Airworthiness Directive Lookup Free FAA AD search by N-number, make or model
Find the FAA airworthiness directives that may apply to an aircraft: 12,857 ADs from the Federal Register since 1995, through Oct 1, 2026, each with its applicability text and the official document. Free, no account.
N1137 is a Airbus A320-200 in the FAA registry (aircraft page). Matched on type certificate model A320-200.
RESULTS
67 ADs in effect may apply to N1137
- In effect67
- Recurring18
- Superseded or removed32
Informational only. These are FAA airworthiness directives whose published applicability names this make and model. Whether an AD applies to a particular aircraft depends on its serial number, installed engines, propellers, parts and modifications, and some ADs listed here will not apply. This list is not the official AD record and not a compliance determination: confirm applicability and compliance against the FAA’s Dynamic Regulatory System and the aircraft’s records with a certificated mechanic or inspector. Covers ADs published in the Federal Register since 1995, through Oct 1, 2026; older ADs, and engine, propeller and appliance ADs that do not name the aircraft, are not included.
Show only ADs in effect N1137’s registration record
- AD 2018-13-08 Superseded by AD 2022-14-10
Airbus Airplanes
This AD was prompted by a report that, during a center fuselage certification full-scale fatigue test, cracks were found on the front spar vertical stringer at frame (FR) 36.
Applicability, as the AD words it
This AD applies to Airbus Model A318-111, -112, -121, and -122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and - 133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and - 233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, - 231, and -232 airplanes; certificated in any category; all manufacturer serial numbers, except airplanes specified in paragraphs (c)(1) and (c)(2) of this AD. (1) Model A319 and A320 series airplanes on which Airbus Modification 160000 (structural reinforcement for sharklet installation) has been embodied in production. (2) Model A321 series airplanes on which Airbus Modification 160021 (structural reinforcement for sharklet installation) has been embodied in production.
- AD 2009-24-19 One-time
Airbus Model A320 Series Airplanes
to ensure continued compliance with the certification requirements, it is considered necessary to require compliance by means of an AD. Actions and Compliance (f) Unless already done.
Applicability, as the AD words it
This AD applies to Airbus Model A320-111, -211, -212, -214, -231, -232, and -233 series airplanes, certificated in any category, all certified models, all serial numbers, equipped with Hamilton Sundstrand (formerly Dowty) Ram Air Turbine (RAT) Ejection Jack, Model ERPS13EJ, part number (P/N) 114160004A or 114160005, except those airplanes on which Airbus modification 27189 was done in production or Airbus Service Bulletin A320-29-1100 was done in service, and on which Airbus modification 28413 was not done in production.
- AD 2009-09-05 One-time
Airbus Model A318-100 and A319-100 Series Airplanes; A320-111 Airplanes; A320-200 Series Airplanes; and A321-100 and A321-200 Series Airplanes
We are issuing this AD to prevent contact between the horizontal hinge pin and the adjacent electrical wire harness, which could result in damage to electrical wires, and consequent arcing and/or failure of associated systems.
Applicability, as the AD words it
This AD applies to Airbus Model A318-111 and 112; A319-111, -112, -113, -114, -115, -131, -132, and -133; A320-111, -211, -212, -214, -231, -232, and -233; and A321-111, -112, -131, -211, -212, - 213, -231, and -232 airplanes; certificated in any category; all manufactured serial numbers; except for those airplanes on which Airbus Modification 36115 has been done in production or Airbus Mandatory Service Bulletin A320-25-1535, dated April 27, 2007, has been done in service.
- AD 2009-09-01 One-time
Airbus Model A318, A319, A320 and A321 Series Airplanes
Applicability, as the AD words it
This AD applies to Airbus Model A318-111, A318-112, A318- 121, A318-122, A319-111, A319-112, A319-113, A319-114, A319-115, A319-131, A319-132, A319-133, A320-111, A320-211, A320-212, A320- 214, A320-231, A320-232, A320-233, A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321-231, and A321-232 airplanes; certificated in any category; except airplanes identified in paragraph (c)(1), (c)(2), (c)(3), or (c)(4) of this AD. (1) Any airplane for which the date of issuance of the original French or German airworthiness certificate or the date of issuance of the original French or German export certificate of airworthiness, is after February 24, 2009 (the effective date of European Aviation Safety Agency (EASA) Airworthiness Directive 2009- 0025 [Corrected: February 11, 2009]). (2) Any airplane for which it can be positively determined from records review that the bearing of any pendulum assembly has not been replaced or re-swaged since the date of issuance of the original French or German airworthiness certificate or the date of issuance of the original French or German export certificate of airworthiness. (3) Any airplane inspected prior to the effective date of this AD in accordance with Airbus Service Bulletin A320-57A1146, dated September 21, 2007 (for Model A318, A319 and A320 series airplanes); or in accordance with Airbus Service Bulletin A320-57A1144, dated February 6, 2007, or A320-57-1144, Revision 01, dated June 18, 2007 (for Model A321 series airplanes), and on which it can be positively determined from a records review that thereafter no replacement with a pendulum assembly whose bearing has been replaced or re-swaged since new manufacture was performed. (4) Any airplane inspected prior to the effective date of this AD in accordance with Airbus Service Bulletin A320-57A1146, dated September 21, 2007 (for Model A318, A319 and A320 series airplanes); or in accordance with Airbus Service Bulletin A320-57A1144, dated February 6, 2007, or A320-57-1144, Revision 01, dated June 18, 2007 (for Model A321 series airplanes), and on which it can be positively determined from a records review that thereafter no pendulum bearing replacement or re-swaging was performed.
- AD 2008-02-15 Recurring
Airbus Model A319 and A320 Series Airplanes
Applicability, as the AD words it
This AD applies to Airbus Model A319 and A320 series airplanes, certificated in any category, all certified models, all serial numbers (MSN); except airplanes identified in paragraphs (c)(1) and (c)(2) of this AD. Model A320 series airplanes MSN 2164 through MSN 2688 that have partially received Airbus Modification 33421 in production are affected by the requirements of this AD. (1) Model A319 series airplanes that have received Airbus Modifications 28238, 28162, and 28342 in production, or Airbus Modification 33421 in production. (2) Model A320 series airplanes that have received Airbus Modification 33421 fully embodied in production.
- AD 2007-16-04 Recurring
Airbus Model A319-100 and A320-200 Series Airplanes
We are issuing this AD to prevent plastic identification labels being ingested into the fuel pumps and consequently entering the engine fuel feed system, which could result in an engine shutdown.
Applicability, as the AD words it
This AD applies to Airbus Model A319-100 and Model A320-200 series airplanes, certificated in any category; as identified in Airbus Service Bulletins A320-28-1102, Revision 02, dated July 10, 2006; and A320-57-1117, Revision 02, dated March 13, 2006; except airplanes having manufacturer's serial numbers 1083, 1310, 1314, and 1360.
- AD 2007-06-17 One-time
Airbus Model A320 Series Airplanes
We are issuing this AD to prevent rupture of a rudder actuator fitting, which could result in reduced controllability of the airplane.
Applicability, as the AD words it
This AD applies to Airbus Model A320 series airplanes, certificated in any category; except those on which Airbus Modification 21733 or 21999 has been incorporated in production.
- AD 2006-22-04 One-time
Airbus Model A318-100 and A319-100 Series Airplanes; Model A320-111 Airplanes; Model A320-200, A321-200, A330-200, A330-300, A340-200, and A340-300 Series Airplanes; Model A340-541 Airplanes; and Model A340-642 Airplanes; Equipped With Certain Sogerma-Services Powered Seats
We are issuing this AD to prevent uncommanded movement of the pilot's or co-pilot's seat during takeoff or landing, which could result in interference with the operation of the airplane and consequent temporary loss of airplane control.
