Airworthiness directives › 2016-20-08
AD 2016-20-08 Airworthiness Directives; Airbus Airplanes
Models named: A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, B4-203, A300 B4-601, B4-603, B4-620. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(5) of this AD, certificated in any category. (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes, all manufacturer serial numbers (MSNs). (2) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, and B4-622R airplanes, all MSNs. (3) Airbus Model A300 F4-605R, all MSNs, except those airplanes on which both Airbus Modifications 11133 and 12699 have been embodied. (4) Airbus Model A300 F4-622R airplanes, all MSNs, except those airplanes on which the modifications identified in paragraph (c)(4)(i) or (c)(4)(ii) of this AD have been embodied. (i) All Airbus Modifications 11133, 12047, 12048, and 12050 have been embodied. (ii) Both Airbus Modifications 11133 and 12699 have been embodied. (5) Airbus Model A300 C4-605R Variant F airplanes, all MSNs.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
This paragraph restates the requirements of paragraph (a) of AD 95-21-09, with Note 3 of AD 95-21-09 incorporated and additional terminating provisions. For Model A300 series airplanes: Prior to the accumulation of 15,000 total landings, or within the next 120 days after May 9, 1985 (the effective date of AD 85-07-04, Amendment 39-5027 (50 FR 13013, April 2, 1985) (“AD 85-07-04”)), whichever occurs later, inspect for cracking of the base steel member and light alloy side members of the No. 2 flap beams, left hand and right hand, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-116, Revision 6, dated July 16, 1993. Accomplishing the requirements of paragraph (h) or (l) of this AD terminates the requirements of this paragraph. Measurement of crack length is performed by measurement of the probe displacement (perpendicular to symmetry plane of beam) between defect indication appearance and its complete disappearance. The bolt hole indication should not be interpreted as an indication of a defect. These two indications appear very close together because the defects originate from the bolt holes. (1) If no cracking is detected: Except as provided by paragraph (i) of this AD, repeat the inspection at intervals not to exceed 1,700 landings until the requirements of paragraph (h) or (l) of this AD are accomplished. (2) If any crack is detected that is less than or equal to 4 millimeters (mm): Repeat the inspection at intervals not to exceed 250 landings, until the requirements of paragraph (h) or (l) of this AD are accomplished. (3) If any crack is detected that exceeds 4 mm: Prior to further flight, replace the flap beam in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-116, Revision 6, dated July 16, 1993, and prior to the accumulation of 15,000 flight cycles on the replaced flap beam, perform the ultrasonic inspection as required by paragraph (h) or (l) of this AD.
Unsafe condition
This AD was prompted by a determination that the compliance times must be reduced. We are issuing this AD to detect and correct cracking of the No. 2 flap beams, which could result in rupture of the flap beams and reduced structural integrity of the airplane.
Affected ADs
This AD replaces AD 95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995) (“AD 95-21-09”).
Read the original on the Federal Register →
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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