Airworthiness Directive · Amendment 39-19130 · Fuel system
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2020-21-05. Comply with the one in force.
This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(7) of this AD, certificated in any category, all manufacturer serial numbers.
(1) Model A330-223F and -243F airplanes.
(2) Model A330-201, -202, -203, -223, and -243 airplanes.
(3) Model A330-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
(4) Model A340-211, -212, and -213 airplanes.
(5) Model A340-311, -312, and -313 airplanes.
(6) Model A340-541 airplanes.
(7) Model A340-642 airplanes.
We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200, A330-200 Freighter, and A330-300 series airplanes; and Airbus Model A340-200, A340-300, A340-500, and A340-600 series airplanes. This AD requires repetitive inspections of certain fuel pumps for cavitation erosion, corrective action if necessary, and revision of the minimum equipment list (MEL). This AD was prompted by a report indicating that a fuel pump showing cavitation erosion breached the fuel pump housing and exposed the fuel pump power supply wires. We are issuing this AD to address the unsafe condition on these products.
(1) For the purpose of this AD, an affected fuel pump has part number (P/N) 568-1-28300-101, P/N 568-1-28300-103, or P/N 568-1-28300-200, and is located at one of the positions specified in paragraph 3.3 of Airbus Alert Operators Transmission (AOT) A28L006-17, Rev. 00, dated November 3, 2017.
(2) A fuel pump having P/N 568-1-28300-101, P/N 568-1-28300-103, or P/N 568-1-28300-200 that is installed in locations other than those specified in paragraph 3.3 of Airbus AOT A28L006-17, Rev. 00, dated November 3, 2017, is not affected by the inspection requirements of paragraph (i) of this AD.
For the purpose of this AD, airplane groups are designated as specified in paragraphs (h)(1) and (h)(2) of this AD.
(1) Group 1 airplanes are equipped with an affected fuel pump.
(2) Group 2 airplanes are not equipped with an affected fuel pump.
For Group 1 airplanes: Before an affected pump exceeds 10,000 flight hours since first installation on an airplane, or the applicable time specified in paragraph (i)(1) or (i)(2) of this AD, whichever occurs later, inspect all affected fuel pumps for cavitation erosion, in accordance with the instruction of Airbus AOT A28L006-17, Rev. 00, dated November 3, 2017. Repeat the inspection thereafter at intervals not to exceed the applicable time specified in table 1 to paragraph (i) of this AD.
(1) For a center tank, rear center tank, or aft transfer fuel pump: Within 30 days after the effective date of this AD.
(2) For a stand-by fuel pump: Within 40 days after the effective date of this AD.
| Erosion—as defined in the AOT | Inspection interval in flight hours |
|---|---|
| No erosion | 5,000 |
| Case 1: Light erosion | 5,000 |
| Case 2: Medium erosion | 800 |
If, during any inspection required by paragraph (i) of this AD, severe erosion (Case 3), as specified in Airbus AOT A28L006-17, Rev. 00, dated November 3, 2017, is found on a fuel pump: Before further flight, replace that fuel pump with a serviceable part, or deactivate that fuel pump as specified in the minimum equipment list (MEL), in accordance with the instructions of Airbus AOT A28L006-17, Rev. 00, dated November 3, 2017.
(1) As of the effective date of this AD, a fuel pump having P/N 568-1-28300-101, P/N 568-1-28300-103, or P/N 568-1-28300-200 may be installed on an airplane, provided that the part is new, or, prior to installation, the part has passed the inspection (no erosion or Case 1: Light erosion) required by paragraph (i) of this AD and, following installation, the part is inspected within the applicable repetitive intervals and as required by paragraph (i) of this AD.
(2) As of the effective date of this AD, a fuel pump having P/N 568-1-28300-101, P/N 568-1-28300-103, or P/N 568-1-28300-200, with Case 2 (medium erosion), as specified in Airbus AOT A28L006-17, Rev. 00, dated November 3, 2017, may be installed on an airplane provided the fuel pump is not installed at a location specified in paragraph 3.3 of Airbus AOT A28L006-17, Rev. 00, dated November 3, 2017.
(1) Within 30 days after the effective date of this AD, revise the applicable MEL, in accordance with the instructions of Airbus AOT A28L006-17, Rev. 00, dated November 3, 2017, and thereafter operate the airplane accordingly.
(2) For Model A340-500 and A340-600 airplanes: In addition to the MEL revision required by paragraph (l)(1) of this AD, revise the applicable MEL to include the information specified in table 2 to paragraph (l)(2) of this AD, and thereafter operate the airplane accordingly.
| Applicability | MEL amendment |
|---|---|
| Model A340-500 and A340-600 series airplanes | MEL Items 28-27-06 and 28-27-07 can be applied, provided that the related circuit breaker is pulled and tagged for the duration of the MEL item. |
At the applicable time specified in paragraph (m)(1) or (m)(2) of this AD: Report the results (including no findings) of each inspection required by paragraph (i) of this AD to inspection.results@airbus.com, in accordance with the instructions in Airbus AOT A28L006-17, Rev. 00, dated November 3, 2017.
(1) If the inspection was done on or before the effective date of this AD: Report within 10 days after the effective date of this AD.
(2) If the inspection was done after the effective date of this AD: Report within 10 days after the inspection.
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.
Aircraft