Applicability, as the AD words it
This AD applies to the airplanes identified in Table 1 of this AD, certificated in any category; equipped with any Sogerma- Services pilot or co-pilot seat identified in Sogerma-Services Service Bulletin TAAI1-25-617, dated February 1, 2005, excluding any seat having part number (P/N) TAAI3-03PE00-01, TAAI3-03PE01-01, TAAI3-03CE00-01, and TAAI3-03CE01-01, with a serial number (S/N) higher than 791, on which the actuator has not been replaced after the date of issuance of the original standard airworthiness certificate or date of issuance of the original export certificate of airworthiness. Table 1.--Applicability Airbus model (1) A318-111 and -112 airplanes. (2) A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes. (3) A320-111 airplanes. (4) A320-211, -212, -214, -231, -232, and -233 airplanes. (5) A321-111, -112, -131, -211 and -231 airplanes. (6) A330-201, -202, -203, -223, and -243 airplanes. (7) A330-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes. (8) A340-211, -212, and -213 airplanes. (9) A340-311, -312, and -313 airplanes. (10) A340-541 airplanes. (11) A340-642 airplanes.
- AD 2006-17-13 One-time
RECARO Aircraft Seating GmbH & Co. (RECARO) Model 3410 Seats
We are issuing this AD to prevent a seat belt from detaching due to a loose locknut and attachment bolt, which could result in injury to an occupant during emergency conditions.
Applicability, as the AD words it
This AD applies to certain RECARO Aircraft Seats GmbH & Co. (RECARO) Model 3410 302, 303, 306, 307, 314, 316, 317, 791, 792, and 795 series seats. These seats are installed on, but not limited to, Boeing 737-200, 737-700, and 737-800 series, 747-400 series, 777-200 and 777-300 series; and Airbus Industries A319-100 series, A320-200 series, and A321-200 series airplanes.
- AD 2006-09-11 Recurring
Airbus Model A319-100, A320-200, A321-100, and A321-200 Series Airplanes
We are issuing this AD to detect and correct corrosion and damage on the lower part of the lavatory walls, which could compromise the structural integrity of the CAS attachments, and cause injury to the cabin attendants during a crash landing.
Applicability, as the AD words it
This AD applies to Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, - 231, -232, and -233 airplanes; Model A321-111, -112, and -131 airplanes; and Model A321-211 and -231 airplanes; certificated in any category; equipped with the lavatories in Table 1 of this AD, onto which at least one cabin attendant seat (CAS) is attached; except those airplanes with lavatory walls that have not been modified since the application of Airbus Modification 31574 in production. Table 1.--Lavatory Installations Affected by This AD Installed by Lavatory-- Airbus Modification Type A DASELL: 23125 Type D DASELL: 22815 Type E DASELL: 22819 Type F DASELL: 23695
- AD 2006-10-03 One-time
Airbus Model A319-100 and A320-200 Series Airplanes; and Model A320-111 Airplanes
Applicability, as the AD words it
This AD applies to Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; and Model A320-111, -211, - 212, -214, -231, -232, and -233 airplanes; certificated in any category; that have received Airbus Modification 20024 in production (installation of a center tank), except airplanes on which Airbus Modification 24373 has been accomplished.
- AD 2006-07-09 Superseded by AD 2007-06-02
Airbus Model A318-100 and A319-100 Series Airplanes; Model A320-111 Airplanes; and Model A320-200, A321-100, and A321-200 Series Airplanes
Applicability, as the AD words it
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 airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; Model A321-111, -112, and -131 airplanes, and Model A321-211, -212, -213, -231 and -232 airplanes; certificated in any category.
- AD 2006-06-15 One-time
Airbus Model A318-100 Series Airplanes; Model A319-100 Series Airplanes; Model A320-111 Airplanes; Model A320-200 Series Airplanes; Model A321-100 Series Airplanes; and Model A321-200 Series Airplanes
This AD was prompted by a report indicating that, during a test of the fire extinguishing system, air leakage through the water drain valves in the forward and aft cargo doors reduced the concentration of fire extinguishing agent to below the level required to suppress a fire.
Applicability, as the AD words it
This AD applies to the Airbus airplanes identified in Table 1 of this AD, certificated in any category. Table 1.--Applicability But not having the following Having the following Or the following Airbus Airbus Airbus model-- Airbus modification service bulletin modification installed in production-- incorporated in service-- installed in production-- A318-111 and -112 airplanes: Not applicable: Not applicable: 33232 A319-111, -112, -113, -114, -115, -131, 25642 or 26213: A320-52-1088: 33232 -132, and -133 airplanes. A320-111 airplanes; and Model A320-211, 26213 or 26603: A320-52-1088: 33232 -212, -214, -231, -232, and -233 airplanes. A321-111, -112, and -131 airplanes; and 26213 or 26603: A320-52-1088: 33232 Model A321-211, -212, -213, -231, and - 232 airplanes.
- AD 2006-06-14 Superseded by AD 2013-24-08
Airbus Model A318-100 and A319-100 Series Airplanes, A320-111 Airplanes, A320-200 Series Airplanes, and A321-100 and A321-200 Series Airplanes
We are issuing this AD to prevent an ignition source in the wing fuel tank in the event of a lightning strike, which could result in a fire or explosion.
Applicability, as the AD words it
This AD applies to Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; A320-111 airplanes; Model A320-211, -212, -214, -231, - 232, and -233 airplanes; Model A321-111, -112, and -131 airplanes; and Model A321-211, -212, -213, -231, and -232 airplanes; certificated in any category; except airplanes on which Airbus Modification 27496 has been installed in production.
- AD 2006-04-06 Superseded by AD 2008-05-12
Airbus Model A318-100 Series Airplanes, Model A319-100 Series Airplanes, Model A320-111 Airplanes, Model A320-200 Series Airplanes, and Model A321-100 Series Airplanes
We are issuing this AD to detect and correct wear of the inboard flap trunnions, which could lead to loss of flap surface control and consequently result in the flap detaching from the airplane.
Applicability, as the AD words it
This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category. (1) Airbus Model A318-111 and -112 airplanes on which Airbus Modification 26495 has been incorporated in production. (2) All Airbus Model A319-111, -112, -113, -114, -115, -131, - 132, and -133 airplanes; Model A320-111 airplanes; Model A320-211, - 212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, and -131 airplanes.
- AD 2006-03-10 Superseded by AD 2009-09-05
Airbus Model A318-100 and A319-100 Series Airplanes; A320-111 Airplanes; A320-200 Series Airplanes; and A321-100 and A321-200 Series Airplanes
We are issuing this AD to prevent contact between the horizontal hinge pin and the adjacent electrical wire harness, which could result in damage to electrical wires, and consequent arcing and/or failure of associated systems.
Applicability, as the AD words it
This AD applies to Airbus Model A318-111 and -112; A319-111, -112, -113, -114, -115, -131, -132, and -133; A320-111, -211, -212, -214, -231, -232, and -233; and A321-111, -112, -131, -211 and -231 airplanes; certificated in any category; serial numbers (S/Ns) 1 through 2396 inclusive, except S/Ns 2104, 2143, 2248, 2270, 2347, 2366, 2372, 2376, 2384, 2386, 2388, 2390, 2391, 2393, and 2395.
