Results
2004-18-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727, 727C, 727-100, -100C, and -200 series airplanes. This amendment requires an inspection of the forward trunnion attach fittings of the main landing gear (MLG), inspections of the attach fitting holes of the forward trunnion attach fittings if necessary, replacement of the forward trunnion attach fittings if necessary, and corrective actions if necessary. This action is necessary to detect and correct cracks and corrosion on the attach fitting holes of the forward trunnion attach fittings of the MLG, which could result in the collapse of the MLG. This action is intended to address the identified unsafe condition.
64-13-02: 64-13-02 FAIRCHILD: Amdt. 735 Part 507 Federal Register May 23, 1964. Applies to all Model F-27 Series Aircraft with Dowty Main Landing Gear Outer Cylinders P/N's 9010Y3, 9017Y1, 200020.609, 2.00021.241, 200021.276, 200042.302, 2.00042.303, 2.00042.601, and 2.00042.618. Compliance required as indicated. Due to failures of main landing gear outer cylinder torque link attach lugs, to which the upper torque link, Dowty P/N C9027Y3 is attached, the following measures are required: (a) Outer cylinders which have accumulated 8,000 or more landings as of the effective date of this AD, but have not been modified in accordance with either Fairchild Service Bulletin No. 32-41A dated April 5, 1961, or Dowty Service Bulletins No. 32-15 dated October 1961, or No. 32-11 issued August 1961, revised December 1962, or equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, must be inspected as follows: (1) Conduct a daily visual inspection for cracks in the vertical radii on the inboard and outboard sides of the main cylinder lug. (2) Inspect the area specified in (a)(1) using dye penetrant method or FAA approved equivalent inspection within the next 50 landings after the effective date of this AD, unless already accomplished within the last 250 landings, and every 300 landings after such inspection. (3) If cracks are found the following shall be accomplished: (i) A crack that can be removed by reworking the outer cylinder in accordance with Fairchild Service Bulletin No. 32-41A dated April 5, 1961, or Dowty Service Bulletins No. 32-15 dated October 1961, or No. 32-11 issued August 1961, revised December 1962, or equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, must be removed before further flight. (ii) If the crack cannot be removed as specified in (a)(3)(i), that cylinder must be replaced before further flight. (b) Outer cylinders modified in accordance with Fairchild Service Bulletin No. 32- 41A dated April 5, 1961, or equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, must be inspected as follows: (1) Conduct a daily visual inspection for cracks in the vertical radii on the inboard and outboard sides of the main cylinder lug. (2) Inspect the area specified in (b)(1) using dye penetrant method of FAA approved equivalent inspection within the next 50 landings after the effective date of this AD unless already accomplished within the last 250 landings, and every 300 landings after such inspection. (3) If cracks are found the following shall be accomplished: (i) A crack that can be removed by reworking the outer cylinder in accordance with Dowty Service Bulletins No. 32-15 dated October 1961, or equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, must be removed before further flight. (ii) If the crack cannot be removed as specified in (b)(3)(i), that cylinder must be replaced before further flight. (c) Outer cylinders modified in accordance with Dowty Service Bulletin No. 32-15 dated October 1961, or equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, must be inspected as follows: (1) Conduct a daily visual inspection for cracks in the vertical radii on the inboard and outboard sides of the main cylinder lug. (2) Inspect the area specified in (c)(1) using dye penetrant method or FAA approved equivalent inspection within the next 50 landings after the effective date of this AD unless already accomplished within the last 250 landings, and every 300 landings after such inspection. (3) If cracks are found, that cylinder must be replaced before further flight. (d) Outer cylinders modified after the accumulation of 7,000 landings, in accordance with Dowty Service Bulletin No. 32-11 issued August 1961, revised December 1962, or equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, must be inspected as follows: (1) Conduct a daily visual inspection for cracks in the vertical radii on the inboard and outboard sides of the main cylinder lug. (2) Inspect the area specified in (d)(1) using dye penetrant method or FAA approved equivalent inspection within the next 50 landings after the effective date of this AD unless already accomplished within the last 650 landings, and every 700 landings after such inspection. (3) If cracks are found, that cylinder must be replaced before further flight. (e) Outer cylinders modified prior to the accumulation of 7,000 landings in accordance with Dowty Service Bulletin No. 32-11 issued August 1961, revised December 1962, or equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, are not required to be inspected under this AD. (f) Where past records of landings have not been maintained or are unavailable, the number of landings prior to the effective date of this AD shall be estimated by substituting two (2) landings for each hour of time in service. Where the operator does not desire to keep a record of landings, the number of landings shall be estimated by substituting two (2) landings for each hour of time in service. (g) Compliance inspection times and affectivity paragraphs, specified in the service bulletins discussed herein, must be disregarded. (h) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. This supersedes AD 61-10-03. This directive effective June 26, 1964.
