Results
2001-03-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes and all Airbus Model A300-600 series airplanes, that requires a one-time high frequency eddy current inspection to detect cracking of the splice fitting at fuselage frame (FR) 47 between stringers 24 and 25; and corrective actions, if necessary. 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 cracking of the splice fitting at fuselage FR 47, which could result in reduced structural integrity of the airplane.
89-23-04: 89-23-04 AIRBUS INDUSTRIE: Amendment 39-6371. Docket No. 89-NM-92-AD. Applicability: Models A300, A310, and A300-600 series airplanes, certificated in any category. Compliance: Required within 30 days after the effective date of this AD, unless previously accomplished. To prevent pitch trim runaway, accomplish the following: A. Perform an inspection to determine if SAMM trim switches, Part Number BP 20- 455, Serial Numbers 110 to 923, inclusive, are fitted on the normal pitch trim electrical circuit, in accordance with All Operators Telex (AOT) 22/88/01, dated November 23, 1988. If any trim switch is determined to have any of these serial numbers, prior to further flight, replace the switch with a serviceable trim switch having a serial number 924 or higher, in accordance with Airplane Maintenance Manual (AMM) 22-27-12 (for Model A310 and A300-600 series airplanes) or AMM 27-11-11 (for Model A300 series airplanes), as appropriate. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6371, AD 89-23-04) becomes effective on December 1, 1989.
77-02-06: 77-02-06 PIPER: Amendment 39-2816. Applies to Model PA-36-285, Serial Nos. 36-7360003 through 36-7560044 certificated in all categories except aircraft incorporating Piper Kit Part Number 760 933. To prevent possible hazards in flight associated with elongation of bolt holes at the forward and/or aft wing attachment fittings, accomplish the following: (a) Within the next 50 hours in service from the effective date of this AD or upon the attainment of 500 total hours in service whichever is later unless previously accomplished within the past 500 hours in service, and at intervals not to exceed 500 hours in service from the last inspection, inspect and alter, if necessary, the forward and/or aft wing attachment fittings in accordance with the instructions section of Piper Service Bulletin No. 471A dated July 16, 1976, or equivalent. (b) Upon the incorporation of Wing Fitting Modification Kit, Piper Part Number 760 933 or equivalent, compliance with the requirementsof this AD may be dispensed with. (c) Equivalent inspections and repairs must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (d) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the inspection intervals specified in this AD. This amendment is effective January 28, 1977.
2007-13-17: We are adopting a new airworthiness directive (AD) that supersedes AD 2006-22-08, which applies to all Air Tractor, Inc. (Air Tractor) Models AT-602, AT-802, and AT-802A airplanes. AD 2006-22-08 currently requires you to repetitively inspect the engine mount for any cracks, repair or replace any cracked engine mount, and report any cracks found to the FAA. Since we issued AD 2006-22-08, the FAA has received reports of two Model AT- 802A airplanes with cracked engine mounts below the initial compliance time in AD 2006-22-08. The FAA has determined that an initial inspection is required when the airplane reaches a total of 1,300 hours time-in-service (TIS) instead of 4,000 hours TIS required by AD 2006- 22-08. Consequently, this AD retains the actions of AD 2006-22-08 while requiring the initial inspection when the airplane reaches a total of 1,300 hours TIS. We are issuing this AD to detect and correct cracks in the engine mount, which could result in failure of the engine mount. Such failure could lead to separation of the engine from the airplane.
2019-16-01: The FAA is adopting a new airworthiness directive (AD) for all International Aero Engines AG (IAE) V2525-D5 and V2528-D5 model turbofan engines. This AD was prompted by reports of cracked turbine exhaust cases (TECs). This AD requires initial and repetitive inspections of the affected TEC and, depending on the results of the inspections, its replacement with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
2001-04-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100, -200, and -300 series airplanes, that requires inspection to determine the orientation of the Wiggins fuel couplers of the fuel tank vent line and scavenge line in the right wing at station 249, and follow-on corrective actions. This amendment is necessary to prevent contact between the nuts of the Wiggins fuel couplers and the stiffener on the access panel of the upper surface of the right wing, which could compromise the lightning protection of the fuel tank of the right wing in the event of a lightning strike, and could result in possible fuel tank explosion. This action is intended to address the identified unsafe condition.