- AD 2005-26-07 One-time
Airbus Model A318-100, A319-100, A320-200, A321-100, and A321-200 Series Airplanes; and Model A320-111 Airplanes
Applicability, as the AD words it
This AD applies to all Airbus Model A318-111, A318-112, A319-111, A319-112, A319-113, A319-114, A319-115, A319-131, A319- 132, A319-133, A320-111, A320-211, A320-212, A320-214, A320-231, A320-232, A320-233, A321-111, A321-112, A321-131, A321-211, and A321-231 airplanes; certificated in any category.
- AD 2005-24-06 Superseded by AD 2007-18-09
Airbus Model A318-100, A319-100, A320-200, A321-100, and A321-200 Series Airplanes, and Model A320-111 Airplanes
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.
Applicability, as the AD words it
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.
- AD 2005-23-05 Recurring
Airbus Model A319-100, A320-200, and A321-100 and -200 Series Airplanes
This AD was prompted by development of a new, improved modification of the telescopic girt bar of the escape slide/raft assembly.
Applicability, as the AD words it
This AD applies to Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133; A320-211, -212, -214, -231, -232, and - 233; and A321-111, -112, -131, -211, and -231 airplanes; certificated in any category; equipped with telescopic girt bars of the escape slide/raft assembly installed per Airbus Modification 20234, or Airbus Service Bulletin A320-25-1055 or A320-25-1218 in service; except those airplanes with Airbus Modification 31708.
- AD 2005-23-02 Superseded by AD 2012-09-12
Airbus Model A319-100 Series Airplanes, Model A320-111 Airplanes, Model A320-200 Series Airplanes, and Model A321-100 Series Airplanes
This AD was prompted by reports of an ACT fuel transfer failure due to air leakage around the seal of the outer manhole covers of the ACTs.
Applicability, as the AD words it
This AD applies to Airbus 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, and - 131 airplanes; certificated in any category; which are equipped with any additional center tank (ACT).
- AD 2005-22-10 One-time
Airbus Model A320-111 Airplanes, and Model A320-200 Series Airplanes
To prevent excessive vibrations of the elevators, which could result in reduced structural integrity and reduced controllability of the airplane.
Applicability, as the AD words it
Model A320-111, -211, -212, -214, -231, -232, and -233 airplanes, certificated in any category.
- AD 2005-20-36 One-time
Airbus Model A320-111 Airplanes; and Model A320-200, A321-100, and A321-200 Series Airplanes
This AD was prompted by the results of fuel system reviews conducted by the manufacturer.
Applicability, as the AD words it
This AD applies to Airbus 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; except those airplanes on which Airbus Modification 23645 has been incorporated in production.
- AD 2005-20-28 One-time
Airbus Model A319-100 Series Airplanes; Model A320-111 Airplanes; Model A320-200 Series Airplanes, and Model A321-100 and -200 Series Airplanes
This AD was prompted by information that the existing system design for interconnection of the EPSUs of the FPEEPMS does not provide adequate floor path lighting and marking for safe evacuation of the airplane in the event of an emergency.
Applicability, as the AD words it
This AD applies to Airbus 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; in which the floor proximity emergency escape path marking system (FPEEPMS) is equipped with BRUCE emergency power supply units (EPSUs) having BRUCE part number (P/N) 100865.
- AD 2005-20-17 One-time
Airbus Model A319-100 Series Airplanes; Model A320-111 Series Airplanes; Model A320-200 Series Airplanes; and Model A321-100 and -200 Series Airplanes
This AD was prompted by a report of failure of the parking brake while the airplane was on the holding point of the runway before takeoff, leading to a runway departure.
Applicability, as the AD words it
This AD applies to Airbus 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; except those modified in production by Airbus Modification 30062.
- AD 2005-19-16 Removed 2005-12-22
Airbus Model A320-111 Airplanes and Model A320-200 Series Airplanes
We are issuing this AD to prevent an ignition source for fuel vapor in the wing, which could result in fire or explosion in the adjacent wing fuel tank.
Applicability, as the AD words it
This AD applies to Airbus Model A320-111, -211, -212, -214, -231, -232, and -233 airplanes, certificated in any category; except those airplanes on which Airbus Modification 25513 has been accomplished in production.
- AD 2005-19-14 Superseded by AD 2007-07-09
Airbus Model A318-100, A319-100, A320-200, A321-100, and A321-200 Series Airplanes; and Model A320-111 Airplanes
This AD was prompted by results of fuel system reviews conducted by the manufacturer.
Applicability, as the AD words it
This AD applies to Airbus Model A318-111 and -112 airplanes; A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; A320-111, -211, -212, -214, -231, -232, and -233 airplanes; and A321-111, -112, -131, -211 and -231 airplanes; certificated in any category; except airplanes that have received Airbus Modification 31892 in production.
- AD 2005-17-07 One-time
Airbus Model A320-111 Airplanes and Model A320-200 Series Airplanes
The FAA is issuing this AD to detect and correct missing locking bolts on the axle nuts of the MLG wheels.
Applicability, as the AD words it
This AD applies to Airbus Model A320-111 airplanes, and Model A320-211, -212, -214, -231, -232, and -233 airplanes; certificated in any category; with serial numbers 2275 through 2440 inclusive, 2442 through 2446 inclusive, 2448, 2450, 2452, 2454, 2456 through 2458 inclusive, 2460 through 2474 inclusive, 2476 through 2478 inclusive, 2480 through 2483 inclusive, 2485, and 2486.
- AD 2005-15-07 Superseded by AD 2016-19-02
Airbus Model A320-111 Airplanes and Model A320-200 Series Airplanes
This AD was prompted by the results of fuel system reviews conducted by the manufacturer.
Applicability, as the AD words it
This AD applies to Airbus Model A320-111 airplanes; and Model A320-211, -212, -214, -231, -232, and -233 airplanes; certificated in any category; except those modified in production by Airbus Modification 22626.
- AD 2005-15-02 One-time
Airbus Model A320-111 Airplanes and Model A320-200 Series Airplanes
This AD was prompted by reports of unsuccessful in-flight ram air turbine (RAT) tests during which a deployed RAT failed to pressurize the blue hydraulic circuit of the RAT system.
Applicability, as the AD words it
This AD applies to Airbus Model A320-111 airplanes and Model A320-200 series airplanes, certificated in any category; equipped with Hamilton Sundstrand airborne ground check module (AGCM) having part number 769104, 769105, or 769106 installed; except those airplanes on which Airbus Modification 27189 has been done in production and on which Airbus Modification 28413 has not been done.
- AD 2005-12-19 One-time
Airbus Model A319, A320, and A321 Series Airplanes
This AD was prompted by a report that, during a test of the fire extinguishing system, air leakage around the temperature sensor for the aft cargo compartment reduced the concentration of fire extinguishing agent to below the level required to suppress a fire.
Applicability, as the AD words it
This AD applies to Airbus Model A319, A320, and A321 series airplanes, certificated in any category; as identified in Table 1 of this AD. Table 1.--Applicability But not having Having the Or the following the following following Airbus Airbus service Airbus Airbus model modification bulletin modification installed in incorporated in installed in production-- service-- production-- A319 series airplanes: 24486 A320-21-1140 32616 A320 series airplanes: 20084 A320-21-1048 32616 A321 series airplanes: 22596 (\1\) 32616 \1\ Not applicable.
- AD 2004-25-03 Recurring
Airbus Model A320 Series Airplanes
This AD was prompted by a full-scale fatigue survey on the Model A320 fleet.
Applicability, as the AD words it
This AD applies to Airbus Model A320-111, -211, -212, and - 231 series airplanes on which Airbus Modification 21202 has not been done, certificated in any category.