2007-17-05: This amendment adopts a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S92-A helicopters. This action requires, within a specified time, borescope inspecting a certain part-numbered tail rotor pitch change shaft and bearing assembly (shaft and bearing assembly) and also inspecting after any installation. This amendment is prompted by an incident involving failure of a shaft and bearing assembly and servo clevis shaft resulting in loss of tail rotor control. The actions specified in this AD are intended to prevent failure of a shaft and bearing assembly, loss of tail rotor pitch and yaw control, and subsequent loss of control of a helicopter.
79-14-02: 79-14-02 PIPER: Amendment 39-3510. Applies to Models PA-31, PA-31-300, PA-31-325 Serial Nos. 31-5 through 31-7912059; Model PA-31-350, Serial Nos. 31-5001 through 31- 7952111; Model PA-31P, Serial Nos. 31P-1 through 31P-7730012; Model PA-31T, Serial Nos. 31T-7400002 through 31T-7920060; and Model PA-31T1, Serial Nos. 31T-7804001 through 31T-7904033 certificated in all categories. To avoid possible separation of the control wheel control shaft stud from the control shaft tube due to the absence of two roll pins, and subsequent loss of aileron control of the affected control wheel, accomplish the following within the next 5 hours in service unless previously accomplished on the pilot and co-pilot control wheel assemblies: a. Secure control wheels in aft position. b. Gain access to the control shaft tube assembly (P/N 42939-00) and to stud (P/N 42938-00) connection, located just aft of the control wheel stop collar (P/N 40950-00). c. Inspect the forward end of the control shaft tube assembly (P/N 42939-00) to determine if two roll pins (P/N 480732) are installed. d. If one or both roll pins are missing, install as required, roll pin Piper P/N 480732, prior to further flight. Piper Service Bulletin No. 651 refers to this subject. This amendment is effective July 6, 1979, except as to recipients of the distribution dated May 3, 1979, which was effective upon receipt.
2013-03-23: We are adopting a new airworthiness directive (AD) for all Gulfstream Aerospace LP (Type Certificate Previously Held by Israel Aircraft Industries, Ltd.) Model Gulfstream G150 airplanes. This AD was prompted by a review that determined that the runway slope and anti-ice corrections to V1 and take-off distances in the Gulfstream G150 Airplane Flight Manual (AFM) were presented in a non-conservative manner. This AD requires revising the performance section of the AFM to include procedures to advise the flightcrew of certain runway slope and anti-ice corrections and take-off distance values. We are issuing this AD to prevent the use of published non-conservative data, which could result in the inability to meet the required take-off performance, with consequent hazard to safe operation during performance-limited take-off operations.
