Airworthiness Directive · Amendment 39-18344 · Nacelles/pylons
Airbus Airplanes
This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category.
(1) Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, and B4-2C airplanes, on which Airbus Modification 02434 has been embodied in production.
(2) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes, except those on which Airbus Modification 10432 has been embodied in production.
(3) Airbus Model A300 B4-601, B4-603, B4-605R, B4-620, B-622, and B4-622R airplanes, except those on which Airbus Modification 10432 has been embodied in production.
We are superseding Airworthiness Directive (AD) 2010-06-04, for certain Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, B4-2C airplanes; Model A310 series airplanes; Model A300 B4-600 series airplanes; and Model A300 B4-600R series airplanes. AD 2010-06-04 required repetitive inspections to detect cracks of the pylon side panels (upper section) at rib 8; and corrective actions if necessary. This new AD continues to require repetitive inspections for cracking of the pylons 1 and 2 side panels (upper section) at rib 8 with reduced compliance times, and corrective actions if necessary. This AD also requires repetitive post-repair and post-modification inspections and repair if necessary. This AD also removes certain airplanes having a certain modification from the applicability. This AD was prompted by reports of cracks found on pylon side panels at rib 8 and a fleet survey and updated fatigue and damage tolerance analyses. We are issuing this AD to detect and correct cracking of pylon side panels (upper section) at rib 8, which could lead to reduced structural integrity of the pylon primary structure, which could cause detachment of the engine from the fuselage.
This paragraph restates the requirements of paragraph (f) of AD 2010-06-04, Amendment 39-16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572)), with revised service information. Accomplishing the initial inspection required by paragraph (h) of this AD terminates the requirements of this paragraph.
(1) For Configuration 01 airplanes as identified in the applicable service bulletin identified in paragraph (g)(9) of this AD: At the applicable time specified in table 1 to paragraph (g) of this AD, except as required by paragraphs (g)(2) and (g)(3) of this AD, perform a detailed visual inspection of the pylons 1 and 2 side panels (upper section) at rib 8, in accordance with paragraph 3.B. of the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(9)(i) through (g)(9)(iii) of this AD or paragraphs (k)(1), (k)(2), or (k)(3) of this AD. Repeat the inspection at the time specified in table 1 to paragraph (g) of this AD.
| For Model— | That have accumulated— | Inspect before the accumulation of— | Or within— | And repeat the inspection at intervals not to exceed— |
|---|---|---|---|---|
| Whichever occurs later | ||||
| A300 B2-1C, B2-203, and B2K-3C airplanes | ≤17,500 total flight cycles 1 | 5,350 total flight cycles | 2,500 flight cycles 2 | 4,300 flight cycles. |
| A300 B2-1C, B2-203, and B2K-3C airplanes | >17,500 total flight cycles 1 | 20,000 total flight cycles or 40,000 total flight hours, whichever occurs first | 250 flight cycles 2 | 4,300 flight cycles. |
| A300 B4-103, B4-203, and B4-2C airplanes | ≤18,000 total flight cycles 1 | 5,350 total flight cycles | 2,000 flight cycles 2 | 4,300 flight cycles. |
| A300 B4-103, B4-203, and B4-2C airplanes | >18,000 total flight cycles 1 | 20,000 total flight cycles or 40,000 total flight hours, whichever occurs first | 250 flight cycles 2 | 4,300 flight cycles. |
| A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R airplanes | ≤18,000 total flight cycles 1 | 4,200 total flight cycles | 2,000 flight cycles 2 | 3,600 flight cycles. |
| A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R airplanes | >18,000 total flight cycles 1 | 20,000 total flight cycles or 40,000 total flight hours, whichever occurs first | 250 flight cycles 2 | 3,600 flight cycles. |
| A310-200 airplanes with GE CF6-80A3 or Pratt & Whitney engines | ≤18,000 total flight cycles 1 | 9,700 total flight cycles or 19,400 total flight hours, whichever occurs first | 1,500 flight cycles 2 | 6,700 flight cycles or 13,400 flight hours, whichever occurs first. |
