AD 2017-25-01 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.

This AD applies to the Airbus airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, all manufacturer serial numbers on which Airbus Modification 39729 was embodied in production, except those airplanes on which Airbus Modification 152155 or Modification 152200 was embodied in production. (1) Airbus Model A318-111, -112, -121, and -122 airplanes. (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes. (3) Airbus Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes.

Comply with this AD within the compliance times specified, unless already done.

Before exceeding the applicable compliance time specified in table 1 to paragraph (g) of this AD, or within 3 months after the effective date of this AD, whichever occurs later: Do a detailed inspection or a special detailed inspection for cracking of the external bottom skin in the area of the rib 2 attachment between stringer 8 and stringer 11 of the left and right wings, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1205, dated May 26, 2016. Do all applicable corrective actions before further flight. Repeat the inspection thereafter at the applicable intervals, based on the method used for the most recent inspection, as specified in table 2 to paragraph (g) of this AD. Table 1 to Paragraph ( g ) of This AD—Initial Inspection Times Airplane model and configuration Compliance time—whichever occurs first since first flight of the airplane Model A318 series airplanes; Model A319 series airplanes; and Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; pre-Airbus Modification 155374; not used as VIP or Elite Before the accumulation of 14,500 total flight cycles or 29,000 total flight hours. Model A318 series airplanes; Model A319 series airplanes; and Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; post-Airbus Modification 155374; not used as VIP or Elite Before the accumulation of 13,600 total flight cycles or 27,300 total flight hours. Model A319 series airplanes; post-Airbus Modifications 28162, 28238, and 28342; used as VIP or CJ Before the accumulation of 7,400 total flight cycles or 32,000 total flight hours. Model A318 series airplanes; post-Airbus Modification 39195; used as VIP or Elite Before the accumulation of 14,500 total flight cycles or 43,500 total flight hours. Table 2 to Paragraph ( g ) of This AD—Repetitive Inspection Intervals Airplane model and configuration Detailed inspection— whichever occurs first Special detailed inspection— whichever occurs first Model A318 series airplanes; Model A319 series airplanes; and Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; not used as VIP or Elite 4,000 flight cycles or 8,000 flight hours 5,000 flight cycles or 10,000 flight hours. Model A319 series airplanes; post-Airbus Modifications 28162, 28238 and 28342; used as VIP or CJ 2,000 flight cycles or 8,600 flight hours 2,500 flight cycles or 11,000 flight hours. Model A318 series airplanes; post-Airbus Modification 39195; used as VIP or Elite 4,000 flight cycles or 12,000 flight hours 5,000 flight cycles or 15,000 flight hours. Note 1 to paragraph (g) of this AD: Airbus Modification 155374 defines the minimum airplane configuration for operation on Commonwealth of Independent States runway profiles.

This AD was prompted by a report indicating that the lower rib foot angle of the center wing box did not match with the bottom skin panel inner surface. Misalignment of the lower rib foot angle of the center wing box with the bottom skin panel inner surface could induce fatigue cracking of the skin panel at the rib foot attachment. We are issuing this AD to detect and correct cracking of the external bottom skin in the area of the rib 2 attachment of the wings, which could result in reduced structural integrity of the wings.

None.