Airworthiness Directive · Amendment 39-14386 · Airbus Model A318-100, A319-100, A320-200, A321-100, and A321-200 Series Airplanes, and Model A320-111 Airplanes
Airbus Model A318-100, A319-100, A320-200, A321-100, and A321-200 Series Airplanes, and Model A320-111 Airplanes
Superseded. A later AD replaced this one: AD 2007-18-09. Comply with the one in force.
This AD applies to all Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, and -231 airplanes; certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A318-100, A319-100, A320-200, A321-100, and A321-200 series airplanes, and Model A320-111 airplanes. This AD requires an inspection to determine whether certain braking and steering control units (BSCUs) are installed or have ever been installed. For airplanes on which certain BSCUs are installed or have ever been installed, this AD requires an inspection of the nose landing gear (NLG) upper support and corrective action if necessary, and a check of the NLG strut inflation pressure and an adjustment if necessary. For some of these airplanes, this AD also requires a revision to the aircraft flight manual to incorporate an operating procedure to recover normal steering in the event of a steering failure. This AD results from a report of an incident where an airplane landed with the NLG turned 90 degrees from centerline. We are issuing this AD to prevent landings with the NLG turned 90 degrees from centerline, which could result in reduced controllability 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.
Within 5 days after the effective date of this AD, perform a records review to determine whether the airplane is equipped with or has ever been equipped with a braking and steering control unit (BSCU) part number (P/N) E21327001 (standard L4.1, Airbus Modification 26965) or P/N E21327003 (standard L4.5, Airbus Modification 33376).
(g) For airplanes on which a records review required by paragraph (f) of this AD conclusively determines that the airplane is not and never has been equipped with BSCU P/N E21327001 or P/N E21327003, no further action is required by this AD.
For airplanes that are not specified in paragraph (g) of this AD and which do not have Airbus Modification 31152 incorporated in production (i.e. applicable only to aircraft with steering powered by the green hydraulic system): Within 10 days after the effective date of this AD, revise the Limitation Section of the Airbus A318/319/320/321 Aircraft Flight Manual (AFM) to include the following information. This may be done by inserting a copy of this AD into the AFM:
The ECAM message, in case of a nose wheel steering failure, will be worded as follows:
—“WHEEL N/W STRG FAULT” for aircraft with the FWC E3 and subsequent standards
—“WHEEL N.W. STEER FAULT” for aircraft with the FWC E2 Standard.
• If the L/G SHOCK ABSORBER FAULT ECAM caution is triggered at any time in flight, and the WHEEL N/W STRG FAULT ECAM caution is triggered after the landing gear extension:
• When all landing gear doors are indicated closed on ECAM WHEEL page, reset the BSCU:
—A/SKID&N/W STRG—OFF THEN ON
▪ If the WHEEL N/W STRG FAULT ECAM caution is no longer displayed, this indicates a successful nose wheel re-centering and steering recovery.
—Rearm the AUTO BRAKE, if necessary.
• If the WHEEL N/W STRG FAULT ECAM caution remains displayed, this indicates that the nose wheel steering remains lost, and that the nose wheels are not centered.
—During landing, delay nose wheel touchdown for as long as possible.
—Refer to the ECAM STATUS.
• If the WHEEL N/W STRG FAULT ECAM caution appears, without the L/G SHOCK ABSORBER FAULT ECAM caution:
—No specific crew action is requested by the WHEEL N/W STRG FAULT ECAM caution procedure.
—Refer to the ECAM STATUS.
Note 1: When a statement identical to that in paragraph (h) of this AD has been included in the general revisions of the AFM, the general revisions may be inserted into the AFM, and the copy of this AD may be removed from the AFM.
(i) For airplanes that are not specified in paragraph (g) of this AD: At the times specified in paragraphs (i)(1) and (i)(2) of this AD, perform a boroscope inspection of the NLG upper support (backplate) to detect ruptured (completely broken) anti-rotation lugs, in accordance with Airbus Technical Note 957.1901/05, dated October 18, 2005; and check the NLG strut inflation pressure and adjust as applicable before further flight, according to a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Ge ne rale de l'Aviation Civile (DGAC) (or its delegated agent). Chapter 12, Subject 12-14-32 of the Airbus A318/A319/A320/A321 Aircraft Maintenance Manual (AMM), as revised by Airbus A318/A319/A320/A321 AMM Temporary Revision (TR) 12-001, dated November 13, 2005, is one approved method.
(1) Within 100 flight cycles following an electronic centralized aircraft monitoring (ECAM) caution “L/G SHOCK ABSORBER FAULT” associated with at least one of the centralized fault display system (CFDS) messages listed in paragraphs (i)(1)(i), (i)(1)(ii), and (i)(1)(iii) of this AD.
(i) “N L/G EXT PROX SNSR 24GA TGT POS.”
(ii) “N L/G EXT PROX SNSR 25GA TGT POS.”
(iii) “N L/G SHOCK ABSORBER FAULT 2526GM.”
(2) Within 90 days after the effective date of this AD unless accomplished previously in accordance with paragraph (i)(1) of this AD.
(j) If any ruptured (completely broken) upper support anti-rotation lugs are found during the inspections required by paragraph (i) of this AD, before further flight, replace the NLG with a serviceable NLG according to a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the DGAC (or its delegated agent). Chapter 32 of the Airbus A318/A319/A320/A321 AMM is one approved method. If any other damage to the upper support lugs is found, before further flight, check whether the NLG wheels can be turned by hand without the compression of the shock absorber (i.e., without climbing the centering cam with the aircraft NLG on jacks) and the nose wheel steering disconnected from the electrical box 5GC. If the wheels can be turned, before further flight, replace the NLG with a serviceable NLG according to a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the DGAC (or its delegated agent). Chapter 32 of the Airbus A318/A319/A320/A321 AMM is one approved method. If the wheels cannot be turned, within 100 flight cycles accomplish corrective actions (which could include replacement or continuing inspections) in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA.
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