| A310-200 airplanes with GE CF6-80A3 or Pratt & Whitney engines | >18,000 total flight cycles 1 | 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first | 250 flight cycles 2 | 6,700 flight cycles or 13,400 flight hours, whichever occurs first. |
| A310-200 airplanes with GE CF6-80C2 engines | ≤18,000 total flight cycles 1 | 7,800 total flight cycles or 15,600 total flight hours, whichever occurs first | 1,500 flight cycles 2 | 5,800 flight cycles or 11,600 flight hours, whichever occurs first. |
| A310-200 airplanes with GE CF6-80C2 engines | >18,000 total flight cycles 1 | 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first | 250 flight cycles 2 | 5,800 flight cycles or 11,600 flight hours, whichever occurs first. |
| A310-300 SR 3 airplanes with Pratt & Whitney JT9D engines | ≤18,000 total flight cycles 1 | 8,600 total flight cycles or 24,000 total flight hours, whichever occurs first | 1,500 flight cycles 2 | 6,700 flight cycles or 18,700 flight hours, whichever occurs first. |
| A310-300 SR 3 airplanes with Pratt & Whitney JT9D engines | >18,000 total flight cycles 1 | 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first | 250 flight cycles 2 | 6,700 flight cycles or 18,700 flight hours, whichever occurs first. |
| A310-300 SR 3 airplanes with GE engines | ≤18,000 total flight cycles 1 | 7,000 total flight cycles or 19,600 total flight hours, whichever occurs first | 1,500 flight cycles 2 | 5,700 flight cycles or 15,900 flight hours, whichever occurs first. |
| A310-300 SR 3 airplanes with GE engines | >18,000 total flight cycles 1 | 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first | 250 flight cycles 2 | 5,700 flight cycles or 15,900 flight hours, whichever occurs first. |
| A310-300 SR 3 airplanes with Pratt & Whitney 4000 engines | ≤18,000 total flight cycles 1 | 7,000 total flight cycles or 19,600 total flight hours, whichever occurs first | 1,500 flight cycles 2 | 5,800 flight cycles or 16,200 flight hours, whichever occurs first. |
| A310-300 SR 3 airplanes with Pratt & Whitney 4000 engines | >18,000 total flight cycles 1 | 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first | 250 flight cycles 2 | 5,800 flight cycles or 16,200 flight hours, whichever occurs first. |
| A310-300 LR 4 airplanes with Pratt & Whitney JT9D engines | ≤18,000 total flight cycles 1 | 5,900 total flight cycles or 29,500 total flight hours, whichever occurs first | 1,500 flight cycles 2 | 6,000 flight cycles or 30,300 flight hours, whichever occurs first. |
| A310-300 LR 4 airplanes with Pratt & Whitney JT9D engines | >18,000 total flight cycles 1 | 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first | 250 flight cycles 2 | 6,000 flight cycles or 30,300 flight hours, whichever occurs first. |
| A310-300 LR 4 airplanes with GE engines | ≤18,000 total flight cycles 1 | 4,800 total flight cycles or 24,100 total flight hours, whichever occurs first | 1,500 flight cycles 2 | 5,100 flight cycles or 25,500 flight hours, whichever occurs first. |
| A310-300 LR 4 airplanes with GE engines | >18,000 total flight cycles 1 | 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first | 250 flight cycles 2 | 5,100 flight cycles or 25,500 flight hours, whichever occurs first. |
| A310-300 LR 4 airplanes with Pratt & Whitney 4000 engines | ≤18,000 total flight cycles 1 | 4,800 total flight cycles or 24,000 total flight hours, whichever occurs first | 1,500 flight cycles 2 | 5,200 flight cycles or 26,300 flight hours, whichever occurs first. |
| A310-300 LR 4 airplanes with Pratt & Whitney 4000 engines | >18,000 total flight cycles 1 | 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first | 250 flight cycles 2 | 5,200 flight cycles or 26,300 flight hours, whichever occurs first. |
(2) For Model A300 and A300-600 airplanes that have accumulated more than 40,000 total flight hours as of April 15, 2010 (the effective date of AD 2010-06-04, Amendment 39-16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572))): Within 250 flight cycles after April 15, 2010, do the actions specified in paragraph (g)(1) of this AD.
