Airworthiness Directive · Amendment 39-18674 · Wings
Airbus Airplanes
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.
We are superseding Airworthiness Directive (AD) 95-21-09 for all Airbus Model A300 series airplanes, and Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 95- 21-09 required repetitive inspections for cracking of the No. 2 flap beams, and replacement of the flap beams, if necessary; and provided optional modifications for extending certain inspection thresholds, and an optional terminating modification for certain inspections. This new AD requires reduced compliance times for inspections and also reduces the number of airplanes affected. 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.
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.
This paragraph restates the requirements of paragraph (b) of AD 95-21-09, with additional terminating provisions. For Model A300 series airplanes: Prior to the accumulation of 15,000 total landings, or within the next 1,000 landings after November 17, 1995 (the effective date of AD 95-21-09), whichever occurs later, perform an ultrasonic inspection to detect cracking of the No. 2 flap beams, in accordance with Airbus Service Bulletin A300-57-116, Revision 6, dated July 16, 1993. Accomplishment of this inspection terminates the inspections required by paragraph (g) of this AD. Accomplishment of the requirements of paragraph (l) of this AD terminates the requirements of this paragraph.
(1) If no cracking is detected: Except as provided by paragraph (i) of this AD, repeat the ultrasonic inspections thereafter at intervals not to exceed 1,700 landings.
(2) If any crack is detected beyond the bolt hole, and that crack is less than or equal to 4 mm in length: Repeat the ultrasonic inspections thereafter at intervals not to exceed 250 landings.
(3) If any crack is detected beyond the bolt hole and that crack is greater than 4 mm in length: Prior to further flight, replace the flap beam in accordance with 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 this paragraph.
This paragraph restates the provisions of paragraph (c) of AD 95-21-09, with changes to compliance extension. For Model A300 series airplanes: After accomplishing the initial inspection required by paragraph (h) of this AD, accomplishment of either paragraph (i)(1) or (i)(2) of this AD before the effective date of this AD extends the fatigue life of the No. 2 flap track beam as specified in those paragraphs, provided that no cracking is detected during any inspection required by paragraph (g) or (h) of this AD.
(1) Removal of any damage and the installation of larger diameter bolts on the No. 2 flap track beam (Modification No. 4740), in accordance with Airbus Service Bulletin A300-57-128, Revision 3, dated January 26, 1990, extends the interval for the first repetitive inspection required by paragraph (h) of this AD from 1,700 landings to 12,000 landings, provided that Modification No. 4740 is accomplished prior to the accumulation of 16,700 total landings on the flap beams. Following accomplishment of the first repetitive inspection, subsequent repetitive inspections shall be performed at intervals not to exceed 1,700 landings.
(2) Cold working of the bolt holes and the installation of larger diameter bolts on the No. 2 flap track beam (Modification No. 5815), in accordance with Airbus Service Bulletin A300-57-141, Revision 7, dated July 16, 1993, extends the interval for the first repetitive inspection required by paragraph (h) of this AD from 1,700 landings to the interval specified in paragraph (i)(2)(i) or (i)(2)(ii) of this AD.
(i) If interference fit bolts that are 15/32 -inch in diameter are fitted, the interval for the first repetitive inspection required by paragraph (h) of this AD is extended to 22,000 landings, provided that Modification No. 5815 is accomplished prior to the accumulation of 16,700 total landings on the flap beam. Following accomplishment of the first repetitive inspection required by paragraph (h) of this AD, subsequent repetitive inspections shall be performed at intervals not to exceed 1,700 landings.
(ii) If interference fit bolts that are 7/16 - or 3/8 -inch in diameter are fitted, the interval for the first repetitive inspection required by paragraph (h) of this AD is extended to 33,000 landings, provided that Modification No. 5815 is accomplished prior to the accumulation of 16,700 total landings on the flap beam. Following accomplishment of the first repetitive inspection required by paragraph (h) of this AD, subsequent repetitive inspections shall be performed at intervals not to exceed 1,700 landings.
This paragraph restates the requirements of paragraph (d) of AD 95-21-09, with terminating provisions. For Model A300-600 series airplanes: Prior to the accumulation of 15,000 total landings, or within the next 1,000 landings after November 17, 1995 (the effective date of AD 95-21-09), whichever occurs later, perform an ultrasonic inspection to detect cracking of the No. 2 flap track beams, in accordance with Airbus Service Bulletin A300-57-6005, Revision 2, dated December 16, 1993. Accomplishing the actions required by paragraph (l) of this AD terminates the requirements of this paragraph.
(1) If no cracking is detected, repeat the ultrasonic inspections thereafter at intervals not to exceed 1,700 landings.
(2) If any crack is detected beyond the bolt hole and that crack is less than or equal to 4 mm in length: Repeat the ultrasonic inspections thereafter at intervals not to exceed 250 landings.