2001-06-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-600, -700, and -800 series airplanes. This action requires repetitive inspections of certain elevator hinge plates, and corrective action, if necessary. This action also provides for an optional replacement of the elevator hinge plates with new, improved hinge plates, which would end the repetitive inspections. This action is necessary to detect and correct fatigue cracking of the elevator hinge plates, which could lead to the loss of the attachment of the elevator to the horizontal stabilizer, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2001-06-02: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series -10 through -50, -61, -61F, -71, -71F airplanes, that currently requires a visual or eddy current inspection(s) of the left and right wing front spar lower caps to detect cracks migrating from attachment holes; and repair, if necessary. That AD also provides for an optional terminating modification of the front spar lower cap. This amendment is prompted by a report that additional cracking was found in the front spar lower cap of a wing. This amendment requires accomplishment of the previously optional terminating action. This amendment also expands the applicability of the existing AD to include additional airplanes and increases the interval for the repetitive eddy current inspections. The actions specified by this AD are intended to prevent reduced structural integrity of the left or right wing due to metal fatigue failure of the front spar lower cap.
79-12-11: 79-12-11 PIPER AIRCRAFT CORPORATION: Amendment 39-3490. Applies to Model PA-44-180, serial numbers 44-7995001 through 44-7995190 airplanes certificated in all categories. Compliance is required within the next 25 hours' time in service after the effective date of this AD or within 30 days after the effective date of this AD, whichever occurs first, unless already accomplished. To prevent a potential fire hazard due to fuel leakage from failed primer lines and cracked and broken fittings, accomplish the following on both engines: (a) Install the fuel primer modification kit, Piper Part Number 763 908V in accordance with Piper Service Bulletin 634 dated December 28, 1978, or later revision approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. (b) Make an appropriate maintenance record entry. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, FederalAviation Administration, Southern Region. This amendment becomes effective June 21, 1979.
2008-13-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: This Airworthiness Directive (AD) is prompted by the discovery on an in-service Mystere-Falcon 20-C5 of a collapsed wing anti-ice flexible hose due to internal ply separation. Consequences on the aircraft can be insufficient anti-icing not detected by the monitoring system. Ice accretion on the wing might then occur and might jeopardize the aircraft flight performance and safety. * * * * * The unsafe condition is undetected excessive ice build-up on the wings, which could interfere with controllability of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
2004-18-01: The FAA is adopting a new airworthiness directive (AD) for Hoffmann Propeller GmbH & Co KG (Hoffmann Propeller) models HO-V343 and HO-V343K propellers. This AD requires initial and repetitive visual inspections of propeller blades for blade shake and blade nut preload. This AD also requires initial and repetitive eddy current inspections of blade hubs for damage and cracks. This AD results from a report of a blade separating from either a model HO-V343 or HO-V343K propeller. We are issuing this AD to prevent propeller hub failure and blade separation due to an unknown root cause, leading to damage and possible loss of control of the airplane.
2001-05-08: This amendment adopts a new airworthiness directive (AD) that applies to all VALENTIN GmbH (Valentin) Model 17E sailplanes. This AD requires you to inspect for, and correct, cracked or improperly installed central wing bolts; install a stronger central bolt if not already installed; and inspect for, and replace, problem telescopic rods. 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 correct improperly installed or cracked central bolts and damaged, deformed, or loose telescopic rods. This condition, if not corrected, could cause the wing to separate from the sailplane, which could cause result in control of the sailplane.
79-12-09: 79-12-09 PIPER AIRCRAFT CORP: Amendment 39-3494. Applies to Model PA-36-285 serial numbers 36-7360001 through 36-7660135 airplanes certificated in all categories. To detect cracks in the engine mount attachment brackets, accomplish the following: (a) Within the next 50 hours in service from the effective date of this AD, unless accomplished within the previous 50 hours in service, and at intervals thereafter not to exceed 100 hours in service from the last inspection, inspect welds for cracks on the aft side of the gussets on the fuselage where the engine mount is attached using dye check or fluorescent penetrant inspection procedures or equivalent. (b) If cracks are found, install Piper Engine Mount Attachment Modification Kit No. 763877, or equivalent, prior to further flight. During the installation of the kit, inspect the welds for cracks on the forward side of the gussets on the fuselage where the engine mount is attached using dye check or fluorescent penetrantinspection procedures or equivalent. If cracks are found, remove weld from cracked area and reweld. (c) Upon incorporation of Piper Modification Kit No. 763877 or equivalent, compliance with this AD may be cancelled. (d) Equivalent inspections and repairs must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (e) 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. Piper S/B No. 615 dated 9/21/78, pertains to this subject. This amendment is effective June 19, 1979.