- AD 2004-25-02 Recurring
Airbus Model A320 Series Airplanes
This AD was prompted by a full-scale fatigue survey on the Model A320 fleet.
Applicability, as the AD words it
This AD applies to Airbus Model A320-111, -211, -212, and - 231 series airplanes on which Airbus Modification 21346 has not been done, certificated in any category.
- AD 2005-01-01 Recurring
Airbus Model A319 and A320-200 Series Airplanes
To prevent loose, missing, or discrepant rivets in specified areas of the door frames of the overwing emergency exits, which could lead to reduced structural integrity of the door frames.
Applicability, as the AD words it
Model A319 series airplanes and A320-200 series airplanes; certificated in any category; as listed in Airbus Service Bulletin A320-53-1147, dated September 22, 2000; Revision 02, dated December 3, 2002; or Revision 03, dated August 5, 2003.
- AD 2004-23-04 One-time
Airbus Model A319 and A320 Series Airplanes
To prevent overheating of the fuel probes due to a short circuit, and fuel leakage due to inadequate space for thermal expansion within the additional center tanks, which could result in fuel vapors or fuel contacting an ignition source.
Applicability, as the AD words it
Model A319 and A320 series airplanes, certificated in any category; as listed in Airbus Service Bulletin A320-28-1087, Revision 02, dated June 10, 2003; and Airbus Service Bulletin A320-28-1086, Revision 01, dated October 23, 2002.
- AD 2004-19-11 Superseded by AD 2016-08-13
Airbus Model A320 Series Airplanes
To detect and correct fatigue cracking in certain areas of the rear spar of the wing, which may lead to reduced structural integrity of the wing and the main landing gear (MLG).
Applicability, as the AD words it
Model A320 series airplanes, certificated in any category, except those modified in accordance with Airbus Modification 24591 (Airbus Service Bulletin A320-57-1089, dated December 22, 1996; Revision 01, dated April 17, 1997; Revision 02, dated November 6, 1998; or Revision 03, dated February 9, 2001).
- AD 2004-13-06 Superseded by AD 2013-15-21
Airbus Model A319 and A320 Series Airplanes
To detect and correct fatigue cracks on the side panels of the keel beams, which could result in reduced structural integrity of the airplane.
Applicability, as the AD words it
Model A319 and A320 series airplanes, certificated in any category; except those airplanes on which Airbus Modification 30355 has been incorporated in production.
- AD 2004-09-19 Recurring
Airbus Model A319 and A320 Series Airplanes
Applicability, as the AD words it
Model A319 and A320 series airplanes, certificated in any category; except those on which Airbus Modification 31888 has been accomplished.
- AD 2004-06-13 One-time
Airbus Model A319 and A320 Series Airplanes
To prevent the loss of the emergency evacuation slides during flight, which could result in damage to the fuselage, and to prevent incorrect inflation of the emergency evacuation slides, which could result in the emergency exits being unusable during an emergency evacuation.
Applicability, as the AD words it
Model A319 and A320 series airplanes, certificated in any category; except airplanes that have Airbus Modifications 24850 and 25844 and 27275 installed in production; or that have Airbus Service Bulletin A320-25-1156, Revision 01, dated February 2, 1999; or Revision 02, dated October 26, 1999; and Airbus Service Bulletin A320-25-1265, dated June 6, 2001; accomplished.
- AD 2004-06-03 One-time
Airbus Model A319, A320, and A321 Series Airplanes
To prevent jamming of the ram air turbine (RAT) actuator in an emergency which requires deployment of the RAT, and consequent loss of hydraulic and electrical power in the airplane.
Applicability, as the AD words it
Model A320 series airplanes which have received modification 27189; Model A319 series airplanes; and Model A321 series airplanes, provided that none has received modification 30978 or 28413; certificated in any category.
- AD 2004-05-04 One-time
Airbus Model A319 and A320 Series Airplanes
To prevent the loss of fuel quantity indication (FQI) of the center fuel tank, and to reduce the potential for an ignition source and possible explosion within the center fuel tank due to electrical arcing between the FQI probes and the adjacent structure in the event that the airplane is struck by lightning.
Applicability, as the AD words it
Model A319 and A320 series airplanes, as listed in Airbus Service Bulletin A320-28A1096, Revision 03, dated August 27, 2002; certificated in any category.
- AD 2004-03-06 Superseded by AD 2007-20-05
Airbus Model A319 and A320 Series Airplanes
To detect and correct fatigue cracks on the wing/fuselage joint cruciform fittings, which could result in reduced structural integrity of the wing/fuselage.
Applicability, as the AD words it
All Model A319 and A320 series airplanes, certificated in any category.
- AD 2003-25-07 Superseded by AD 2016-17-03
Airbus Model A319 and A320 Series Airplanes Equipped With Elevator and Aileron Computer (ELAC) L80 Standard
To prevent activation of the high angle-of-attack protection during final approach for landing, which could result in loss of the ability to flare properly during landings.
Applicability, as the AD words it
Model A319 and A320 series airplanes; certificated in any category; equipped with Elevator and Aileron Computer (ELAC) L80 Standard having part numbers listed in Airbus Service Bulletin A320-27-1135, dated June 29, 2001.
- AD 2002-04-10 Superseded by AD 2005-01-01
Airbus Model A319 Series Airplanes and A320-200 Series Airplanes
To detect and correct loose, missing, or discrepant rivets in specified areas of the door frames of the overwing emergency exits, which could lead to reduced structural integrity of the door frames.
Applicability, as the AD words it
Model A319 series airplanes and A320-200 series airplanes, as listed in Airbus Service Bulletin A320-53-1147, dated September 22, 2000; certificated in any category.
- AD 2001-20-16 One-time
Airbus Model A319 and A320 Series Airplanes
To prevent the airplane from departing the end of the runway during a landing or a rejected takeoff due to reduced braking performance.
Applicability, as the AD words it
Model A319 and A320 series airplanes, certificated in any category, equipped with Goodrich carbon brakes having part number 2-1526-4, 2-1526-5, 2-1572, 2-1600-1, or 2-1600- 2.
- AD 2001-17-14 Superseded by AD 2007-24-04 Engine
CFM International CFM56 Series Turbofan Engines
To prevent an LPT conical support from remaining in service beyond its certified cyclic life limit, which could result in an uncontained engine failure and damage to the airplane.
Applicability, as the AD words it
This airworthiness directive (AD) is applicable to CFM International (CFMI) CFM56-5C4/1 series turbofan engines with low pressure turbine (LPT) conical support, part number (P/N) 337-002- 407-0, installed. These engines are installed on, but not limited to Airbus Industrie A320 series airplanes.
- AD 2001-08-26 Superseded by AD 2003-25-07
Airbus Model A319 and A320 Series Airplanes Equipped with Elevator and Aileron Computer (ELAC) L80 Standard
To prevent activation of the high angle-of-attack protection during final approach for landing, which could result in loss of the ability to flare properly during landings.
Applicability, as the AD words it
Model A319 and A320 series airplanes; certificated in any category; equipped with Elevator and Aileron Computer (ELAC) L80 Standard having part numbers listed in Airbus Operator Information Telex (OIT) 999.0036/01/CL, dated March 23, 2001.
- AD 2000-14-14 Recurring
BFGoodrich Main Brake Assemblies as Installed on Airbus Model A319 and A320 Series Airplanes
To detect and correct thermal oxidation of the main brake assemblies, which could result in deterioration of the main landing gear (MLG) brakes, and consequent reduced braking performance.
Applicability, as the AD words it
Model BFGoodrich main brake assemblies having part number (P/N) 2-1598-1 or P/N 2-1600-1, as installed on Airbus Model A319 and A320 series airplanes, certificated in any category.