(3) If any crack is detected beyond the bolt hole and that crack is greater than 4 mm in length: Prior to further flight, replace the flap beam in accordance with Airbus Service Bulletin A300-57-6005, Revision 2, dated December 16, 1993, and prior to the accumulation of 15,000 landings on the replaced flap beam, perform the ultrasonic inspection required by paragraph (j) of this AD.
This paragraph restates the provisions of paragraph (e) of AD 95-21-09, with Note 5 of AD 95-21-09 incorporated and changes to terminating action. For Model A300-600 series airplanes: Installation of oversized transition fit bolts in cold-worked holes, in accordance with Airbus Service Bulletin A300-57-6006, Revision 4, dated July 25, 1994 (Modification No. 5815), constitutes terminating action for the repetitive inspection requirements of paragraph (j) of this AD, provided that no cracking is detected during any inspection required by paragraph (j) of this AD, and provided that the installation is accomplished prior to the accumulation of 15,000 total landings and before the effective date of this AD. If any bolt requires oversizing above 7/16 -inch diameter during accomplishment of this installation, prior to further flight, repair using a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate; or by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA. As of the effective date of this AD, any new repair approval must be done using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA. If Airbus Service Bulletin A300-57-6005, Revision 2, dated December 16, 1993, was accomplished concurrently with Airbus Service Bulletin A300-57-6006, Revision 3, dated December 16, 1993 (Modification No. 5815), the ultrasonic inspection for cracking required by paragraph (j) of this AD need not be performed since the eddy current inspection detailed for Modification No. 5815 is more comprehensive.
At the applicable time specified in paragraph (l)(1) or (l)(2) of this AD and, thereafter at intervals not to exceed those defined in table 3 to paragraph (l) of this AD, as applicable, accomplish an ultrasonic inspection for cracking of the steel base member and the aluminum side members' flap beam on the left-hand (LH) and right-hand (RH) sides, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0116, Revision 07, dated September 19, 2011, including Appendixes A and B; or Airbus Service Bulletin A300-57-6005, Revision 06, dated November 14, 2013; as applicable. For the purposes of this AD, average flight time (AFT) must be established as specified in paragraph (m) of this AD. Doing the actions required by this paragraph terminates the requirements of paragraphs (g) through (k) of this AD.
(1) For Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes (referred to as Model A300 series airplanes): Within the applicable compliance time defined in table 1 to paragraph (l) of this AD.
(2) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R airplanes, and Model A300 C4-605R Variant F airplanes (referred to as Model A300-600 series airplanes): At the later of the times specified in paragraphs (l)(2)(i) and (l)(2)(ii) of this AD.
(i) Within the compliance time defined in table 2 to paragraph (l) of this AD.
(ii) Within 300 flight cycles or 640 flight hours after the effective date of this AD, whichever occurs first.
| Airplane configuration | Compliance times for airplanes with an AFT of less than 1.5 | Compliance times for airplanes with an AFT of more than or equal to 1.5 |
|---|---|---|
| Model A300 B2-1A, B2-1C, B2K-3C, B2-203 airplanes on which Airbus Modifications 4740 and 5815 have not been embodied | Within 15,000 flight cycles or 16,900 flight hours since first flight of the airplane, whichever occurs first | Within 15,000 flight cycles or 16,900 flight hours since first flight of the airplane, whichever occurs first. |
| Model A300 B4-103 airplanes on which Airbus Modifications 4740 and 5815 have not been embodied | Within 15,000 flight cycles or 20,500 flight hours since first flight of the airplane, whichever occurs first | Within 15,000 flight cycles or 20,500 flight hours since first flight of the airplane, whichever occurs first. |
| Model A300 B4-2C, and B4-203 airplanes on which Airbus Modifications 4740 and 5815 have not been embodied | Within 16,200 flight cycles or 22,200 flight hours since first flight of the airplane, whichever occurs first | Within 15,000 flight cycles or 34,000 flight hours since first flight of the airplane, whichever occurs first. |
| Model A300 B2-1A, B2-1C, B2K-3C, B2-203 airplanes on which Airbus Modification 4740 has been embodied | Within 12,000 flight cycles or 13,500 flight hours since embodiment of Airbus Modification 4740, whichever occurs first | Within 12,000 flight cycles or 13,500 flight hours since embodiment of Airbus Modification 4740, whichever occurs first. |
| Model A300 B4-103 airplanes on which Airbus Modification 4740 has been embodied | Within 12,000 flight cycles or 16,400 flight hours since embodiment of Airbus Modification 4740, whichever occurs first | Within 12,000 flight cycles or 16,400 flight hours since embodiment of Airbus Modification 4740, whichever occurs first. |
| Model A300 B4-2C, and B4-203 airplanes on which Airbus Modification 4740 has been embodied | Within 12,900 flight cycles or 17,700 flight hours since embodiment of Airbus Modification 4740, whichever occurs first | Within 12,000 flight cycles or 27,200 flight hours since embodiment of Airbus Modification 4740, whichever occurs first. |
