Airworthiness Directive · Amendment 39-16769 · Fuselage
Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300-B4-103, A300 B4-203, and A300 B4-2C Airplanes
Superseded. A later AD replaced this one: AD 2016-25-15. Comply with the one in force.
This AD applies to Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300-B4-103, A300 B4-203, and A300 B4-2C airplanes; certificated in any category; serial numbers 0003 through 0156 inclusive.
We are superseding an existing airworthiness directive (AD) that applies to the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
For airplanes on which an eddy current inspection of the “special” areas of the longitudinal lap joints has not been done as of the effective date of this AD in accordance with Airbus Mandatory Service Bulletin A300-53-0211: Prior to the accumulation of 24,000 total flight cycles, or within 2,000 flight cycles after the effective date of this AD, whichever occurs later; do an eddy current inspection for cracking of the “special” areas of the longitudinal lap joints, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. If no cracking is found, repeat the inspection thereafter at the applicable intervals specified in Table 1 of this AD. If any crack is found during any inspection required by this paragraph, repair or modify before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006; and do the applicable inspection of the repaired or modified area in accordance with paragraph (k) of this AD. “Special” areas of the longitudinal lap joints are defined in Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006.
| For airplanes— | Inspect special area— | Repeat at intervals not to exceed— |
|---|---|---|
| All | STGR5 LH and RH (FR54 through FR58) | 3,600 flight cycles. |
| All | STGR22 LH and RH (FR26 through FR40) | 2,700 flight cycles. |
| All | STGR22 RH (FR58 through FR65) | 3,000 flight cycles. |
| All | STGR31 LH/RH (FR26 through FR39) | 3,000 flight cycles. |
| MSN 0003 | STGR31 LH/RH (FR54 through FR58) | 3,600 flight cycles. |
(h) For airplanes on which an eddy current inspection of the “special” areas of the longitudinal lap joints has been done before the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211; except for airplanes on which a repair or modification of the “special” areas has been done in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211: Do the next inspection of the “special” areas of the longitudinal lap joints at the earlier of the times specified in paragraphs (h)(1) and (h)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. If no cracking is found, repeat the inspection thereafter at the applicable intervals specified in Table 2 of this AD. If any crack is found during any inspection required by this paragraph, repair or modify before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006, and do the applicable inspection of the repaired or modified area in accordance with paragraph (k) of this AD. “Special” areas of the longitudinal lap joints are defined in Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006.
(1) Within 6,000 flight cycles after doing the last inspection of the “special” areas of the longitudinal lap joints, in accordance with Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006.
(2) Within the applicable intervals specified in Table 2 of this AD, or within 60 days after the effective date of this AD, whichever occurs later.
| For airplanes— | Inspect special area— | Repeat at intervals not to exceed— |
|---|---|---|
| All | STGR5 LH and RH (FR54 through FR58) | 3,600 flight cycles. |
| All | STGR22 LH and RH (FR26 through FR40) | 2,700 flight cycles. |
| All | STGR22 RH (FR58 through FR65) | 3,000 flight cycles. |
| All | STGR31 LH/RH (FR26 through FR39) | 3,000 flight cycles. |
| MSN 0003 | STGR31 LH/RH (FR54 through FR58) | 3,600 flight cycles. |
(i) For airplanes on which an eddy current inspection of the “standard” areas of the longitudinal lap joints has not been done before the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211: At the applicable time specified in Tables 3 and 4 of this AD, do an eddy current inspection for cracking of the longitudinal lap joints in the “standard” areas, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. Repeat the inspection thereafter at the applicable intervals specified in Tables 3 and 4 of this AD. If any crack is found during any inspection required by this paragraph, repair or modify before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006, and do the applicable inspection of the applicable area specified in Tables 3 and 4 of this AD. “Standard” areas of the longitudinal lap joints are defined in Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006.
