Airworthiness Directive · Amendment 39-14684 · Airbus Model A300 B2 and B4 Series Airplanes; and Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)
Airbus Model A300 B2 and B4 Series Airplanes; and Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)
This AD applies to Airbus airplanes identified in Table 1 of this AD, certificated in any category.
| Affected Airbus Airplanes |
| (1) All Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes. |
| (2) All Model A300 B4-2C, B4-103, and B4-203 airplanes. |
| (3) All Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes. |
| (4) All Model A300 B4-605R and B4-622R airplanes. |
| (5) All Model A300 F4-605R and F4-622R airplanes. |
| (6) All Model A300 C4-605R Variant F airplanes. |
The FAA is superseding two existing airworthiness directives (AD) that apply to certain Airbus Model A300 B2, A300 B4, and A300-600 series airplanes. One AD currently requires an inspection for cracks of the lower outboard flange of gantry No. 4 in the main landing gear (MLG) bay area, and repair if necessary. The other AD currently requires, among other actions, repetitive inspections of the gantry lower flanges, and repair if necessary. This new AD requires new repetitive inspections for cracks in the lower flange of certain gantries, and repair if necessary, which ends the existing inspection requirements. This new AD also provides for optional terminating actions for the new repetitive inspections. This AD results from a report of a large fatigue crack along the outboard flange of beam No. 4 and a subsequent determination that existing inspections are inadequate. We are issuing this AD to detect and correct fatigue cracks in the lower flanges of gantries 1 through 5 inclusive in the MLG bay area, which could result in reduced structural integrity of the fuselage, and consequent rapid decompression of the airplane.
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 Airbus Modification 10147 has not been done: At the later of the times specified in paragraphs (f)(1) and (f)(2) of this AD: Do a one-time detailed inspection for cracking of the lower outboard flange of gantry No. 4 in the MLG bay area per paragraph 4.2.1 of Airbus All Operators Telex (AOT) A300-53A0371, Revision 01 (for Model A300 B2 and B4 series airplanes); or AOT A300-53A6145, Revision 01 (for Model A300-600 series airplanes); both dated September 10, 2003; as applicable.
(1) Before the accumulation of 8,000 total flight cycles since the date of issuance of the original Airworthiness Certificate or the date of issuance of the Export Certificate of Airworthiness, whichever is first.
(2) Within 30 days after January 22, 2004 (the effective date AD 2003-26-10).
Note 1: For the purposes of this AD, a detailed inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.”
Repair any cracking found during the inspection required by paragraph (f) of this AD before further flight, per a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent); or the European Aviation Safety Agency (EASA) (or its delegate agent).
For Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes, and Model A300 B4-2C, B4-103, and B4-203 airplanes, on which Airbus Modification 3474 has been done: Prior to the accumulation of 16,300 total flight cycles, or within 500 flight cycles after July 30, 1998 (the effective date of AD 98-13-37), whichever occurs later, perform a one-time ultrasonic inspection for cracking of the gantry lower flanges in the MLG bay area, in accordance with Airbus AOT 53-11, dated October 13, 1997.
(1) If any cracking is detected, prior to further flight, repair in accordance with the AOT.
(2) If no cracking is detected, no further action is required by this paragraph.
(i) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622R, C4-605R Variant F airplanes, and F4-605R airplanes, on which Airbus Modification 12169 has not been done in production: Perform the requirements of paragraphs (i)(1), (i)(2), (i)(3), and (i)(4) of this AD, in accordance with Airbus Service Bulletin A300-53-6128, dated March 5, 2001.
(1) At the later of the times specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD, perform initial ultrasonic inspections or high-frequency eddy current (HFEC) inspections for cracks of the lower flanges of gantries 3, 4, and 5 between fuselage frames FR47 and FR54, in accordance with the Accomplishment Instructions, including the Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive, of the service bulletin.
(i) In accordance with the thresholds specified in the Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive, of the service bulletin; or
(ii) Within 200 flight cycles after October 19, 2004 (the effective date AD 2004-18-13).
(2) Perform repetitive ultrasonic inspections or high-frequency eddy current inspections for cracks of the lower flanges of gantries 3, 4, and 5 between fuselage frames FR47 and FR54, in accordance with the thresholds and Accomplishment Instructions, including the Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive, of the service bulletin.
(3) Perform repairs and reinforcements, in accordance with the thresholds and the Accomplishment Instructions, including the Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive, of the service bulletin, except as specified in paragraph (i)(4) of this AD.