| Model A300 B2-1A, B2-1C, B2K-3C, B2-203 airplanes on which Airbus Modification 5815 has been embodied and no bolt larger than 7/16 -inch diameter is fitted | Within 33,000 flight cycles or 37,200 flight hours since embodiment of Airbus Modification 5815, whichever occurs first | Within 33,000 flight cycles or 37,200 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. |
| Model A300 B4-103 airplanes on which Airbus Modification 5815 has been embodied and no bolt larger than 7/16 -inch diameter is fitted | Within 33,000 flight cycles or 45,200 flight hours since embodiment of Airbus Modification 5815, whichever occurs first | Within 33,000 flight cycles or 45,200 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. |
| Model A300 B4-2C, and B4-203 airplanes on which Airbus Modification 5815 has been embodied and no bolt larger than 7/16 -inch diameter is fitted | Within 35,600 flight cycles or 48,800 flight hours since embodiment of Airbus Modification 5815, whichever occurs first | Within 33,000 flight cycles or 74,900 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. |
| Model A300 B2-1A, B2-1C, B2K-3C, B2-203 airplanes on which Airbus Modification 5815 has been embodied and at least one bolt with a 15/32 -inch diameter is fitted | Within 22,000 flight cycles or 24,800 flight hours since embodiment of Airbus Modification 5815, whichever occurs first | Within 22,000 flight cycles or 24,800 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. |
| Model A300 B4-103 airplanes on which Airbus Modification 5815 has been embodied and at least one bolt with a 15/32 -inch diameter is fitted | Within 22,000 flight cycles or 30,100 flight hours since embodiment of Airbus Modification 5815, whichever occurs first | Within 22,000 flight cycles or 30,100 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. |
| Model A300 B4-2C, and B4-203, airplanes on which Airbus Modification 5815 has been embodied and at least one bolt with a 15/32 -inch diameter is fitted | Within 23,700 flight cycles or 32,500 flight hours since embodiment of Airbus Modification 5815, whichever occurs first | Within 22,000 flight cycles or 49,900 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. |
| Airplane configuration | Compliance times for airplanes with an AFT of less than 1.5 | Compliance times for airplanes with an AFT of more than or equal to 1.5 |
|---|---|---|
| Model A300-600 series airplanes on which Airbus Modification 5815 and Airbus Modification 11133 have not been embodied | Within 16,200 flight cycles or 24,300 flight hours since first flight of the airplane, whichever occurs first | Within 15,000 flight cycles or 32,400 flight hours since first flight of the airplane, whichever occurs first. |
| Model A300-600 series airplanes on which Airbus Modification 5815 has been embodied and no bolt larger than 7/16 -inch diameter is fitted | Within 35,600 flight cycles or 53,400 flight hours since embodiment of Airbus Modification 5815, whichever occurs first | Within 33,000 flight cycles or 71,200 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. |
| Model A300-600 series airplanes on which Airbus Modification 5815 has been embodied and at least one bolt 15/32 -inch diameter is fitted | Within 23,700 flight cycles or 35,600 flight hours since embodiment of Airbus Modification 5815, whichever occurs first | Within 22,000 flight cycles or 47,500 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. |
| Model A300-600 series airplanes on which Airbus Modification 11133 has been embodied | Within 35,600 flight cycles or 53,400 flight hours since first flight, whichever occurs first | Within 33,000 flight cycles or 71,200 flight hours since first flight, whichever occurs first. |
| Airplane models | Repetitive interval (not to exceed) for airplanes with an AFT of less than 1.5 | Repetitive interval (not to exceed) for airplanes with an AFT equal to or more than 1.5 |
|---|---|---|
| A300 B2-1A, B2-1C, B2K-3C, B2-203 | 1,500 flight cycles or 1,600 flight hours, whichever occurs first | 1,500 flight cycles or 1,600 flight hours, whichever occurs first. |
| A300 B4-103 airplanes | 1,500 flight cycles or 2,000 flight hours, whichever occurs first | 1,500 flight cycles or 2,000 flight hours, whichever occurs first. |
| A300 B4-2C, and B4-203 | 1,600 flight cycles or 2,200 flight hours, whichever occurs first | 1,500 flight cycles or 3,400 flight hours, whichever occurs first. |
| A300-600 series airplanes | 1,600 flight cycles or 2,400 flight hours, whichever occurs first | 1,500 flight cycles or 3,200 flight hours, whichever occurs first. |
For the purpose of this AD, the AFT must be established as specified in paragraphs (m)(1), (m)(2), and (m)(3) of this AD.
(1) For the initial inspection, the average flight time is the total accumulated flight hours, counted from take-off to touch-down, divided by the total accumulated flight cycles at the effective date of this AD.
(2) For the first repeated inspection interval, the average flight time is the total accumulated flight hours divided by the total accumulated flight cycles at the time of the inspection threshold.
(3) For all inspection intervals onward, the average flight time is the flight hours divided by the flight cycles accumulated between the last two inspections.
If any crack is found during any inspection required by paragraph (l) of this AD: Before further flight, replace the flap beam using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). Replacement of the flap beam does not constitute terminating action for the inspections required by paragraph (l) of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