(3) For Model A310 airplanes that have accumulated more than 55,500 total flight hours as of April 15, 2010 (the effective date of AD 2010-06-04, Amendment 39-16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572))): Within 250 flight cycles after April 15, 2010, do the actions specified in paragraph (g)(1) of this AD.
(4) For Configuration 01 airplanes, as identified in the applicable service bulletin identified in paragraph (g)(9) of this AD: If a crack is found during any inspection required by paragraph (g)(1) of this AD, before further flight, install a doubler, in accordance with paragraph 3.C. of the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(9) of this AD.
(5) For Configuration 02 airplanes, as identified in the applicable service bulletin identified in paragraph (g)(9) of this AD: At the applicable time specified in paragraph 1.E.(2) of the applicable service bulletin identified in paragraphs (g)(9)(i) through (g)(9)(iii) of this AD, or within 250 flight cycles after April 15, 2010 (the effective date of AD 2010-06-04, Amendment 39-16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572))), whichever occurs later, perform a detailed visual inspection of the pylons 1 and 2 side panels (upper section) at rib 8, in accordance with paragraph 3.B. of the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(9) of this AD.
(6) For Configuration 03 airplanes, as identified in the applicable service bulletin identified in paragraph (g)(9) of this AD: At the applicable time specified in paragraph 1.E.(2) of the applicable service bulletin identified in paragraphs (g)(9)(i) through (g)(9)(iii) of this AD, or within 250 flight cycles after April 15, 2010 (the effective date of AD 2010-06-04, Amendment 39-16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572))), whichever occurs later, perform a detailed visual inspection, and a high frequency eddy current inspection as applicable, of the pylons 1 and 2 side panels (upper section) at rib 8, in accordance with paragraph 3.B. of the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(9) of this AD.
(7) For Configuration 02 and 03 airplanes, as identified in the applicable service bulletin identified in paragraph (g)(9) of this AD: If a crack is found during any inspection required by paragraph (g)(1), (g)(5), or (g)(6) of this AD, before further flight, repair in accordance with paragraph 3.C. of the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(9) of this AD.
(8) For all airplanes, except those in Configuration 01, as identified in the applicable service bulletin identified in paragraph (g)(9) of this AD: Repeat the inspection specified in paragraph (g)(1), (g)(5), or (g)(6) of this AD, as applicable, at the intervals specified in paragraph 1.E.(2) of the applicable service bulletin identified in paragraph (g)(9)(i) through (g)(9)(iii) of this AD.
(9) For the actions specified in paragraph (g) of this AD, use the applicable service bulletin identified in paragraphs (g)(9)(i) through (g)(9)(iii) of this AD, or paragraph (k)(1), (k)(2), or (k)(3) of this AD.
(i) Airbus Mandatory Service Bulletin A300-54-0075, excluding Appendixes 1, 2, and 3, Revision 02, dated June 26, 2008 (For Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, and B4-2C airplanes).
(ii) Airbus Mandatory Service Bulletin A300-54-6015, excluding Appendixes 1, 2, and 3, Revision 02, dated June 26, 2008 (For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R airplanes).
(iii) Airbus Mandatory Service Bulletin A310-54-2018, excluding Appendixes 1, 2, and 3, Revision 02, dated June 26, 2008 (for Model A310 series airplanes).
