Airworthiness directives › 2018-03-12
AD 2018-03-12 Airworthiness Directives; Airbus Airplanes
Models named: A318-111, -112, -121, -122, A319-111, -113, -114, -115, -131, -132. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to Airbus Model A318-111, -112, -121, and -122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, 231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes; certificated in any category; all manufacturer serial numbers, except airplanes specified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD. (1) Airplanes on which Airbus modification (Mod) 157039 has been embodied in production. (2) Model A319 series airplanes on which Mod 28238, Mod 28162, and Mod 28342 have been embodied in production. (3) Model A318 series airplanes on which Mod 39195 has been embodied in production or Airbus Service Bulletin A320-00-1219 has been embodied in service.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
Within the applicable compliance times specified in table 1 to paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and (j) of this AD: Do a rototest inspection of all holes below each door stop fitting at fuselage FR66 and FR68, both left-hand (LH) and right-hand (RH) sides, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016; or using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). Repeat the inspections thereafter at the applicable compliance times specified in table 1 to paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and (j) of this AD, until the modification specified in paragraph (i) of this AD is done. Where the “Threshold” column of table 1 to paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and (j) of this AD, specifies compliance times in “FC” (flight cycles), those compliance times are total flight cycles since the first flight of the airplane. BILLING CODE 4910-13-P ER12FE18.000 ER12FE18.001 ER12FE18.002 BILLING CODE 4910-13-C
Unsafe condition
This AD was prompted by reports of fatigue damage in the structure for the door stop fittings on certain fuselage frames (FR). We are issuing this AD to detect and correct cracking at the door stop fitting holes of fuselage FR66 and FR68. Such cracking could result in reduced structural integrity of the airplane due to the failure of structural components.
Affected ADs
None.
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1