Results
77-08-02: 77-08-02 PIPER: Amendment 39-2874 as amended by Amendment 39-3074. Applies to PA-31, PA-31-300 and PA-31-325, S/Nos. 31-752 thru 31-7712010; PA-31-350, S/Nos. 31-5001 thru 31-7752028; PA-31P, S/Nos. 31P-67 thru 31P-7730001; PA-31T, S/Nos. 31T-7400002 thru 31T-7720008. Compliance required within the next 50 hours in service after the effective date of this AD unless already accomplished. To avoid an electrical short between the Pilot/Copilot Microphone and Phone Jack Relay and mounting bracket, comply as follows: (a) Key both the pilot and copilot microphone at the same time. If you can transmit through the pilot's microphone, the subject relay is not installed in the aircraft and no further action is required. (b) If the relay is installed, comply with the "Instructions" paragraph of Piper Service Bulletin No. 526A, dated July 25, 1977, or with an approved equivalent method. Upon request with substantiating data submitted through an FAA Maintenance Inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, who must also approve equivalent methods of compliance. Amendment 39-2874 become effective April 20, 1977. This amendment 39-3074 is effective November 15, 1977.
2007-14-03: We are adopting a new airworthiness directive (AD) for certain Cirrus Design Corporation (CDC) Models SR20 and SR22 airplanes. This AD requires you to replace the pick-up collar support and nylon screws, of the Cirrus Airplane Parachute System (CAPS), with a new design pick-up collar support and custom tension screws. This AD results from a CDC report of an in-flight CAPS activation where the parachute failed to successfully deploy. We are issuing this AD to correct pick-up collar support fasteners of the CAPS, which could result in the premature separation of the collar. This condition, if not corrected, could result in the parachute failing to successfully deploy (CAPS failure).
2019-14-15: The FAA is superseding Airworthiness Directive (AD) 2017-25- 12, which applied to all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2017-25-12 required repetitive inspections for cracking of the webs of the stub beams at certain fuselage stations (STAs), and applicable on-condition actions. This AD also requires repetitive inspections to include certain other fuselage stations for cracking of the stub beams, repetitive inspections for existing repairs at certain locations, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
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.