Airworthiness Directive · Amendment 39-18659 · Nacelles/pylons
Airbus Airplanes
This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(6) of this AD, certificated in any category, except airplanes on which Airbus Modification 10149 has been incorporated in production.
(1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes.
(2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
(3) Airbus Model A300 B4-605R and B4-622R airplanes.
(4) Airbus Model A300 F4-605R airplanes.
(5) Airbus Model A300 C4-605R Variant F airplanes.
(6) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes.
We are superseding Airworthiness Directive (AD) 2000-10-18 for certain Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. AD 2000-10-18 required repetitive inspections to detect cracks in the lower spar of the engine pylons between ribs 6 and 7, and repair if necessary. This new AD reduces the compliance times for the initial inspection and the repetitive intervals. This AD was prompted by the determination that the compliance times for the initial inspection and the repetitive intervals must be reduced to allow timely detection of cracks in the engine pylon's lower spar between ribs 6 and 7. We are issuing this AD to detect and correct fatigue cracking, which could result in reduced structural integrity of the engine pylon's lower spar, and possible separation of the engine from the airplane.
Except as provided by paragraphs (i)(1) and (i)(2) of this AD, at the applicable time specified in paragraph 1.E., “Compliance,” of the applicable Airbus service bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD: Do an eddy current or liquid penetrant inspection for cracking of the engine pylon's lower spar between ribs 6 and 7; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of the applicable Airbus service bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD, except as required by paragraph (i)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection of the engine pylon's lower spar between ribs 6 and 7 thereafter at the applicable time and intervals specified in paragraph 1.E., “Compliance,” of the applicable Airbus service bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD until a repair or modification specified in the Accomplishment Instructions of the applicable Airbus service bulletin identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD is done.
(1) Airbus Service Bulletin A300-54-0073, Revision 03, dated October 11, 2012 (for Model A300 series airplanes).
Note 1 to paragraph (g)(1) of this AD: Airbus Service Bulletin A300-54-0080, Revision 02, dated July 9, 2002, is an additional source of guidance for accomplishing the modification specified in Airbus Service Bulletin A300-54-0073, Revision 03, dated October 11, 2012.
(2) Airbus Service Bulletin A300-54-6014, Revision 07, dated September 5, 2012 (for Model A300-600 series airplanes).
Note 2 to paragraph (g)(2) of this AD: Airbus Service Bulletin A300-54-6020, Revision 02, dated July 9, 2002, is an additional source of guidance for accomplishing the modification specified in Airbus Service Bulletin A300-54-6014, Revision 07, dated September 5, 2012.
(3) Airbus Service Bulletin A310-54-2017, Revision 06, dated October 3, 2012 (for Model A310 series airplanes).
Note 3 to paragraph (g)(3) of this AD: Airbus Service Bulletin A310-54-2023, Revision 03, dated July 9, 2002, is an additional source of guidance for accomplishing the modification specified in Airbus Service Bulletin A310-54-2017, Revision 06, dated October 3, 2012.
For airplanes on which any repair or modification specified in the Accomplishment Instructions of the applicable Airbus service bulletin identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD is done: Except as provided by paragraphs (i)(1) and (i)(2) of this AD, at the applicable time specified in paragraph 1.E., “Compliance,” of the applicable Airbus service bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD: Do an eddy current or liquid penetrant inspection for cracking of the engine pylon's lower spar between ribs 6 and 7; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of the applicable Airbus service bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD, except as required by paragraph (i)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection of the engine pylon's lower spar between ribs 6 and 7 thereafter at the applicable time and intervals specified in paragraph 1.E., “Compliance,” of the applicable Airbus service bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD.
(1) Where a “Threshold” is specified in paragraph 1.E., “Compliance,” of the service information specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, the “FC” and “FH” compliance times are total flight cycle and total flight hour compliance times, except that if a repair or service bulletin identified in paragraph 1.E., “Compliance,” of the service bulletins specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD has been done, the “FC” and “FH” compliance times are flight cycle and flight hour compliance times since the identified repair or service bulletin was done.
(2) Except as provided by paragraphs (i)(2)(i) and (i)(2)(ii) of this AD: For the “Grace period” specified in paragraph 1.E., “Compliance,” of the service information specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, operators must comply with the actions specified in paragraphs (g) and (h) of this AD, as applicable, at the later of the applicable times in the “Threshold” and “Grace Period” times specified in paragraph 1.E., “Compliance,” of the applicable service information, except the language “for aircraft that have already exceeded or are close to exceed[ing] the threshold or scheduled interval” does not apply.
(i) Where Airbus Service Bulletin A300-54-0073, Revision 03, dated October 11, 2012; and Airbus Service Bulletin A310-54-2017, Revision 06, dated October 3, 2012; specify a compliance time “... after receipt of this Inspection Service Bulletin without exceeding the requirements of previous issue of this ISB,” this AD requires compliance within the specified compliance time after the effective date of this AD.
(ii) Where Airbus Service Bulletin A300-54-6014, Revision 07, dated September 5, 2012, specifies a compliance time “... after receipt of this Inspection Service Bulletin without exceeding the requirements of previous issue of this SB,” this AD requires compliance within the specified compliance time after the effective date of this AD.
(3) If any crack is found during any inspection required by this AD and the applicable Airbus service bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD specifies to contact Airbus: Before further flight, repair the crack 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).
For the purpose of paragraphs (g) and (h) of this AD, the AFT must be established as specified in paragraphs (j)(1), (j)(2), and (j)(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 onwards, the average flight time is the flight hours divided by the flight cycles accumulated between the last two inspections.
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.