- AD 2000-11-21 One-time
Airbus Model A319, A320, and A321 Series Airplanes
To prevent failure of the servocontrol piston rod, which could result in reduced controllability of the airplane.
Applicability, as the AD words it
The following models, certificated in any category, excluding those on which Airbus Service Bulletin A320-27- 1126, dated April 26, 1999 (for Model A319 and 321 series airplanes); or A320-27-1127, dated April 26, 1999, or Revision 01, dated October 6, 1999 (for Model A320 series airplanes); has been accomplished: Model A319 series airplanes, serial numbers (S/N) 0546 through 0972 inclusive; Model A320 series airplanes, S/N 0002 through 0842 inclusive, 0846 through 0859 inclusive, 0865, 0866, and 0872 through 0960 inclusive; and Model A321 series airplanes, S/N 0364 through 0974 inclusive.
- AD 2000-10-15 Superseded by AD 2004-19-11
Airbus Model A320 Series Airplanes
To detect and correct fatigue cracking in certain areas of the rear spar of the wing, which may lead to reduced structural integrity of the wing and the main landing gear (MLG).
Applicability, as the AD words it
Model A320 series airplanes, certificated in any category, except those on which Airbus Modification 24591 (Airbus Service Bulletin A320-57-1089, dated December 22, 1996; Revision 01, dated April 17, 1997; or Revision 02, dated November 6, 1998) has been accomplished.
- AD 99-26-22 Superseded by AD 2004-06-13
Airbus Model A319 and A320 Series Airplanes
To prevent the loss of the escape slides during flight, which could make the emergency exits located over each wing unusable and result in damage to the fuselage.
Applicability, as the AD words it
Model A319 and A320 series airplanes, certificated in any category; except airplanes on which Airbus Modifications 24850 and 25844 have been installed in production, or on which Airbus Service Bulletin A320-25-1156, Revision 01, dated February 2, 1999, has been accomplished.
- AD 99-25-07 One-time
BFGoodrich Main Brake Assemblies as Installed on Airbus Model A319 and A320 Series Airplanes
To prevent thermal oxidation of the main brake assemblies of the main landing gear (MLG), which could result in deterioration of the MLG brakes, and consequent reduced braking performance.
Applicability, as the AD words it
BFGoodrich main brake assemblies having part number (P/N) 2-1598 or 2-1600, as installed on Airbus Model A319 and A320 series airplanes, certificated in any category.
- AD 99-25-03 Recurring Engine
International Aero Engines AG V2500-A1 Series Turbofan Engines
To prevent high pressure turbine (HPT) disk fracture, which could result in an uncontained engine failure and damage to the airplane.
Applicability, as the AD words it
International Aero Engines AG (IAE) V2500-A1 series turbofan engines, installed on but not limited to Airbus Industrie A320 series airplanes.
- AD 99-21-29 Superseded by AD 2001-24-05
Airbus Model A320 Series Airplanes
To prevent reduced controllability of the airplane due to the failure of the rudder artificial feel unit to properly disengage from autopilot mode.
Applicability, as the AD words it
Model A320 series airplanes, certificated in any category, except airplanes on which Airbus Industrie Modification 22624 has been accomplished or on which Modification 21999 was accomplished in production.
- AD 99-20-06 One-time
Airbus Industrie Model A320 Series Airplanes
To prevent malfunction of the low pressure non-return valve in the airborne ground check module (AGCM) of the ram air turbine (RAT), which could result in loss of the blue hydraulic system, and consequent loss of certain flight control and electrical systems.
Applicability, as the AD words it
Model A320 series airplanes, certificated in any category; except those airplanes on which Airbus Industrie Modification 27728 or 27189 has been installed in production, or on which Airbus Industrie Service Bulletin A320-29-1086 has been accomplished.
- AD 99-06-16 One-time Engine
CFM International CFM56-5 Series Turbofan Engines
To prevent a low cycle fatigue failure of the high pressure turbine rotor (HPTR) front air seal, which could result in an uncontained engine failure and damage to the aircraft.
Applicability, as the AD words it
CFM International CFM56-5 series turbofan engines installed on, but not limited to, Airbus A319 and A320 series aircraft.
- AD 99-06-09 One-time
Airbus Model A320 Series Airplanes
To prevent incorrect distribution of fire extinguishing chemicals in the event of a fire in the cargo compartment, which, if unconfined, could spread beyond the cargo compartment.
Applicability, as the AD words it
Model A320 series airplanes having manufacturer serial numbers 002 through 402 inclusive, on which Airbus Modification 20071 (reference Airbus Service Bulletin A320-26-1020, Revision 1, dated January 4, 1993) has been accomplished; except those airplanes on which Airbus Service Bulletin A320-26-1034, dated May 9, 1995; Revision 1, dated September 13, 1995; Revision 2, dated April 1, 1996; or Revision 3, dated December 5, 1997; has been accomplished; certificated in any category.
- AD 99-05-05 One-time Engine
International Aero Engines AG (IAE) V2500-A1 Series Turbofan Engines
To prevent a high pressure turbine (HPT) disk fracture, which could result in an uncontained engine failure, and damage to the airplane.
Applicability, as the AD words it
International Aero Engines AG (IAE) Models V2500- A1 turbofan engines, installed on but not limited to Airbus Industrie A320 series airplanes.
- AD 99-02-10 One-time
Airbus Model A320 Series Airplanes
To prevent leakage from hydraulic pipe fittings in the trimmable horizontal stabilizer (THS), which could result in failure of the THS and consequent reduced controllability of the airplane.
Applicability, as the AD words it
Model A320 series airplanes; serial numbers 002 through 008 inclusive, 010 through 014 inclusive, 016 through 078 inclusive, 080 through 104 inclusive, 106 through 363 inclusive, 365 through 384 inclusive, 386 through 411 inclusive, 413 through 433 inclusive, 435 through 457 inclusive, 459 through 467 inclusive, and 469 through 472 inclusive; except for airplanes on which Airbus Service Bulletin A320-29-1058, Revision 1, dated November 28, 1994, has been accomplished; certificated in any category.
- AD 99-02-04 One-time
Airbus Model A320 and A321 Series Airplanes
To prevent failure of the slat and flap control computer (SFCC), which could result in uncommanded slat retraction during takeoff and consequent insufficient wing lift available to complete a successful takeoff.
Applicability, as the AD words it
Model A320 series airplanes, as listed in Airbus Service Bulletin A320-27-1096, Revision 01, dated January 14, 1998; and Model A321 series airplanes, as listed in Airbus Service Bulletin A320-27-1103, dated June 14, 1996; certificated in any category.
- AD 99-02-03 One-time
Airbus Model A320 Series Airplanes
To prevent the trickling of water into the avionics compartment, which could result in avionics computer and equipment malfunctions.
Applicability, as the AD words it
Model A320 series airplanes on which Airbus Modification 22119 or 21999 has not been accomplished, certificated in any category.
- AD 99-01-19 Superseded by AD 2020-22-06
Airbus Model A320 Series Airplanes
To detect and correct fatigue cracking of the fuselage, which could result in reduced structural integrity of the airplane.
Applicability, as the AD words it
Model A320 series airplanes on which Airbus Modification 21346 (reference Airbus Service Bulletin A320-53-1031, dated December 9, 1994) has not been accomplished; certificated in any category.
- AD 99-01-18 Recurring
Airbus Model A320 Series Airplanes
To detect and correct fatigue cracking of the fuselage, which could result in reduced structural integrity of the airplane.