2007-17-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Deformations of cross sections of the rear exhaust pipes were stated on several serial numbers having logged varying operating hours. One strongly deformed exhaust pipe showed additional cracks near the welding. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
79-12-08: 79-12-08 PIPER: Amendment 39-3493. Applies to series PA-24-400 S/N 26-2 through 26-148; PA-30 S/N 30-2 through 30-2000; and PA-39 S/N 39-1 through 39-155 aircraft. PART A This part applies to all aircraft listed above. Compliance required within 50 hours of operation after the effective date of this AD and at each 50 hours of operation thereafter. To prevent fuel mismanagement from inter-port leakage with the fuel selector valve causing fuel to transfer from one tank to another, accomplish checks in accordance with the Instructions paragraph in Piper Service Letter No. 851, Part A or an approved equivalent. Item 3 is to be repeated only twice. If drainage still exceeds one half (1/2) fluid ounce of fuel then comply with Item 5. Item 5 is maintenance and must be performed by a certified mechanic. PART B This part applies to the cited Models PA-30 and PA-39 aircraft. If the airplane has been exposed to below freezing temperatures, compliance is required prior to the first flight of the day and after each refueling operation. To eliminate water contamination of the aircraft fuel supply, accomplish a check in accordance with the Instructions paragraph of Piper Service Letter 851, Part B, Item 2a and 2b or an approved equivalent check. PART C This part applies to the cited Model PA-24-400 aircraft. If the airplane has been exposed to below freezing temperatures, compliance is required prior to the first flight of the day and after each refueling operation. To eliminate water contamination of the aircraft fuel supply, accomplish a check in accordance with the Instructions paragraph in Piper Service Letter No. 851, Part C, Item 2a or an approved equivalent check. Upon submission of substantiating data through an FAA maintenance inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the repetitive intervals. The checks required by this AD may be performed by the pilot. Equivalent checks, inspections, and maintenance must be approved by Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective June 19, 1979.
2001-06-03: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A330-301, -321, and -322 series airplanes, and all Model A340 series airplanes. This action requires replacing, with oversize fasteners, the interference fit fasteners between ribs 2 and 7 and between ribs 9 and 11; and reinforcing the cover plate of the torsion box of the aft passenger/crew doors. This action is necessary to prevent propagation of fatigue cracking of the top wing skin and the torsion box of the aft passenger/crew doors, which could lead to reduced structural capability of the airplane. This action is intended to address the identified unsafe condition.
2019-18-04: The FAA is superseding Airworthiness Directive (AD) 2005-17- 14, which applied to all Airbus SAS Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4- 605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. AD 2005-17-14 required repetitive tests to detect desynchronization of the rudder servo actuators, and adjustment or replacement of the spring rods of the rudder servo actuators, if necessary. AD 2005-17-14 also required repetitive tests/inspections/analyses of the rudder servo actuators, and related investigative/corrective actions if necessary. This AD retains some requirements of AD 2005-17-14 and revises the inspection procedures and compliance times, as specified in a European Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by reports of desynchronization of the rudder servo actuators. The FAA is issuing this AD to address the unsafe condition on these products.