| For airplanes— | Before the accumulation of— | Inspect standard area— | Repeat at intervals not to exceed— |
|---|---|---|---|
| All | 32,000 total flight cycles | STGR5, 13, 22 LH and RH, STGR31 LH (FR18 through FR26) | 3,600 flight cycles. |
| All | 32,000 total flight cycles | STGR27 RH, STGR39 RH (FR18 through FR20A, FR25A, FR26) | 8,000 flight cycles. |
| All | 32,000 total flight cycles | STGR43 LH, STGR46 RH, STGR51 LH (FR19 through FR26) | 5,700 flight cycles. |
| All | 32,000 total flight cycles | STGR5 LH/RH (FR26 through FR40); STGR11 LH/RH (FR27 through FR32); STGR13 LH/RH (FR 26 through FR28, FR31 through FR40); STGR27 LH/RH (FR 27 through FR32); STGR43 LH/RH (FR 26 through FR39); STGR49 RH (FR26 through FR39) | 3,000 flight cycles. |
| All | 32,000 total flight cycles | STGR47 LH (FR26 through FR39) | 5,700 flight cycles. |
| All | 32,000 total flight cycles | STGR5, 13, 22 LH/RH (FR40 through FR54) | 5,000 flight cycles. |
| All except MSN 0003 | 32,000 total flight cycles | STGR13, 44, 52 LH/RH (FR54 through FR58); STGR22 LH/RH (FR54, FR55); STGR31 LH/RH (FR54 through FR58) | 3,600 flight cycles. |
(j) For airplanes on which an eddy current inspection of the “standard” areas of the longitudinal lap joints has been done as of the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211; except for airplanes on which a repair or modification of the “standard areas” has been done in accordance with Airbus Mandatory Service Bulletin A300-53-0211: Do the next inspection of the “standard” areas of the longitudinal lap joints at the earlier of the times specified in paragraphs (j)(1) and (j)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. Thereafter, if no cracking is found, repeat the inspection at the applicable intervals specified in Tables 3 and 4 of this AD. If any crack is found during any inspection required by this paragraph, repair or modify before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006, and do the applicable inspection of the repaired or modified area in accordance with paragraph (k) of this AD. “Standard” areas of the longitudinal lap joints are defined in Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006.
| For airplanes— | Before the accumulation of— | Inspect standard area— | Repeat at intervals not to exceed— |
|---|---|---|---|
| Pre-Mod 1398 | 32,000 total flight cycles | STGR5, 13 LH/RH 22 LH (FR58 through FR65); STGR31 LH (FR58 through FR72); STGR31 RH (FR65 through FR72) | 2,700 flight cycles. |
| All | 32,000 total flight cycles | STGR27 RH, STGR39 RH (FR58, FR59A, FR63A through FR65) | 8,000 flight cycles. |
| Post-Mod 1398 | 32,000 total flight cycles | STGR5, 13 LH/RH 22 LH (FR58 through FR65); STGR31 LH (FR58 through FR72); STGR 31 RH (FR65 through FR72) | 3,000 flight cycles. |
| Pre-Mod 1398 | 32,000 total flight cycles | STGR5, 13, 22 LH/RH (FR65 through FR72) | 2,300 flight cycles. |
| Post-Mod 1398 | 32,000 total flight cycles | STGR5, 13, 22 LH/RH (FR65 through FR72) | 3,000 flight cycles. |
| All | 32,000 total flight cycles | STGR44 LH (FR58 through FR72); STGR52 LH/RH (FR58 through FR65); STGR47 RH (FR58 through FR72); STGR57 LH (FR65 through FR72) | 3,000 flight cycles. |
| All | 24,000 total flight cycles | STGR22 RH (FR58 through FR65) | 3,000 flight cycles. |
| All | 32,000 total flight cycles | STGR6 LH/RH (FR72 through FR80); STGR24 LH/RH (FR76 through FR80) | 3,000 flight cycles. |
| All | 32,000 total flight cycles | STRG17 LH/RH (FR76 through FR80); STGR29 LH/RH (FR72 through FR76); STGR35 LH/RH (FR72 through FR80) | 5,700 flight cycles. |
| All | 27,000 total flight cycles | STGR51 LH/RH (FR72 through FR80) | 5,700 flight cycles. |
(1) Within the applicable time in paragraph (j)(1)(i) or (j)(1)(ii) of this AD after doing the last inspection of the “standard” areas of the longitudinal lap joints in accordance with Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006.