Applicability, as the AD words it
Model A320 series airplanes, having manufacturer's serial numbers 002 through 008 inclusive, 010 through 014 inclusive, 016 through 039 inclusive, 041 through 052 inclusive, 054, 056, and 057; on which Airbus Modification 21905 (reference Airbus Service Bulletin A320-53-1056, Revision 02, dated February 16, 1998) has not been accomplished; certificated in any category.
- AD 99-01-17 Superseded by AD 2004-25-03
Airbus Model A320 Series Airplanes
To detect and correct fatigue cracking of the fuselage, which could result in reduced structural integrity of the airplane.
Applicability, as the AD words it
Model A320 series airplanes on which Airbus Modification 21202 (reference Airbus Service Bulletin A320-53-1033, Revision 3, dated July 4, 1994) has not been accomplished, certificated in any category.
- AD 98-20-18 Superseded by AD 99-25-03 Engine
International Aero Engines (IAE) V2500- A1 Series Turbofan Engines
To prevent an HPT disk fracture, an uncontained engine failure, and damage to the aircraft.
Applicability, as the AD words it
International Aero Engines (IAE) V2500-A1 series turbofan engines, with high pressure turbine (HPT) stage 1 disks, part number (P/N) 2A1801, serial numbers (S/Ns) P100430, P100421, P100621, and P100618; HPT stage 1 disk, P/N 2A1101, S/ N P100346; and HPT stage 2 disk, P/N 2A0902, S/N P100381, installed. These engines are installed on Airbus A320 series aircraft.
- AD 98-22-05 Superseded by AD 2004-14-09
Airbus Model A320 Series Airplanes
To prevent fatigue cracking of the lower surface panel on the wing center box, which could result in reduced structural integrity of the airplane.
Applicability, as the AD words it
Model A320 series airplanes on which Airbus Modification 22418 (reference Airbus Service Bulletin A320-57-1043, Revision 02, dated May 14, 1997) has not been accomplished, certificated in any category.
- AD 98-21-01 One-time Engine
International Aero Engines AG (IAE) V2500-A1 Series Turbofan Engines
To prevent fan blade root cracks, which could result in fan blade root failure, an uncontained engine failure, and damage to the aircraft, for those engines that have not previously been inspected in accordance with IAE Service Bulletin (SB) No. V2500-ENG-72-0316, dated May 15, 1998; or No. V2500-ENG-72-0316, Revision 1, dated June 5, 1998; or No.V2500-ENG-72-0316, Revision 2, dated August 28, 1998.
Applicability, as the AD words it
International Aero Engines AG (IAE) V2500-A1 series turbofan engines, installed on but not limited to Airbus A320 series aircraft.
- AD 98-20-31 Recurring
Airbus Model A320 Series Airplanes
To detect and correct cracking in the pressurized floor pick-up angles at the rear spar of the wing, which could result in reduced structural integrity of the airframe.
Applicability, as the AD words it
Model A320 series airplanes, as listed in Airbus Service Bulletin A320-57-1090, Revision 01, dated June 10, 1997; certificated in any category.
- AD 98-20-30 Recurring
Airbus Model A320 Series Airplanes Equipped With a Bulk Cargo Door
To prevent fatigue cracking of the upper frame flanges, which could result in reduced structural integrity of the airplane.
Applicability, as the AD words it
Model A320 series airplanes, equipped with a bulk cargo door (Airbus Modification 20029), certificated in any category.
- AD 98-20-29 One-time
Airbus Industrie Model A320 Series Airplanes
To prevent pitch-up of the airplane due to activation of the spoilers during an automatic landing, which, if not corrected, could result in tail strikes and structural damage to the airplane.
Applicability, as the AD words it
Model A320 series airplanes on which Airbus Industrie Modification 23132, 24348, or 24511 has not been accomplished; certificated in any category.
- AD 98-19-23 One-time
Airbus Model A320 Series Airplanes
To prevent the possible loss of data recorded on the DFDR as a result of vibrations and/or accelerations during flight.
Applicability, as the AD words it
Model A320 series airplanes; equipped with a LORAL Digital Flight Data Recorder (DFDR) F800 [part number (P/N) 17M800-251/-261], and on which Airbus Modification 24959 (Airbus Service Bulletin A320-31-1088, Revision 1, dated September 16, 1996) has not been accomplished; certificated in any category.
-
Airbus Model A310, A300-600, and A320 Series Airplanes
Applicability, as the AD words it
Model A310 and A300-600 series airplanes on which Airbus Modification 10156 has not been accomplished (reference Airbus Service Bulletin A310-26-2023 or A300-26-6024), and Model A320 series airplanes on which Airbus Modification 22561 (reference Airbus Service Bulletin A320-26-1017) or Airbus Modification 24548 (reference Airbus Service Bulletin A320-26-1037) has not been accomplished; certificated in any category.
- AD 98-18-24 Superseded by AD 2018-20-02
Airbus Industrie Model A320 Series Airplanes
To correct fatigue cracking in the inner flange of door frame 66, left and right, which could result in reduced structural integrity of the airplane.
Applicability, as the AD words it
Model A320 series airplanes on which Airbus Modification 21778 (reference Airbus Service Bulletin A320-53-1072, dated November 7, 1995, as revised by Change Notice 0A, dated July 5, 1996) has not been accomplished, certificated in any category.
- AD 98-18-26 Superseded by AD 2016-01-11
Airbus Model A320 Series Airplanes
To detect and correct fatigue cracking of the front spar vertical stringers on the wings, which could result in reduced structural integrity of the airframe.
Applicability, as the AD words it
Model A320 series airplanes on which Airbus Modification 21290 (reference Airbus Service Bulletin A320-57-1017, Revision 01, dated March 17, 1997) has not been installed, certificated in any category.
- AD 98-18-16 One-time
Airbus Model A320 Series Airplanes
To prevent structural damage to the tail section when it strikes the runway, which could result in depressurization of the fuselage during flight.
Applicability, as the AD words it
Model A320 series airplanes on which Airbus Modification 22764 has not been installed, certificated in any category.
- AD 98-15-04 Recurring
Airbus Model A320 Series Airplanes
To prevent fatigue cracking on the bottom flanges of the longitudinal floor beams at frame 43, which could result in reduced structural integrity of the airplane.
Applicability, as the AD words it
Model A320 series airplanes, on which Airbus Modification 20904 (reference Airbus Service Bulletin A320-53-1008, dated March 31, 1995) has not been accomplished, certificated in any category.
- AD 98-13-14 Superseded by AD 2017-11-13
Airbus Model A320 Series Airplanes
To detect and correct fatigue cracking of the former junction at frame 68, which could result in reduced structural integrity of the aft fuselage.
Applicability, as the AD words it
Model A320 series airplanes, as listed in Airbus Service Bulletins A320-53-1089 and A320-53-1090, both dated November 22, 1995; on which Airbus Modifications 21780 and 21781 (reference Airbus Service Bulletin A320-53-1090) have not been installed; certificated in any category.
- AD 98-12-33 Recurring
Airbus Model A320 Series Airplanes
To detect and correct fatigue cracking on the connecting angle between frame 56 and the right-hand frame support at stringer 38, which could result in reduced structural integrity of the airplane.
Applicability, as the AD words it
Model A320 series airplanes, on which Airbus Modification 20941 (reference Airbus Service Bulletin A320-53-1011, dated December 9, 1994) has not been accomplished, certificated in any category.
- AD 98-06-20 One-time
Airbus Model A320 Series Airplanes
To prevent reduced structural integrity of the fuselage, restricted operation of the main landing gear (MLG) free-fall system, and, consequently, reduced ability to use the MLG during an emergency.
