Airworthiness Directive · Amendment 39-18823 · Fuselage
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2020-07-18. Comply with the one in force.
This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category; manufacturer serial numbers 4895, 4903, 4911, 4919, 4929, 4938, 4942, 4944, 4946, 4948, and 4951, 4956 through 5541 inclusive, 5544, 5547, 5550, 5551, 5553, 5556, 5559, 5561, 5562, 5563, 5565, 5566, 5570, 5572, 5576, and 5578.
(1) Airbus Model A318-112 airplanes.
(2) Airbus Model A319-111, -112, -115, -132, and -133 airplanes.
(3) Airbus Model A320-214, -232, and -233 airplanes.
(4) Airbus Model A321-211, -212, -213, -231, and -232 airplanes.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A318-112 airplanes, A319-111, -112, -115, -132, and -133 airplanes, A320-214, -232, and -233 airplanes, and A321-211, -212, - 213, -231, and -232 airplanes. This AD was prompted by a quality control review on the final assembly line, which determined that aluminum alloy with inadequate heat treatment had been delivered and used on several structural parts. This AD requires a one-time eddy current conductivity measurement of certain cabin, cargo compartment, and frame structural parts to determine if aluminum alloy with inadequate heat treatment was used, and replacement if necessary. We are issuing this AD to address the unsafe condition on these products.
Within 6 years since the date of issuance of the original certificate of airworthiness or the date of issuance of the original export certificate of airworthiness: Do a one-time eddy current conductivity measurement of the cabin, cargo compartment, and frame structural parts identified in the “Affected P/N (part number)” column of tables 1, 2, and 3 to paragraphs (g) and (i) of this AD to determine if aluminum alloy with inadequate heat treatment was used, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, except as required by paragraph (h) of this AD.
(1) For cabin structural parts: Airbus Service Bulletin A320-53-1292, dated July 23, 2015; including Appendixes 01 and 02, dated July 23, 2015.
(2) For cargo compartment structural parts: Airbus Service Bulletin A320-53-1293, dated July 30, 2015; including Appendixes 01 and 02, dated July 30, 2015.
(3) For frame structural parts: Airbus Service Bulletin A320-53-1294, dated July 23, 2015; including Appendixes 01 and 02, dated July 23, 2015.
| Affected P/N | Acceptable replacement P/N | Area |
|---|---|---|
| D2127245500000 | D2127245500000 | Cabin. |
| D2127247600200 | D2127247600200 | Cabin. |
| D2127247600300 | D2127247600300 | Cabin. |
| D2127399900200 | D2127399900200 | Cabin. |
| D2127399900300 | D2127399900300 | Cabin. |
| D2127698900800 | D2127698900800 | Cabin. |
| D2127698902400 | D2127698902400 | Cabin. |
| D2527075131200 | D2527075131251 | Cabin. |
| D2527075131300 | D2527075131351 | Cabin. |
| D2527075138000 | D2527075138000 | Cabin. |
| D2527075138100 | D2527075138100 | Cabin. |
| D2527075138200 | D2527075138200 | Cabin. |
| D2527075138300 | D2527075138300 | Cabin. |
| D2527075138600 | D2527075138651 | Cabin. |
| D2527075138800 | D2527075138851 | Cabin. |
| D2527240220600 | D2527240220651 | Cabin. |
| D2527240220700 | D2527240220751 | Cabin. |
| D2527240220800 | D2527240220851 | Cabin. |
| D9249591201000 | D9249591201000 | Cabin. |
| D9249591201800 | D9249591201800 | Cabin. |
| D9249591227800 | D9249591227851 | Cabin. |
| D9249591227900 | D9249591227951 | Cabin. |
| D9249591228000 | D9249591228051 | Cabin. |
| D9249591228100 | D9249591228151 | Cabin. |
| Affected P/N | Acceptable replacement P/N | Area |
|---|---|---|
| D2707033520000 | D2707033520000 | Cargo. |
| D2827027120000 | D2827027120000 | Cargo. |
| D2827093500400 | D2827093500400 | Cargo. |
| D2907013701200 | D2907013701251 | Cargo. |
| D2907013800400 | D2907013800451 | Cargo. |
| D3247012900000 | D3247012900051 | Cargo. |
| D3817003820000 | D3817003820000 | Cargo. |
| D3817012320200 | D3817012320251 | Cargo. |
| D3837021201600 | D3837021201600 | Cargo. |
| D3837033300400 | D3837033300400 | Cargo. |
| D4918518320200 | D4918518320200 | Cargo. |
| D5347043420400 | D5347043420451 | Cargo. |
| D9248511000000 | D9248511000051 | Cargo. |
| D9249254100200 | D9249254100251 | Cargo. |
| D9249282300000 | D9249282300000 | Cargo. |
| Affected P/N | Acceptable replacement P/N | Area |
|---|---|---|
| D2827098326800 | D2827098326851 | Frame. |
| D5347051620600 | D5347051620651 | Frame. |
| D5347051720600 | D5347051720651 | Frame. |
| D5347057120000 | D5347057120051 | Frame. |
| D5347067520600 | D5347067520651 | Frame. |
| D5347067521400 | D5347067521451 | Frame. |
| D5347067520800 | D5347067520851 | Frame. |
| D5347067521000 | D5347067521051 | Frame. |
| D5347067521600 | D5347067521651 | Frame. |
| D5347067620600 | D5347067620600 | Frame. |
| D5347067720200 | D5347067720251 | Frame. |
| D5347067720400 | D5347067720451 | Frame. |
| D5347986520200 | D5347986520251 | Frame. |
Where Subtask 531293-832-207-001 of Airbus Service Bulletin A320-53-1293, dated July 23, 2015; including Appendixes 01 and 02, dated July 23, 2015, specifies inspecting Item 19 of Figure A-GVAAA for material heat treatment conformity, and that figure (incorrectly) identifies the inspection area for Item 19 as the four hinge brackets adjacent to the A-profile, this AD requires inspecting part number D491-85183-202-00, which is the A-profile, and not just the brackets.
Note 1 to paragraph (h) of this AD: Airbus Technical Adaptation 80095365/011/2016, Issue 1, dated December 1, 2016 (“TA”) specifies that for Figure A-GVAAA, Sheet 01, of Airbus Service Bulletin A320-53-1293, dated July 30, 2015, Item 19 should point to part number D491-85183-202-00 (and not just to the brackets). The TA also specifies that for Figure A-GRAAA, Sheet 01, of Airbus Service Bulletin A320-53-1293, dated July 30, 2015, the correct Item 19 identification is part number D491-85183-202-00.
If during the measurement required by paragraph (g) of this AD, any affected part number specified in table 1, 2, or 3 to paragraphs (g) and (i) of this AD is found to have a measured value greater than that specified in Figure A-GFAAA, Sheet 01, “Inspection Flowchart,” of the applicable service information identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD: Before further flight, replace the affected part with the corresponding acceptable replacement part specified in table 1, 2, or 3 to paragraphs (g) and (i) of this AD, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD.
Although the service information identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD specifies to submit certain information to the manufacturer, this AD does not include that requirement.
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.