(4) If a new crack is found during any action required by paragraph (i)(1), (i)(2) or (i)(3) of this AD and the Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive, of the service bulletin specifies to contact Airbus for appropriate action: Prior to further flight, repair per a method approved by the Manager, International Branch, ANM-116; the DGAC (or its delegated agent); or the European Aviation Safety Agency (EASA) (or its delegate agent).
Any inspection accomplished before October 19, 2004, in accordance with Airbus AOT 53-11, dated October 13, 1997, is acceptable for compliance with the corresponding inspection specified in paragraph (i)(1) of this AD, for that inspection area only. Operators must do the applicable inspections in paragraph (i)(1) of this AD for the remaining inspection areas.
At the later of the applicable times specified in the “Threshold (FC)” and “Grace Period” columns of Tables 1 and 2 in paragraph 1.E of the applicable service bulletin in Table 2 of this AD: Do an ultrasonic inspection or HFEC inspection, including rework of the pressure diaphragm, for cracks in the lower flanges of the left and right gantries 1 through 5 inclusive between FR47 and FR54, in accordance with the Accomplishment Instructions of the applicable service bulletin in Table 2 of this AD. Repeat the inspection at the applicable times specified in the “Interval (FC)” column of Tables 1 and 2 in paragraph 1.E of the applicable service bulletin in Table 2 of this AD. Accomplishment of the initial inspection ends the inspections required by paragraphs (f), (h), and (i) of this AD.
| Airbus Service Bulletin— | For airplanes identified in— |
|---|---|
| (1) A300-53-0379, Revision 01, dated October 4, 2005 | Paragraphs (c)(1) and (c)(2) of this AD inclusive. |
| (2) A300-53-6152, Revision 01, dated October 4, 2005 | Paragraphs (c)(3) through (c)(6) of this AD inclusive. |
If any crack is detected during any ultrasonic or HFEC inspection required by paragraph (k) of this AD, before further flight, repair the crack in accordance with the Accomplishment Instructions of the applicable service bulletin in Table 2 of this AD, except as provided by paragraph (n) of this AD.
Accomplishment of the actions specified in Table 3 of this AD ends the repetitive inspections required by paragraph (k) of this AD.
| Before or at the same time with— | Reinforce— | By doing all the actions in accordance with the Accomplishment Instructions of— | For airplanes identified in— |
|---|---|---|---|
| (1) The actions required by paragraph (k) of this AD and the action specified in paragraph (m)(2) of this AD | The flanges of the left and right portals 1 through 5 inclusive between FR47 and FR54 of the landing gear, including a rotating probe inspection for cracks of holes and repair if necessary | Airbus Service Bulletin A300-53-0380, dated August 5, 2005, except as provided by paragraph (n) of this AD | Paragraphs (c)(1) and (c)(2) of this AD inclusive. |
| Airbus Service Bulletin A300-53-6153, dated August 24, 2005, except as provided by paragraph (n) of this AD | Paragraphs (c)(3) through (c)(6) of this AD inclusive. | ||
| (2) The actions required by paragraph (k) of this AD | Portals 3, 4, and 5 of the plates/skin | Airbus Service Bulletin A300-53-0360, Revision 01, dated May 31, 2006, except as provided by paragraph (n) of this AD | Paragraphs (c)(1) and (c)(2) of this AD inclusive. |
| Airbus Service Bulletin A300-53-6132, Revision 01, dated June 7, 2006, except as provided by paragraph (n) of this AD | Paragraphs (c)(3) through (c)(6) of this AD inclusive. |
Where the applicable service bulletin recommends contacting Airbus for appropriate action: Before further flight, repair the crack in accordance with a method approved by the Manager, International Branch, ANM-116; the DGAC (or its delegated agent); or the European Aviation Safety Agency (EASA) (or its delegate agent).
Accomplishing the inspections and repair before the effective date of this AD in accordance with Airbus Service Bulletin A300-53-0379, dated May 9, 2005; or Airbus Service Bulletin A300-53-6152, dated May 9, 2005; as applicable; is acceptable for compliance with the corresponding requirements of paragraphs (k) and (l) of this AD.
(p) Accomplishing the reinforcement before the effective date of this AD in accordance with Airbus Service Bulletin A300-53-0360, dated May 3, 2002; and Airbus Service Bulletin A300-53-6132, dated February 5, 2002; is acceptable for compliance with the corresponding requirements of paragraph (m)(2) of this AD.
Although the service bulletins in this AD specify 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.