(i) For longitudinal lap joints with bonded doublers: 6,000 flight cycles.
(ii) For longitudinal lap joints without bonded doublers: 8,000 flight cycles.
(2) Within the applicable time specified in Tables 3 or 4 of this AD, or within 60 days after the effective date of this AD, whichever occurs later.
For airplanes on which a repair or modification has been done in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211: At the applicable initial inspection time specified in Table 5 of this AD, do an eddy current inspection for cracking of the repaired or modified areas, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. If no cracking is found, repeat the inspection thereafter at the applicable intervals specified in Table 5 of this AD. If any crack is found during any inspection required by this paragraph, repair or modify before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006.
| Repair or retrofit solution/area—as identified in Airbus Mandatory Service Bulletin A300-53-0211— | Initial inspection after repair or retrofit— | Follow-up inspections at intervals not to exceed— |
|---|---|---|
| Repair 1: (Without cut out) also applicable to the solution with removed inner doubler | Skin/doubler thickness | |
| • < 1 inch: 10,000 flight cycles after repair | 1,000 flight cycles. | |
| • ≥ 1 inch and < 2 inch: 30,000 flight cycles after repair | 2,000 flight cycles. | |
| • ≥ 2 inch: 60,000 flight cycles after repair | 6,400 flight cycles. | |
| Repair 4 (With cut out) | Within 32,000 flight cycles after repair | 5,000 flight cycles. |
| Repair 4A (With cut out) | Within 24,000 flight cycles after repair | 5,300 flight cycles. |
| Repair 7 (MSN 0095 at STGR52 LH in Section 16) | Within 37,000 flight cycles after repair | 12,000 flight cycles. |
| Repair 9 (MSN 0073 and 0095 STGR44 LH/RH in Sections 16 and 17) | Within 36,000 flight cycles after repair | 5,000 flight cycles. |
| Repair 10 (Post-repair inspections in Figure 13) | Within 20,000 flight cycles after repair | 11,000 flight cycles. |
| Repair 2 (With cut out) | Within 24,000 flight cycles after repair | 5,300 flight cycles. |
| Repair 3 (Without cut out) | Within 24,000 flight cycles after repair | 5,300 flight cycles. |
| Retrofit 1 (Retrofit lap joint) | Within 32,000 flight cycles after retrofit | 5,000 flight cycles. |
| Retrofit 2 Retrofit lower shell (4 panel solution) STGR43 LH (FR26 through FR39), STGR43 RH (FR26 through FR38), and STGR49 RH (FR26 through FR38) | Within 32,000 flight cycles after retrofit | 3,000 flight cycles. |
| Retrofit 2 Retrofit lower shell (4 panel solution) STGR46 RH (FR19 through FR26), and STGR47 LH (FR26 through FR39), and STGR51 LH (FR19 through FR26) | Within 32,000 flight cycles after retrofit | 5,700 flight cycles. |
| Retrofit 3 Retrofit lower shell (3 panel solution) STGR43 LH (FR26 through FR39), and STGR43 RH (FR26 through FR38) | Within 32,000 flight cycles after retrofit | 3,000 flight cycles. |
| Retrofit 3 Retrofit lower shell (3 panel solution) STGR46 RH (FR19 through FR26), and STGR51 LH (FR19 through FR26), and STGR54 LH (FR26 through FR39) | Within 32,000 flight cycles after retrofit | 5,700 flight cycles. |
| Retrofit 3A (STGR43 LH/RH between FR37 and FR39 in Section 14) | Within 32,000 flight cycles after retrofit | 5,000 flight cycles. |
| Retrofit 4 (Retrofit lap joint without cut out) | Within 42,000 flight cycles after retrofit | 5,000 flight cycles. |
| Retrofit 5 (Retrofit lap joint) | Within 42,000 flight cycles after retrofit | 5,000 flight cycles. |
| Retrofit 6 (Retrofit lap joint) | Within 34,000 flight cycles after retrofit | 12,000 flight cycles. |
| Retrofit 7 (Retrofit lap joint) | Within 47,600 flight cycles after retrofit | 5,400 flight cycles. |
For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 13 through 18 (except Sections 16 and 17 at Stringer 31 left-hand and right-hand) for disbonding and cracking have not been done as of the effective date of this AD in accordance with Airbus Service Bulletin A300-53-229: Prior to the accumulation of 24,000 total flight cycles or within 15 years since new, whichever occurs first; or within 60 days after the effective date of this AD; whichever occurs later, do a detailed inspection of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 13 through 18 (except Sections 16 and 17 at Stringer 31 left-hand and right-hand) for disbonding and cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and no cracking is found, repeat the inspection thereafter at the applicable intervals specified in Table 6 of this AD.