79-08-02: 79-08-02 PIPER: Amendment 39-3446. Applies to Model PA-38-112, Serial Nos. as shown below, certificated in all categories. To avoid possible hazards in flight associated with a crack in the stabilizer pulley bracket mounting fitting P/N 77615-07 or improperly torqued stabilizer to fin or fin to fuselage attaching bolts, accomplish the following: (a) Serial Nos. 38-78A0001 through 38-78A0040, 38-78A0042 through 38-78A0592, 38-78A0594, 38-78A0596, 38-78A0598 through 38-78A0620, 38-78A0622 through 38-78A0658, 38-78A0660 through 38-78A0714, 38-78A0716 through 38-78A0721, 38-78A0723 through 38-78A0735, 38-78A0737 through 38-78A0740, 38-78A0742, 38-78A0743, 38-78A0745 through 38-78A0766, 38-78A0768 through 38-78A0778, 38-78A0780 through 38-78A0784, 38-78A0787 through 38-78A0811, 38-78A0813, 38-78A0814, 38-78A0816, 38-78A0818, 38-78A0820, 38-78A0821, 38-78A0829, 38-78A0844, 38-79A0003 through 38-79A0005, 38-79A0007, 38-79A0008, 38-79A0010 through 38-79A0014, 38-79A0017 through38-79A0030, 38-79A0033 through 38-79A0036, 38-79A0038 through 38-79A0041, 38-79A0043 through 38-79A0047, 38-79A0049 through 38-79A0078, 38-79A0080 through 38-79A0089, 38-79A0092, 38-79A0093, 38-79A0095, 38-79A0097 through 38-79A0099, 38-79A0101 through 38-79A0110, 38-79A0112 through 38-79A0114, 38-79A0116, 38-79A0119 through 38-79A0121, 38-79A0123 through 38-79A0128, 38-79A0130 through 38-79A0132, 38-79A0135 through 38-79A0137, 38-79A0139, 38-79A0140, 38-79A0142 through 38-79A0148, 38-79A0150 through 38-79A0165, 38-79A0167, 38-79A0168, 38-79A0170, 38-79A0172 through 38-79A0175, 38-79A0177, 38-79A0179 through 38-79A0181, 38-79A0184 through 38-79A0189, 38-79A0191 through 38-79A0197, 38-79A0199, 38-79A0200, 38-79A0204 through 38-79A0206, 38-79A0208 through 38-79A0212, 38-79A0214, 38-79A0216, 38-79A0217, 38-79A0220 through 38-79A0222, 38-79A0226, 38-79A0229 through 38-79A0231, 38-79A0234 through 38-79A0236, 38-79A0238, 38-79A0240, 38-79A0242, 38-79A0246, 38-79A0248, 38-79A0250, 38-79A0253, 38-79A0259, 38-79A0271 through 38-79A0273, 38-79A0277, 38-79A0301, 38-79A0307 and 38-79A0312. Compliance required within the next ten hours in service unless previously accomplished. 1. Remove the dorsal fin forward fairing P/N 77606-03 and inspect the edges of the stabilizer pulley bracket mounting fitting P/N 77615-07 at the bend radius for cracks using a dye penetrant inspection method. 2. Report positive findings including crack length from paragraph (a) Inspection to Chief, Engineering and Manufacturing Branch, FAA, Eastern Region within ten days of inspection. (Reporting approved by Office of Management and Budget under OMB No. 04-RO174.) 3. If a cracked fitting is found, replace with an undamaged part of the same part number before further flight except a ferry flight under FAR 21.197 to a place of repair may be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (b) Serial Nos. 38-78A0001 through 38-79A0254. Compliance required within the next 100 hours in service unless previously accomplished. 1. Disconnect rudder cables from rudder, remove lower rudder hinge bolt and displace rudder to gain access to rear spar attachment bolts. 2. Remove lower vertical fin fairing, upper vertical fin fairing, upper vertical fin inspection panel and lower aft vertical fin inspection panel. 3. Using a calibrated torque wrench, check the torque of each of eighteen (18) stabilizer to fin and fin to fuselage attach bolts and tighten as required to 90-110 in-lbs. Torque value given takes into account friction drag torque. (Piper Service Bulletin No. 637 refers to the subject.) This amendment is effective April 12, 1979.
2007-17-08: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Instead of the hub normally used which carries the starter ring gear and the hub for the tooth belt a slip-clutch can be mounted. The unit contains the hub for the tooth belt and the starter ring gear. Occurrences during service have shown that under bad conditions excessive wear on several parts of the clutch can occur. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
56-25-04: 56-25-04 LOCKHEED: Applies to All Models 49, 149, 649, 649A, 749, 749A Aircraft; Model 1049 Serial Numbers 4001 Through 4024; Model 1049C Serial Numbers 4501 Through 4520 and 4523 Through 4538. Compliance required at first block overhaul following receipt of parts or by March 1, 1958, whichever occurs first. In view of the continuing series of incidents wherein flaps extend on one side of the aircraft out of symmetry with the other side, a means shall be installed which will automatically shut off the hydraulic power to the flap actuating motors whenever an asymmetrical condition exists. One method of accomplishing this means is described in Lockheed Service Bulletin No. 49/SB-794 for the 49/749 Series and No. 1049/SB-2270 for the 1049 Series.