Except as required by paragraphs (l)(1) and (l)(2) of this AD, at the applicable times specified in paragraph 1.E., “Compliance,” of the applicable service bulletin identified in paragraph (k) of this AD: Do a detailed inspection for cracking of the pylons 1 and 2 side panels (upper section) at rib 8, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (k) of this AD. Accomplishing the inspection required by this paragraph terminates the requirements of paragraph (g)(1) through (g)(9) of this AD.
(1) If any cracking is found, before further flight, do a high frequency eddy current (HFEC) inspection to confirm the crack, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (k) of this AD.
(i) If any crack indication is confirmed during the HFEC inspection specified in paragraph (h)(1) of this AD, and the crack is less than 20 mm, before further flight, repair, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (k) of this AD.
(ii) If any crack indication is confirmed during the HFEC inspection specified in paragraph (h)(1) of this AD and the crack is greater than or equal to 20 mm, before further flight, repair 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).
(2) If no cracking is found, or if crack indication is not confirmed during the HFEC inspection required by paragraph (h)(1) of this AD, at the applicable interval specified in paragraph 1.E., “Compliance,” of the applicable service bulletin identified in paragraph (k) of this AD, repeat the inspection specified in paragraph (h) of this AD, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (k) of this AD until the modification specified in paragraph (i) is done.
Modifying by installing a doubler on the left hand (LH) pylon 1 and right hand (RH) pylon 2, on pylon side panels (upper section), at rib 8, in accordance with the Accomplishment Instructions of the service information identified in paragraph (i)(1), (i)(2), or (i)(3) of this AD; as applicable; terminates the repetitive inspections specified in paragraph (h)(2) of this AD.
(1) Airbus Service Bulletin A300-54-0081, dated August 11, 1993.
(2) Airbus Service Bulletin A310-54-2024, dated August 11, 1993.
(3) Airbus Service Bulletin A300-54-6021, Revision 02, dated May 21, 2008.
For airplanes on which the modification has been done as specified in paragraph (i) of this AD, and airplanes on which the repair has been done as specified in paragraph (h) of this AD: At the applicable compliance time specified in paragraph 1.E., Compliance,” of the applicable service bulletin identified in paragraph (k) of this AD, do the post-modification and post-repair detailed inspections for cracking, as applicable, of the LH and RH side panels of pylons 1 and 2, in accordance with the applicable service bulletins identified in paragraph (k) of this AD. Repeat the inspections thereafter at the times specified in paragraph 1.E., “Compliance” of the applicable service bulletin specified in paragraph (k) of this AD. If any cracking is found, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. This repair is not a terminating action for the repetitive inspections required by this paragraph.
Use the applicable service bulletin identified in paragraphs (k)(1) through (k)(3) of this AD to accomplish the inspections required by paragraphs (g), (h), and (j) of this AD.
(1) Airbus Service Bulletin A300-54-0075, Revision 03, excluding Appendixes 1, 2, 3, and 5; including Appendix 4; dated March 27, 2013 (for Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, and B4-2C airplanes).
(2) Airbus Service Bulletin A310-54-2018, Revision 03, excluding Appendixes 1, 2, 3, and 5; including Appendix 4; dated April 11, 2013 (for Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes).
(3) Airbus Service Bulletin A300-54-6015, Revision 03, excluding Appendixes 1, 2, 3, and 5; including Appendix 4; dated April 11, 2013 (for Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R airplanes).
(1) Where the compliance time column in the tables in paragraph 1.E., “Compliance,” of the applicable service bulletin identified in paragraph (k) of this AD specifies a “threshold” in “FC” or “FH,” and does not specify from repair or service bulletin embodiment, those compliance times are total flight cycles and total flight hours.
(2) Where the tables in paragraph 1.E., “Compliance,” of the applicable service bulletin specified in paragraph (k) of this AD specifies “grace period after the receipt of the service bulletin,” this AD requires compliance within the corresponding compliance time after the effective date 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.