| For area— | Inspect at intervals not to exceed— |
|---|---|
| Sections 13 and 14 as specified in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997 | Within 7 years or 12,000 flight cycles after doing the inspection, whichever occurs first. |
| Sections 15 through 18 as specified in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997 | Within 8.5 years or 12,000 flight cycles after doing the inspection, whichever occurs first. |
(1) If no cracking is found and “minor” disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22.
(2) If no cracking is found and “major” disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997.
(3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997.
(m) For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 13 through 18 (except Sections 16 and 17 at Stringer 31 left-hand and right-hand) for disbonding and cracking have been done as of the effective date of this AD in accordance with Airbus Service Bulletin A300-53-229; except for airplanes on which a repair of that area has been done in accordance with Airbus Service Bulletin A300-53-229: At the applicable time specified in Table 6 of this AD, or within 60 days after the effective date of this AD, whichever occurs later, do a detailed inspection of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 13 through 18 (except Sections 16 and 17 at Stringer 31 left-hand and right-hand) for disbonding and cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and no cracking is found, repeat the inspection at the applicable intervals specified in Table 6 of this AD.
(1) If no cracking is found and “minor” disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22.
(2) If no cracking is found and “major” disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997.
(3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997.
(n) For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 16 and 17 at Stringer 31 left-hand and right-hand for disbonding and cracking have not been done as of the effective date of this AD in accordance with Airbus Service Bulletin A300-53-229: Prior to the accumulation of 24,000 total flight cycles or within 12 years since new, whichever occurs first; or within 60 days after the effective date of this AD; whichever occurs later, do a detailed inspection of the fuselage bonded inner doubles of the longitudinal lap joints in Sections 16 and 17 at Stringer 31 left-hand and right-hand for disbonding and cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and no cracking is found, repeat the inspection thereafter at intervals not to exceed 7 years or 12,000 flight cycles, whichever occurs first.
(1) If no cracking is found and “minor” disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22. Doing a repair in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, terminates the repetitive inspections required by this paragraph for that area.
(2) If no cracking is found and “major” disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997.
(3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997.
(o) For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 16 and 17 at Stringer 31 left-hand and right-hand for disbonding and cracking have been done as of the effective date of this AD in accordance with Airbus Service Bulletin A300-53-229; except airplanes on which a repair of that area has been done in accordance with Airbus Service Bulletin A300-53-229: Within 7 years or 12,000 flight cycles after doing the inspection, whichever occurs first; or within 60 days after the effective date of this AD; whichever occurs later, do a detailed inspection of the fuselage bonded inner doubles of the longitudinal lap joints in Sections 16 and 17 at Stringer 31 left-hand and right-hand for disbonding and cracking in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and corrosion are found, repeat the inspection thereafter at intervals not to exceed 7 years or 12,000 flight cycles, whichever occurs first.
(1) If no cracking is found and “minor” disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22. Doing a repair in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, terminates the repetitive inspections required by this paragraph for that area.
(2) If no cracking is found and “major” disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997.
(3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997.
(p) Although Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997; and Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006; specify to submit certain information to the manufacturer, this AD does not include that requirement.
Note 1: This AD differs from the MCAI and/or service information as follows: (1) Although the MCAI or service information allows further flight after cracks are found during compliance with the required action, this AD requires that you repair the crack(s) before further flight. (2) The MCAI or service information does not include enforceable compliance times for certain actions; however, this AD requires that those actions be done at the enforceable times specified in this AD. (3) Although the MCAI or service information tells you to submit information to the manufacturer, paragraph (p) of this AD specifies that such submittal is not required.
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.