2018-07-05: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) CF6-80A, -80A1, -80A2, and -80A3 turbofan engines. This AD was prompted by high cycle fatigue (HCF) cracking of the low-pressure turbine (LPT) stage 3 nozzles. This AD requires replacement of the LPT stage 3 nozzles, part numbers (P/Ns) 9290M52P05 and 9290M52P06, installed. We are issuing this AD to address the unsafe condition on these products.
2001-05-10: This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-10 and MD-11 series airplanes, and KC-10A (military) airplanes, that requires installation of thrust reverser interlocks on certain airplanes, inspections of the thrust reverser systems to detect discrepancies on certain other airplanes, and corrective actions, if necessary. This amendment is prompted by a determination that the current thrust reverser systems do not adequately preclude unwanted deployment of a thrust reverser. The actions specified by this AD are intended to prevent unwanted deployment of a thrust reverser, which could result in reduced controllability of the airplane.
79-07-02: 79-07-02 ESB WISCO, INCORPORATED: Amendment 39-3442. EXIDE AC 78M and WILLARD W 78M BATTERIES. Applies to those batteries manufactured during December 1978, January and February 1979, identified by the figures N-8, A-9, or B-9 stamped on either terminal post. They may be installed in, but not limited to, the following aircraft: Aero Commander 1960 on - various models, Bellanca 1959 on - various models, Callair 1964 on - various models, Champion 7 series models: 7GC, 7HC, etc., Enstrom F-28 series, possible other models, Helio All series, Lake Amphibian Model C-1 and LA-4, Navion Rangemaster and others, Piper Cherokee and Pawnee PA-28 and PA-25, but not limited to these models, Rockwell All models, Stinson All models, Wing Derringer models. Compliance is required as follows. Remove from service before next flight and replace with any approved battery of comparable rating. This amendment becomes effective April 3, 1979.
2007-17-02: We are adopting a new airworthiness directive (AD) to supersede AD 82-07-04, which applies to certain Allied Ag Cat Productions, Inc. (Ag Cat) G-164 series airplanes. AD 82-07-04 currently requires you to modify the fuel shut-off valve control by installing a new stop-plate. Since we issued AD 82-07-04, we have determined the need to add airplane models and serial numbers that were not previously included in the Applicability section. Consequently, this AD retains the actions of AD 82-07-04 and adds airplane models and serial numbers to the Applicability section. We are issuing this AD to prevent turning the fuel shut-off valve clockwise past the "ON'' position stop which, if not corrected, could allow the fuel valve to be rotated to an unplacarded "OFF'' position. This condition could lead to reduced fuel flow and consequent loss of engine power.
2019-18-03: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737 series airplanes, excluding Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires revising the existing maintenance or inspection program to remove text that allows the size of the thrust reverser upper locking actuator lock sensor target to be changed, and, for certain airplanes, performing repetitive integrity tests of the thrust reverser upper locking actuator. This AD was prompted by a report indicating that alteration of thrust reverser upper locking actuators in accordance with certain data in the Boeing aircraft maintenance manual (AMM) could delay or prevent detection of the failure of the locking mechanism of a thrust reverser upper locking actuator. The FAA is issuing this AD to address the unsafe condition on these products.
2001-05-09: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 430 helicopters that requires modifying the electrical system. This amendment is prompted by the loss of electrical power due to design deficiencies discovered during single-pilot Instrument Flight Rules (IFR) flight testing. The actions specified by this AD are intended to prevent loss of electrical power and subsequent loss of control of the helicopter.