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75-16-04: 75-16-04 PIPER AIRCRAFT CORPORATION: Amendment 39-2272. Applies to PA-28-151 airplanes serial numbers 28-7415001 through 28-7515425; certificated in all categories. Compliance required within the next 50 hours' time in service or at the next scheduled inspection, whichever occurs first, after the effective date of this AD, unless already accomplished. To prevent over-travel of the carburetor air box valve, accomplish the following or accomplish an alternate modification method approved by the Chief, Engineering and Manufacturing Branch, Southern Region. (1) Remove lower nose cowl and metal bottom panel for access to the carburetor air box. (2) Loosen clamps attaching carburetor heat and induction air hoses to air box. Remove hoses from air box. (3) Remove control cable from bracket and lever on air box. Retain all hardware except cotter pin for reinstallation. (4) Remove air box bottom and valve by removing (12) #6 screws, nuts, and washers around the bottom of the air box. Retain the air box bottom and valve and attaching hardware for reinstallation. (5) Remove safety wire securing (4) MS20074-04-04 bolts which mount air box to carburetor. Remove the bolts and AN936A416 washers. Remove air box from carburetor. Remove and discard old 73451-07 gasket, but retain mounting hardware for reinstallation. (6) Install (2) plates, Piper Part Number 35646002, to top stiffener, secured with 8 (4 each plate) MS28470AL3-4 (Piper P/N 420-201) rivets. Installation must prevent valve over- travel. (7) Install new gasket Piper P/N 73451-07, and reworked air box on carburetor using (4) MS20874-04-04 bolts and AN936A416 washers. Safety wire bolts. (8) Reinstall bottom and valve assembly to air box using (12) #6 screws, nuts, and washers previously removed. Insure lever on valve is on the same side of box as control cable bracket. (9) