Results
48-03-03: 48-03-03 PIPER: Applies to PA-11 Aircraft Serial Numbers 11-1 Through 11-301, and 11-1350 Through 11-1400, Except Serial Numbers 11-233, 11-243, 11-261, 11-266, 11-281, 11- 296, and 11-300. Compliance required by April 1, 1948. In order to prevent engine malfunctioning due to insufficient fuel flow when less than 5 gallons of fuel are in the wing tank and the airplane is operated in prolonged glides and dives, a header tank (Piper P/N 10725) must be installed in the fuel system. Until the header tank is installed, avoid prolonged glides and dives when less than 5 gallons fuel are in the main tank. (Piper Service Bulletin No. 99 dated July 29, 1947, covers this subject.)
2002-26-03: This amendment adopts a new airworthiness directive (AD) that applies to Brackett Aircraft Company (Brackett) single screen air filter assemblies that are installed on airplanes. This AD requires you to check the Brackett single screen air filter assembly for correct installation. This AD also requires you to install an additional screen, replace the Brackett single screen air filter assembly with a double screen filter, or replace with another approved design filter at a specified time. This AD is the result of several reports of service difficulties of incorrect installation of the air filters. The actions specified by this AD are intended to detect and correct incorrect installation of the air filter, which could result in failure of the air filter. Such failure could lead to engine/turbocharger ingestion of the air filter foam element.
2006-15-13: The FAA is adopting a new airworthiness directive (AD) for McCauley Propeller Systems propeller models B5JFR36C1101/114GCA-0, C5JFR36C1102/L114GCA-0, B5JFR36C1103/114HCA-0, and C5JFR36C1104/ L114HCA-0. This AD requires a onetime fluorescent penetrant inspection (FPI) and eddy current inspection (ECI) of propeller blades for cracks, and if any crack indications are found, removing the blade from service. This AD results from a report of two propeller blades on the same propeller assembly, found cracked during propeller overhaul. We are issuing this AD to detect cracks in the propeller blade that could cause failure and separation of the propeller blade and loss of control of the airplane.
99-01-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires repetitive inspections to detect fatigue cracking in certain areas of the fuselage; and corrective action, if necessary. This amendment also provides for an optional terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct fatigue cracking of the fuselage, which could result in reduced structural integrity of the airplane.
98-15-01: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-145 series airplanes, that requires a one-time inspection to detect bulging or cracking of the pitot 1 and pitot 2 drain tubes in the forward electronic compartment; and cleaning the tubes or replacing drain tubes with new tubes, if necessary. This amendment also requires modification of the pitot/static system. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct bulging and cracking of the pitot 1 and pitot 2 drain tubes in the forward electronic compartment caused by cycles of water freezing and expanding inside the tubes, which could result in erroneous airspeed indications to the flight crew and reduced operational safety in all phases of flight.
2024-10-12: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Canada Limited Model 407 helicopters. This AD was prompted by a report that a certain part-numbered fuel system standpipe assembly (standpipe) may have sharp edges at the interval weld joints due to a quality escape during the manufacturing process. This AD requires inspecting certain fuel system parts and, depending on the inspection results, taking corrective actions and performing a fuel quantity gauging system calibration. Depending on the results of the fuel quantity gauging system calibration, this AD requires performing additional corrective actions and repeating the fuel quantity gauging system calibration. The FAA is issuing this AD to address the unsafe condition on these products.
80-15-02: 80-15-02 PARTENAVIA COSTRUZIONI AERONAUTICHE S.p.A.: Amendment 39- 3839. Applies to Partenavia Model P.68 and P.68B airplanes serial numbers 1 through 165, except serial number 40, certificated in all categories, which have rudder cable pulley brackets P/N 2.3097-1 installed. Compliance required as indicated, unless already accomplished. To prevent the loss of proper rudder cable tension and rudder control system failure, accomplish the following: (a) For airplanes which have more than 500 hours time in service on the effective date of this AD, within the next 50 hours time in service after the effective date of this AD, accomplish paragraph (c) or paragraph (e) of this AD. (b) For airplanes which have less than 500 hours time in service on the effective date of this AD, before accumulating a total of 500 hours time in service, or within the next 50 hours time in service after the effective date of this AD, whichever occurs later, accomplish paragraph (c) or paragraph (e) of this AD. (c) Inspect the rudder pedal interconnecting bell crank bracket for cracks with special attention to the lower bracket and the rear face of aircraft frame number 3 for cracks and loose rivets in the area of the rudder cable pulley bracket attachment in accordance with PART II "Instructions" of Partenavia Service Bulletin 40, dated September 9, 1978, or an FAA-approved equivalent. If no cracks are found, repeat the inspection at intervals not to exceed 50 hours time in service since the last inspection until paragraph (e) of this AD is accomplished. (d) If as a result of an inspection required by paragraph (c) of this AD, cracks or loose rivets are found, before further flight, except as provided in paragraph (g) of this AD, (1) repair cracks in frame number 3 by stop drilling; (2) remove any loose rivets and replace with new rivets; and (3) replace any cracked brackets, P/N 2.3097-1, by compliance with paragraph (e) of this AD. Uponcompliance with subparagraphs (1), (2) and (3) of this paragraph, the repetitive inspections required by paragraph (c) are no longer required. (e) Replace the rudder pedal interconnecting bell crank bracket, P/N 2.3097-1, with a new bracket, P/N 2.3111-1, in accordance with PART III "Instructions" of Partenavia Service Bulletin No. 40, dated September 9, 1978, or an FAA-approved equivalent. (f) Equivalent means of compliance specified in this AD must be approved by the Chief, Aircraft Certification Staff, Europe, Africa and Middle East Office, c/o American Embassy, Brussels, Belgium. (g) Aircraft may be flown in accordance with FAR 21.197 and 21.199 to a location where the repairs and replacement can be performed. This amendment becomes effective July 21, 1980.