Applicability, as the AD words it
Model A320 series airplanes, manufacturer's serial numbers 002 through 008 inclusive, 010 through 078 inclusive, and 080 through 107 inclusive; certificated in any category.
- AD 89-23-06 Recurring Engine
CFM International CFM56-2, -3, -3B, - 3C, and -5 Series Turbofan Engines
To prevent a No. 3 bearing failure and subsequent inflight engine shutdown.
Applicability, as the AD words it
CFM International (CFMI) CFM56-2, -3, -3B, -3C, and -5 series turbofan engines, installed on but not limited to Airbus A319 and A320 series, McDonnell Douglas DC-8 series, and Boeing 737 series aircraft.
- AD 98-01-17 One-time
Airbus Model A320 Series Airplanes
To prevent failure of the main landing gear (MLG) to retract properly as a result of failure of a capacitor in the landing gear circuitry and subsequent electrical power interruption.
Applicability, as the AD words it
Model A320 series airplanes on which Airbus Modification 21574 (Airbus Service Bulletin A320-32-1139, Revision 1, dated December 30, 1994) or 21999 has not been installed, certificated in any category.
- AD 98-01-12 Superseded by AD 2004-01-03
Airbus Industrie Model A320 Series Airplanes
To prevent jamming of the upper safety locking pin on the passenger door, which could result in inability to open the passenger door and, consequently, could impede or delay passengers from exiting the airplane during an emergency.
Applicability, as the AD words it
Model A320 series airplanes on which Airbus Industrie Modification No. 24389 (Airbus Industrie Service Bulletin No. A320-52-1057, dated July 26, 1994) has not been accomplished, certificated in any category.
- AD 97-11-01 Superseded by AD 2000-12-04
Airbus Model A320 Series Airplanes
To prevent fatigue cracking in the area where the center fuselage joins the wing, which could reduce the structural integrity of this area and consequently result in rapid decompression of the fuselage.
Applicability, as the AD words it
Model A320 series airplanes as listed in Airbus Service Bulletin A320-53-1026, dated August 5, 1994; on which modifications 21281P1495 and 21680P1818 have not been installed; certificated in any category.
- AD 97-07-14 Superseded by AD 2015-18-05
Airbus Model A320 Series Airplanes
To prevent fatigue cracking in the rib flange of the front spar side of the wing center section, and consequent reduced structural integrity of fuselage frame 36 and the wing center section.
Applicability, as the AD words it
Model A320 series airplanes as listed in Airbus Service Bulletin A320-57-1013, Revision 1, dated September 29, 1992; certificated in any category.
- AD 97-05-13 One-time Engine
CFM International CFM56-5 Series Turbofan Engines
To prevent an air turbine engine starter failure, which could result in damage to the engine electrical harnesses.
Applicability, as the AD words it
CFM International (CFMI) CFM56-5 series turbofan engines, installed with air turbine engine starter, Part Number 301- 781-201-0, installed on but not limited to Airbus A320 series aircraft.
- AD 97-05-04 One-time
Airbus Model A320 Series Airplanes
To prevent loss of the standby emergency generation system, which provides necessary back-up capability when both main generators fail.
Applicability, as the AD words it
Model A320 series airplanes; on which a generator control unit (GCU) having part number (P/N) 520915 has not been installed, or on which Airbus Modification 21052 (reference Airbus Service Bulletin A320-24-1022) and Airbus Modification 21736 (reference Airbus Service Bulletin A320-24-1035) have not been accomplished; certificated in any category.
- AD 97-02-04 One-time
Airbus Model A300, A300-600, A310, and A320 Series Airplanes
To prevent the loss of brake effectiveness during a high energy rejected takeoff (RTO).
Applicability, as the AD words it
Model A300, A300-600, A310, and A320 series airplanes equipped with Messier-Bugatti, BFGoodrich, Allied Signal (ALS) Aerospace Company (Bendix), or Aircraft Braking Systems (ABS) brakes; certificated in any category.
- AD 96-25-07 Recurring
Airbus Industrie Model A320 Series Airplanes
To prevent the ram air turbine (RAT) from breaking away from its support leg, which could damage the airplane structure and systems, and could injure ground personnel.
Applicability, as the AD words it
Model A320-111, -211, -212, -214, -231, and -232 series airplanes; on which Airbus Industrie Modification 24701 (as described in Airbus Service Bulletin A320-29-1065, dated February 28, 1995) has not been installed; certificated in any category.
- AD 96-25-04 Superseded by AD 2019-22-04
Airbus Model A320 Series Airplanes
To prevent electrical short circuiting due to chafing of the wire bundles in the wing, horizontal stabilizer, or main landing gear (MLG) bay.
Applicability, as the AD words it
Model A320 series airplanes on which Airbus Modification No. 22109 (Airbus Service Bulletin A320-24-1045, Revision 3, dated June 10, 1993) has not been accomplished; certificated in any category.
- AD 95-26-15 One-time
Allied Signal Commercial Avionics Systems CAS-81 Traffic Alert and Collision Avoidance Systems (TCAS) as Installed in, but not Limited to, Various Transport Category Airplanes
To ensure that the flightcrew is advised of the potential hazard associated with failure of the audio output of the CAS-81 TCAS, and of the procedures necessary to address it.
Applicability, as the AD words it
CAS-81 Traffic Alert and Collision Avoidance Systems (TCAS) installed in transport category airpanes, including but not limited to, the following airplane models, certificated in any category: Aerospatiale Models ATR42 and ATR72 series airplanes; Airbus Industrie Models A300B2, A300B4, A310-200, A310-300, A300-600, A320-100, A320-200, A321-100, A330-300, A340-200, and A340-300 series airplanes; Beech Models 1900 and BE-65 through -90 (inclusive) series airplanes; Boeing Models 727-100, 727-200, 737-200, 737-300, 737-400, 737- 500, 747-100, 747-200, 747-300, 747-400, 747SP, 757-200, 767-200, 767-300, and 777-200 series airplanes; Convair Model CV-580 airplanes; de Havilland DHC-7 series airplanes and Model DHC-8-100 airplanes; Embraer Model EMB-120 series airplanes; Fairchild Model F227 airplanes; Fokker Models F28 Mark 100, Mark 1000, and Mark 4000 series airplanes; General Dynamics Models Convair 340 and 440 airplanes; Gulfstream Models G-159 and G-IV airplanes; Lockheed Model L1011 series airplanes; McDonnell Douglas Models DC-8-60, DC-9-31, DC-9-51, DC-10-10; DC-10-30, DC-10-30F, MD-11, and MD-80 series airplanes; Rockwell International NA-265-65 airplanes; Saab Model 340 series airplanes; and Shorts Model 360 series airplanes.
- AD 96-18-16 One-time Engine
CFM International CFM56-2/-2A/-2B/-3/- 3B/-3C/-5 Series Turbofan Engines
To prevent a low cycle fatigue (LCF) failure of the low pressure turbine rotor (LPTR) stub shaft and conical support, which could result in an uncontained engine failure and damage to the aircraft.
Applicability, as the AD words it
CFM International (CFMI) CFM56-2/-2A/-2B/-3/-3B/- 3C/-5 series turbofan engines installed on, but not limited to Airbus A319 and A320 series, McDonnell Douglas DC-8 series, and Boeing 737, as well as Boeing E-3, E-6, and KC-135 (military) series aircraft. Note: This airworthiness directive (AD) applies to each engine 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 engines 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 in accordance with paragraph (k) 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.
