AD 2015-25-06 Airworthiness Directives; Airbus Airplanes

Models named: A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, B4-2C, A310-203, -204, -221, -222. Read the applicability below — it usually turns on serial or part numbers too.

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.

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

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. Table 1 to Paragraph ( g ) of This AD—Compliance Times for Configuration 1 Airplanes 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. 1  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))). 2  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))). 3  “SR” applies to airplanes with average flights less than 4 flight hours. 4  “LR” refers to airplanes with average flights of 4 or more flight hours. (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).

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 AD replaces AD 2010-06-04, Amendment 39-16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572)).