion, and nicks or wear at whichever occurs later in paragraph (f)(2)(i) or (f)(2)(ii) of this AD and repetitively thereafter at intervals not to exceed 200 hours time-in-service (TIS) following Daher-Socata Mandatory Service Bulletin SB 150-32, Revision 3, dated September 2015: (i) Upon accumulating 200 hours TIS since the airplane's first flight or 200 hours TIS since the last inspection required by AD 92-06-10; or (ii) Within the next 50 hours TIS after May 18, 2016 (the effective date of this AD) or within 500 hours TIS since the last inspection required by AD 92-06-10, whichever occurs first. (3) If any cracks or damage is found in any inspection required by paragraphs (f)(1) or (f)(2) in this AD, contact SOCATA for FAA-approved repair or replacement instructions approved specifically for this AD and, before further flight, implement those instructions. Use the contact information found in paragraph (j) of this AD to contact SOCATA. (4) Replace the nose landing gear wheel axle attachment screws with new screws at whichever occurs later in paragraph (f)(4)(i) or (f)(4)(ii) of this AD following Daher-Socata Mandatory Service Bulletin SB 150-32, Revision 3, dated September 2015: (i) Upon accumulating 2,000 hours TIS since airplane's first flight or 2,000 hours TIS since last nose landing gear wheel attachment screw replacement with new screws; or (ii) Within 50 hours TIS since April 17, 1992 (the effective date retained from AD 92-06-10). (5) After May 18, 2016 (the effective date of this AD), a used nose landing gear or a used nose landing gear wheel axle may be installed provided it has been inspected and found free of cracks and/or damage and the nose landing gear wheel axle attachment screws have been replaced with new screws as specified in paragraphs (f)(1), (f)(2), and (f)(4) of this AD.
Required actions
This AD allows credit for the inspections required in paragraph (f)(1) and (f)(2) of this AD, if done before May 18, 2016 (the effective date of this AD), following Daher-Socata Mandatory Service Bulletin SB 150-32, Revision 2, dated January 1994.
Unsafe condition
This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as fatigue failure of the nose landing gear wheel axle. We are issuing this AD to detect and correct chafing and cracking of the nose gear wheel axle, which could lead to failure of the nose landing gear with consequent damage to the airplane and/or occupants.
Affected ADs
This AD supersedes AD 92-06-10 Amendment 39-8190 (57 FR 8063; March 6, 1992) (“AD 92-06-10”).
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