- AD 96-18-12 One-time
Airbus Model A320 Series Airplanes
To ensure that the proper P-clips are installed.
Applicability, as the AD words it
Model A320 series airplanes, manufacturer's serial numbers 129 through 343 inclusive, 345 through 347 inclusive, and 349 through 363 inclusive; certificated in any category.
- AD 96-16-03 One-time
Airbus Model A320-200 Series Airplanes
To prevent damage to the internal area of the shock absorber sub-assembly, which could cause an overextension of the shock absorber and failure of the torque link.
Applicability, as the AD words it
Model A320-200 series airplanes on which Airbus Modification 24594 (reference Airbus Service Bulletin A320-32-1144) has not been installed, certificated in any category.
- AD 96-04-06 One-time
Airbus Model A320 Series Airplanes
To prevent an electrical overvoltage of the relays, which could result in the loss of the braking/steering control unit (BSCU) systems, and subsequent loss of the antiskid functions and nose wheel steering of the airplane.
Applicability, as the AD words it
Model A320 series airplanes on which Airbus Modification 23611 (reference Airbus Service Bulletin A320-32-1115) has not been installed, certificated in any category.
- AD 95-24-08 One-time
Airbus Model A320 Series Airplanes
To prevent deployment of a thrust reverser during flight, which could adversely affect the controllability of the airplane.
Applicability, as the AD words it
Model A320 series airplanes; as listed in Airbus Industrie Service Bulletin A320-29-1048, Revision 1, dated December 4, 1992, and Revision 2, dated September 1, 1994; certificated in any category.
- AD 95-22-11 One-time
Airbus Model A320 Series Airplanes
To prevent the initiation and propagation of fatigue cracking in fuselage frame 20, which could adversely affect the structural integrity of this area of the fuselage.
Applicability, as the AD words it
Model A320 airplanes; having manufacturer's serial numbers (MSN) 006, 008, 011, 017, 018, 039, 042, 045, 046, and 047; certificated in any category.
- AD 95-22-10 One-time
Airbus Model A320 Series Airplanes
To prevent the initiation and propagation of fatigue cracking in the pintle pins of the main landing gear (MLG), which could lead to the failure of the pintle pins and consequent collapse of the MLG.
Applicability, as the AD words it
Model A320 airplanes; as listed in Airbus Service Bulletin A320-32-1024, dated January 29, 1990; certificated in any category.
- AD 95-17-12 Superseded by AD 99-02-10
Airbus Model A320 Series Airplanes
To prevent loss of the pilot's ability to control the moveable surfaces of the THS.
Applicability, as the AD words it
Model A320 series airplanes on which Airbus Modification 22621 (reference Airbus Service Bulletin A320-27-1041) and Airbus Modification 23556 (reference Airbus Service Bulletin A320-29-1058) have not been installed, certificated in any category.
- AD 95-04-12 Recurring
Airbus Model A310, A300-600, and A320 Series Airplanes
To prevent failure of the lavatory smoke detection system to detect smoke in the lavatory.
Applicability, as the AD words it
Model A310 and A300-600 series airplanes on which Airbus Modification 10156 has not been accomplished, and Model A320 series airplanes on which Airbus Modification 22561 or Airbus Service Bulletin A320-26-1017 has not been accomplished; certificated in any category. This AD is not applicable to airplanes on which the air extraction system is not configured to detect smoke in the extracted air. (That is, airplanes that do not have standard air extraction systems are not subject to the requirements of this AD.)
- AD 94-01-04 One-time
Honeywell Traffic Alert and Collision Avoidance System II Computer Units, as Installed on Various Transport Category Airplanes
To prevent collisions or near misses caused by incompatibility between the TCAS II processors and the current air traffic control system.
Applicability, as the AD words it
Traffic Alert and Collision Avoidance System (TCAS) II computer units; part numbers 4066010-901, -902, and -903; as installed on, but not limited to, the following airplanes, certificated in any category: Airbus Industrie Model A300-600, A310-200, A310-300, A320-200, and A340 series airplanes; Boeing Model 727-100 and -200; 737-100, -200, -300, and -400; 747- 100, -200, -300, -400 and 747SP; 757-200 and -500; and 767-200 and - 300 series airplanes; Cessna Citation Model C550 and C560 series airplanes, and Cessna Citation III and VII series airplanes; Canadair Challenger Model CL-600-2B16 and -2A12 series airplanes; British Aerospace Model 125-800A; Gulfstream Model GII, GIIB, GIII, and GIV series airplanes; Lockheed Model L-1011 series airplanes; McDonnell Douglas Model DC-9-10, -20, -30-, -40, and -50; DC-10-10, -15, -30, and -40; MD-11; and DC-9-80 series airplanes; and Model MD-88 airplanes; Dassault Aviation Model Mystere-Falcon 50 and 900 series airplanes; Short Brothers Model SD3-60 series airplanes; de Havilland Model DHC-8-100 and DHC-7 series airplanes; Fokker Model F27 series airplanes; and Corporate Jets Limited Model BAe 125-800A and BAe 125-1000A series airplanes.
Radar reads the logbooks and ties each AD to the entries that show how and when it was complied with, with recurring ADs due by date and hours.
QUESTIONS
AD lookup questions
Sources: FAA final rules under 14 CFR part 39, from the Federal Register; make and model from the FAA aircraft registry. The FAA’s Dynamic Regulatory System holds the official AD list.
What is an airworthiness directive (AD)?
An airworthiness directive is a legally enforceable rule the FAA issues under 14 CFR part 39 when it finds an unsafe condition in an aircraft, engine, propeller or appliance that is likely to exist in others of the same design. It says which products it applies to and what must be done, and by when: an inspection, a part replacement, a modification or a limitation. No one may operate a product to which an AD applies except in accordance with it.
How do I look up the ADs for my aircraft?
Type the N-number, or the make and model, into the box above. Radar finds the aircraft's make and model in the FAA registry and lists every AD published in the Federal Register whose applicability names it, newest first, with the AD's own applicability text and a link to the official document. The FAA's Dynamic Regulatory System (drs.faa.gov) holds the official list.
Does every AD in the results apply to my aircraft?
Not necessarily. An AD can be limited to serial number ranges, to aircraft with certain parts or modifications installed, or to a configuration. The results are ADs that may apply because they name the make and model. A certificated mechanic or inspector determines applicability against the aircraft's serial number and records, and records how each applicable AD was complied with.
What is the difference between a recurring and a one-time AD?
A one-time AD is complied with once, for example by replacing a part. A recurring (repetitive) AD requires an action again at an interval, such as an inspection every 100 hours or every 12 months, until a terminating action ends it. Radar marks an AD Recurring when its text requires repetitive actions; always read the AD for the intervals.
What does superseded mean?
When the FAA replaces an AD with a new one, the old AD is superseded: its requirements are carried into, or replaced by, the new AD. Results show the ADs in effect by default; superseded and removed ADs can be shown for the history.
Where does this data come from?
The Federal Register, where the FAA publishes every AD as a final rule. Radar reads each one from the Federal Register API (12,857 ADs since 1995) and refreshes the list every weekday. Make and model come from the FAA aircraft registry. ADs issued before 1995 are not in the Federal Register's online edition and are not included.
Are engine and propeller ADs included?
Only when their applicability names the aircraft. Most engine and propeller ADs name the engine or propeller model, so check those by the installed engine and propeller models. Appliance ADs that list the aircraft among those the appliance can be installed on are included and marked Appliance.
Know which ADs apply, and where each one was signed off.
Radar reads every logbook page, typed or handwritten, and builds one searchable record per tail: times, inspections, ADs and components, each tied to the page it came from.