Results
77-12-02: 77-12-02 PIPER: Amendment 39-2915 as amended by Amendment 39-3161. Applies to Piper Models PA-31 and PA-31-300 airplanes which have wing luggage lockers installed per STC SA986SW certificated in all categories. Compliance required as indicated. Within the next 25 hours in service or at the next annual inspection, whichever occurs first, after the effective date unless already accomplished, inspect the elevator balance weights for security of attachment ("rivnut pullup") or remove these weights and check elevator unbalance (108 in-lbs. tail heavy maximum) and repair or rebalance elevator, as necessary, in accordance with Nayak Service Bulletin No. 1, dated May 16, 1977, or later approved revisions or in accordance with an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. Amendment 39-2915 became effective June 17, 1977. This amendment 39-3161 becomes effective April 10, 1978.
2019-16-03: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report of a front engine mount primary pin which moved axially out of place; investigation revealed that incorrect washers had been installed on the engine mount pins. This AD requires a one-time inspection of the washers installed on the front and rear engine mount primary pins and thrust link pins of both engines, depending on configuration, and corrective actions if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2010-05-09: 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: A number of propeller blade outer sleeves have been found with cracks since 1996. Testing has shown that blade retention integrity is not affected by this cracking. However, this condition, if not detected and corrected, can lead to blade counterweight release, possibly resulting in damage to the aircraft and injury to occupants or persons on the ground. We are issuing this AD to prevent blade counterweight release, which could result in injury or damage to the airplane.
2007-15-01: 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: In-service reports have been received by BAE of failed bolts fitted to frame 199 wing spigot post assembly. If left uncorrected failure of these bolts will severely compromise the structural integrity of the wing to fuselage attachment. Failure of which would lead to loss of the aircraft. We are issuing this AD to require actions to correct the unsafe condition on these products.
2018-05-07: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 787-8 and 787-9 airplanes. This AD was prompted by a flight test report indicating that the crew oxygen masks in the flight deck did not deploy correctly. This AD requires an inspection at four locations in the flight deck to determine whether any crew oxygen mask having a certain part number is installed, and replacement of affected crew oxygen masks. We are issuing this AD to address the unsafe condition on these products.
96-20-09: This amendment adopts a new airworthiness directive (AD), applicable to all Jetstream Model HS 748 series airplanes. This action requires a one-time inspection to ensure proper operation, positioning, and lubrication of the aileron, rudder, and elevator cable tensioners; gust lock levers; and cable pressure seals. It also requires a revision to the maintenance program to include these inspections on a repetitive basis. This amendment is prompted by reports of seizure and consequent jamming of the flight control cable tension regulators and gust lock mechanisms. The actions specified in this AD are intended to prevent the flight control cable tension regulators from jamming, which could result in the inability to achieve full deflection of the associated flight control surfaces, and lead to reduced controllability of the airplane.
2007-14-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A330 and A340 airplanes. This AD requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors caused by latent failures, alterations, repairs, or maintenance actions, could result in fuel tank explosions and consequent loss of the airplane.
2001-04-05: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Beech Model 1900D airplanes that are equipped with a KLN-90B Global Positioning System (GPS) incorporated in accordance with AlliedSignal Supplemental Type Certificate (STC) SA00245WI-D. This AD requires rewiring the KLN-90B GPS to eliminate the possibility of inconsistent NAV "FLAG" displays. This AD is the result of an instance where the copilot's NAV "FLAG" display was based on the pilot's NAV source validity. The actions specified by this AD are intended to assure that the copilot's NAV "FLAG" displays are based on the copilot's selected NAV source. Inconsistent NAV "FLAG" displays could cause the copilot to make decisions based on an invalid GPS source without knowing it was invalid.
2018-05-05: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model MYSTERE-FALCON 900, FALCON 900EX, FALCON 2000, and FALCON 2000EX airplanes. This AD was prompted by reports of a loose screw on certain slat mechanical stop assemblies, and punctures in certain fuel caps. This AD requires a one-time inspection, and corrective action if necessary. We are issuing this AD to address the unsafe condition on these products.
2001-03-08: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 series airplanes, that currently requires, among other actions, certain revisions to the Airplane Flight Manual; and removal of all elevator flutter dampers. That AD also requires installation of new elevator flutter dampers, and replacement of shear pins and shear links with new improved shear pins and shear links. This amendment adds airplanes to the applicability of the existing AD; and requires replacing certain shear pins with new, improved shear pins; and, for certain airplanes, inspection of the maintenance records to determine replacement status of the shear pins; 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 prevent premature failure of the shear pins of the elevator damper, which may increase the likelihood of jamming or restricting movement of the elevator and the resultant adverse effect on controllability of the airplane.
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.
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.
2001-03-11: This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace HP137 Mk1, Jetstream series 200, and Jetstream Models 3101 and 3201 airplanes that are equipped with certain main landing gear (MLG) radius rods. This AD requires inspection of the MLG radius rods for cracks and replacement of any cracked rod. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to detect and correct cracks in the MLG radius rods. Such cracks could result in MLG failure during takeoff, landing, or taxi operations, with consequent loss of airplane control.
76-18-05: 76-18-05 PIPER: Amendment 39-2715. Applies to Models PA-30, Serial Nos. 30-1 through 30-2000, and PA-39, Serial Nos. 39-1 through 39-155 certificated in all categories. To prevent possible hazards in flight associated with cracks in the radius of the bend relief holes of the forward fin attachment channel assembly accomplish the following within the next 50 hours in service from the effective date of this AD unless previously accomplished. a. Visually inspect the forward fin attachment channel P/N 22903-00 around the radius of the bend relief cutouts for cracks using a magnifying glass of at least five power or an approved equivalent inspection. b. Cracked parts must be replaced with a part of the same number or equivalent that has been inspected in accordance with this AD and found acceptable prior to further flight, except that the Airplane may be flown in accordance with FAR 21.197 to a base where a repair can be made. c. Equivalent inspections and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (Piper Service Letter No. 777 refers to this subject.) This amendment is effective September 10, 1976.