Airworthiness Directive · Amendment 39-14540 · Airbus Model A310 Airplanes, Model A300 B4-600 Series Airplanes, Model A300 B4-600R Series Airplanes, Model A300 F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes
Airbus Model A310 Airplanes, Model A300 B4-600 Series Airplanes, Model A300 B4-600R Series Airplanes, Model A300 F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes
Superseded. A later AD replaced this one: AD 2008-11-05. Comply with the one in force.
This AD applies to Airbus Model A310 airplanes; Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R and F4-622R airplanes; and Model A300 C4-605R Variant F airplanes; certificated in any category; equipped with a carbon fiber reinforced plastic (CFRP) rudder having any series of part number (P/N) A55471500; except for those airplanes on which Airbus Modification 8827 has been incorporated in production.
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A310 airplanes, Model A300 B4-600 series airplanes, Model A300 B4-600R series airplanes, Model A300 F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes. This AD requires inspections of the rudder for discrepancies and corrective action if necessary. This AD also requires reporting all inspection results to the airplane manufacturer and the FAA. This AD results from two separate findings of inner skin disbonding discovered while undergoing unrelated repair and maintenance procedures. We are issuing this AD to detect discrepancies of the rudder, which could result in reduced structural integrity of the rudder.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Within 500 flight cycles or 120 days after the effective date of this AD, whichever occurs first: Do the actions specified in paragraphs (f)(1), (f)(2), and (f)(3) of this AD, in accordance with paragraph 4.2.2 of Airbus All Operators Telex (AOT) A310-55A2043 (for Model A310 airplanes) or AOT A300-55A6042 (for Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R and F4-622R airplanes; and Model A300 C4-605R Variant F airplanes), both dated March 2, 2006, as applicable.
(1) Do a general visual inspection of the drainage at the lower edge of the rudder spar to determine if the aft edges of the leading edge butt strap at rib 0 are clean. If any aft edge side of the leading edge butt strap at rib 0 is not clean, before further flight, restore the drainage to the correct condition.
Note 1: For the purposes of this AD, a general visual inspection is: “A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.”
Note 2: AOT A310-55A2043 refers to Chapter 55-42-11 of the Airbus A310 Structural Repair Manual (SRM) as an additional source of service information for restoring the drainage to the correct condition. AOT A300-55A6042 refers to Chapter 55-42-11 of the Airbus A300-600 SRM as an additional source of service information for restoring the drainage to the correct condition.
(2) Do a general visual inspection of the rear spar of the rudder external surfaces below the rudder actuators for the presence of hydraulic fluid. If any hydraulic fluid is found, before further flight, clean the contaminated rudder external surfaces.
Note 3: AOT A310-55A2043 refers to Chapter 51-78-20 of the Airbus A310 SRM as an additional source of service information for cleaning hydraulic fluids from the rudder external surfaces. AOT A300-55A6042 refers to Chapter 51-78-20 of the Airbus A300-600 SRM as an additional source of service information for cleaning hydraulic fluids from the rudder external surfaces.
(3) Clean the inner surface of the rudder panels and do a manual tap test inspection, or an automatic tap test inspection using Woodpecker tool WP632, at the inner side of the rudder panels for any disbonding in the inspection areas defined in Airbus Technical Disposition 943.0046/06, dated March 2, 2006. If any disbond area is found during a manual tap test inspection, as an option, an automatic tap test inspection using Woodpecker tool WP632 may be accomplished before further flight to verify the finding. If any disbond area crosses the perimeter of any inspection zone defined in Airbus Technical Disposition 943.0046/06, before further flight, repeat the tap test inspection in the applicable area outside of the defined inspection zone to obtain the size of the entire disbond area.
(i) If one disbond area per panel with a diameter of less than 130mm is found during the inspection required by paragraph (f)(3) of this AD: Within 6 months, do a temporary or permanent repair of the disbond area using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA. Chapter 55-41-12 of the Airbus A310 SRM is one approved method for accomplishing the temporary or permanent repair on Model A310 airplanes. Chapter 55-41-12 of the Airbus A300-600 SRM is one approved method for accomplishing the temporary or permanent repair on Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R and F4-622R airplanes; and Model A300 C4-605R Variant F airplanes. If a temporary repair is accomplished, within 1,500 flight cycles after accomplishing the temporary repair, do a permanent repair of the disbond area in accordance with this paragraph.
(ii) If one disbond area per panel with a diameter of 130mm or greater, but less than 200mm, is found during the inspection required by paragraph (f)(3) of this AD: Before further flight after the inspection, do a temporary or permanent repair of the disbond area using a method approved by the Manager, International Branch, ANM-116, FAA. Chapter 55-41-12 of the Airbus A310 SRM is one approved method for accomplishing the temporary or permanent repair on Model A310 airplanes. Chapter 55-41-12 of the Airbus A300-600 SRM is one approved method for accomplishing the temporary or permanent repair on Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R and F4-622R airplanes; and Model A300 C4-605R Variant F airplanes. If a temporary repair is accomplished, within 1,500 flight cycles after accomplishing the temporary repair, do a permanent repair of the disbond area in accordance with this paragraph.
(iii) If one disbond area per panel with a diameter of 200mm or greater is found during the inspection required by paragraph (f)(3) of this AD: Before further flight after the inspection, repair the disbond area using a method approved by the Manager, International Branch, ANM-116, FAA.
(iv) If more than one disbond area of any diameter is found on a single panel during the inspection required by paragraph (f)(3) of this AD: Before further flight, repair the disbond areas using a method approved by the Manager, International Branch, ANM-116, FAA.
At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD, submit a report of all findings (both positive and negative) of the inspection required by paragraph (f)(3) of this AD to M. Xavier Jolivet, Dept. SEE83; fax +33(0) 5 61-93-36-14; e-mail Xavier.Jolivet@airbus.com, and to Thomas Stafford, International Branch, ANM-116, FAA; fax (425) 227-1149; e-mail Thomas.Stafford@faa.gov. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane. Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120-0056.
(1) If the inspection is accomplished after the effective date of this AD: Submit the report within 10 days after the inspection.
(2) If the inspection was accomplished before the effective date of this AD: Submit the report within 10 days after the effective date of this AD.
As of the effective date of this AD, no person may install a CFRP rudder, any series of P/N A55471500, on any airplane, unless the CFRP rudder has been inspected and any applicable corrective action has been accomplished in accordance with paragraphs (f)(2) and (f)(3) of this AD.
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.
