Airworthiness Directive · Amendment 39-12015 · Airbus Model A319, A320, and A321 Series Airplanes
Airbus Model A319, A320, and A321 Series Airplanes
All Model A319, A320, and A321 series airplanes; certificated in any category.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance per paragraph (f) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A319, A320, and A321 series airplanes, that requires a revision to the Airplane Flight Manual; inspection to detect damage of the wiring and adjacent structure along the length of the fairing of the fuel boost pump; corrective actions, if necessary; and modification of the fuel pump wire and fairing. The actions specified by this AD are intended to prevent electrical arcing of the fuel boost pump wire, which could result in wing structural damage, fire, and/or fuel vapor explosion. This action is intended to address the identified unsafe condition.
To prevent electrical arcing of the fuel boost pump wire, which could result in wing structural damage, or fire and/or fuel vapor explosion, accomplish the following:
(a) Within 10 days after the effective date of this AD, revise the Limitations Section of the FAA-approved AFM to include the following which may be accomplished by inserting a copy of this AD or Airbus Temporary Revision 2.04.00/31 into the AFM:
“FUEL SYSTEM
If circuit breaker 1QA, 2QA, 7QA, and 8QA for any wing tank fuel boost pump is tripped, do not reset.”
(b) Within 90 days after the effective date of this AD: For each fuel boost pump, remove the rear and intermediate fairings located on the lower wing skin and perform a detailed visual inspection of the wiring and the adjacent structure along the length of the fairings. Inspect to detect damage to the wires including chafed, pinched, or melted wires, and any signs of arcing damage to the structure. When replacing the fairing following the inspection, take care not to pinch or otherwise damage the wiring of the fuel boost pumps; incorrect replacement of the fairing could cause damage to the wiring.
(1) If any damage to the wire, as described in paragraph (b) of this AD, is detected: Prior to further flight, either repair the wire or replace the wire with new wire per the manufacturer's Aircraft Wiring Manual, Standard Practices, Chapter 20. Submit a report at the time specified and per paragraph (d) of this AD.
(2) If any arcing damage to the structure is detected: Prior to further flight, repair the damaged structure per the airplane Structural Repair Manual or a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Ge ne rale de l'Aviation Civile (DGAC), which is the airworthiness authority for France (or its delegated agent). For a repair method to be approved by the Manager, International Branch, ANM-116, as required by this paragraph, the Manager's approval letter must specifically reference this AD. Submit a report at the time specified and per paragraph (d) of this AD.
Note 2: For the purposes of this AD, a detailed visual 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.”
(c) As of the effective date of this AD: For any fuel boost pump on which circuit breaker 1QA, 2QA, 7QA, and 8QA of the pump has tripped, prior to further use of that pump, accomplish the inspection and applicable corrective actions specified by paragraph (b) of this AD.
(d) If any damage is detected during any inspection required by paragraphs (b) and (c) of this AD: Within 10 days after accomplishing that inspection, submit a report of the inspection findings to the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; fax (425) 227-1149. The report must include a description of the damage found, the airplane serial number, and the number of landings and flight hours on the airplane. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056.
(e) Within 24 months after the effective date of this AD: Modify the fuel pump wire and fairing, per a method approved by the Manager, International Branch, ANM-116.