2001-04-04: This amendment adopts a new airworthiness directive (AD) that applies to all Dornier Luftfahrt GMBH (Dornier) Models 228-100, 228-101, 228-200, 228-201, 228-202, and 228-212 airplanes that have windshield spray nozzle option SCN 3109 installed. This AD requires you to deactivate the windshield spray nozzle heating elements. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent the windshield spray nozzle heating system from overheating, which could result in smoke in the cockpit and prompt the crew to initiate emergency actions.
2007-13-18: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: The aim of the Airworthiness Directive (AD) is to introduce a new life limit for engine and Nose Landing Gear (NLG) mounts installed on EADS SOCATA TB 9, TB 10 and TB 200 airplanes, as defined in the updated Airworthiness Limitations Section (ALS) of the relevant Aircraft Maintenance Manuals (AMM). We are issuing this AD to require actions to correct the unsafe condition on these products.
77-01-01: 77-01-01 PIPER AIRCRAFT CORPORATION: Amendment 39-2796. Applies to Model PA-28-140 serial numbers 28-7225001 through 7725086; Model PA-28-150/160/180 serial numbers 28-7205001 through 7505259; Model PA-28-151 serial numbers 28-7415001 through 7715200; Model PA-28-181 serial numbers 28-7690001 through 7790192; Model PA-28-235 serial numbers 28-721001 through 7610181; Model PA-28R-200 serial numbers 28R-7235001 through 7635459; Model PA-32-260 serial numbers 32-7200001 through 7700005; and Model PA-32-300 serial numbers 32-7240001 through 7740012 certificated in all categories. Compliance required as indicated. To prevent possible fuel exhaustion due to an erroneous fuel quantity gauge indication, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, unless (b) and/or (c) have been accomplished, attach the following Placard to the instrument panel near the fuel quantity gauges, in clear view of the pilot, using 1/8" minimum size type: "WARNING FUEL GAUGES MAY INDICATE AS MUCH AS 2 1/2 GALLONS WHEN TANKS ARE EMPTY." The placard may be fabricated by the owner/operator or Piper Part Number 35669-14 may be used. (b) Within the next 200 hours' time in service or 12 months, whichever occurs first, after the effective date of this AD, check each of the fuel quantity gauges for proper calibration in accordance with the following procedures. These checks may be performed by the pilot. (1) Place the airplane on a known level area in an approximately static level condition. (2) Insure that each fuel tank contains a minimum of five (5) gallons of fuel. (3) Start the engine and run at 1000 rpm for approximately two (2) minutes. Alternator portion of split master switch must be on. (4) Shut down the engine but leave the master switch on during steps (5), (6) and (7). (5) Defuel each airplane fuel tank. CAUTION: Insure that the aircraft and the defuelingvehicle are properly grounded and insure that proper fire protection equipment is available. (6) Repeat (3). (7) With the engine running, determine the fuel quantity indication for each gauge. (8) If the gauges indicate zero (0) or below, no further action is required. Return the airplane to service. (9) If a gauge indicates above zero (0), accomplish (c), or replace the erroneous gauge with a serviceable gauge, which has the appropriate Piper Part Number and is identified with a white dot on the lower right hand corner of the face. (c) The fuel quantity gauges that do not meet (b)(9) must be calibrated to a zero (0) indication in accordance with FAA approved Piper instructions by an FAA approved facility or by an FAA authorized Piper Aircraft Corporation employee. (d) When (b) and/or (c) have been accomplished, the placard required by (a) may be removed. (e) Alternate method of compliance must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. Piper Service Bulletin 533 also pertains to this same subject. This amendment becomes effective January 7, 1977.
76-19-07: 76-19-07 PIPER: Amendment 39-2733. Applies to Piper Models PA-24-250, Serial Nos. 24-1, 24-103 through 24-3641, and 24-3643 through 24-3687 and PA-24-260, Serial Nos. 24-3642, 24-4000 through 24-5047 certificated in all categories with Piper Kit Number 760 747 Stabilator Modification installed. To prevent possible hazards in flight associated with cracks occurring in the corners of the balance weight cutout of the stabilator balance weight tube assembly, accomplish the following within the next one hundred hours in service from the effective date of this AD unless previously accomplished. a. Replace the stabilator balance weight tube assembly in accordance with the directions contained in the "Instructions" section of Piper Service Bulletin Number 496 or approved equivalent replacement. b. Equivalent replacement must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective September 29, 1976.