2018-02-18: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, and A320 series airplanes and Model A321-111, -112, -131, -211, -212, -213, -231, -232 airplanes. This AD requires revising the airplane flight manual (AFM) to provide guidance to the flight crew for emergency procedures when erroneous airspeed indications are displayed on the back-up speed scale (BUSS). This AD was prompted by a determination that, when two angle of attack (AoA) sensors are adversely affected by icing conditions at the same time, data displayed on the BUSS could be erroneous. We are issuing this AD to address the unsafe condition on these products.
78-26-03: 78-26-03 GRUMMAN: Amendment 39-3369. Applies to Models G-164, G-164A and G-164B aircraft, certificated in all categories, that have been in service for either more than 500 hours or six months. Compliance is required as indicated: To detect corrosion of the lower wing attachment fittings, P/N's A1050-1, -3, -4, -101, -102, -103, -104, -13, -19, -20, -411, -412 and 3050-13, -14, -15, -16, accomplish the following: (a) Within the next 25 hours in service and thereafter at intervals not to exceed 500 hours in service or six months, whichever comes first, since the last inspection, visually inspect the lower wing panel attachment fittings for corrosion. (b) If surface corrosion (corrosion which is evidenced by dulling, pitting, blistering, scaling, roughness, or localized discoloration of the metal surface) is found on the attachment fittings, remove the wing and the corrosion. If it is required to clean up corrosion of the rear fittings follow the procedure below: 1. Press wing attachment bolt bushing below corroded surface. Do not fully remove the bushing. 2. Remove corrosion. 3. Equalize the amount the bushing extends from each surface of the fitting. 4. Measure gap in fuselage fitting. 5. Fabricate shims for both sides of fitting so that total width of fitting does not exceed gap of fuselage and bushing does not exceed width of fitting by more than .020". If the front or rear wing attachment fitting dimensions are found to be in excess of the minimum limits specified in paragraph (c), (d), or (e), protect the surface from further corrosion in accordance with FAA Advisory Circular 43.13-1A, Paragraph 250(b) or equivalent. (c) For G-164 aircraft S/N's 001 thru 400: If after removal of the corrosion, the thickness of the front or rear fitting is found to be less than the .231", or the distance from the edge of the fitting is found to be less than .290", install an unused fitting of the same part number or an equivalent.(d) For G-164A aircraft S/N's 401 and up. If after removal of the corrosion, the thickness of the front or rear fitting is found to be less than .220", or the distance from the edge of the hole to the edge of the fitting is found to be less than .340", install an unused fitting of the same part number or an equivalent. (e) For G-164B aircraft S/N's 001 and up. If after removal of the corrosion, the thickness of the front or rear fitting is found to be less than .230", or the distance from the edge of the hole to the edge of the fitting is found to be less than .515", install an unused fitting of the same part number or an equivalent. Equivalent parts and corrosion protection must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Upon request, with substantiating data submitted through an FAA Maintenance Inspector, the compliance times specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. The aircraft may be flown in accordance with FAR 21.197 to a location where the AD can be accomplished. Grumman Service Bulletin No. 65 dated October 16, 1978, covers this same subject. This amendment is effective December 20, 1978.
2002-25-09: This amendment adopts a new airworthiness directive (AD) that applies to certain Air Tractor, Inc. (Air Tractor) Models AT-250, AT- 300, AT-301, AT-302, AT-400, AT-400A, AT-401, AT-401A, AT-402, AT-402A, AT-501, AT-502, and AT-502A airplanes. This AD requires you to install an overturn skid plate in the cockpit area. This AD is the result of reports of foreign material entering the cabin area during an overturn skid of the affected airplanes. The actions specified by this AD are intended to minimize the possibility of dirt or mud penetrating the cockpit in case of an aircraft overturn. Such mud and dirt penetration into the cockpit could lead to pilot asphyxia or injury.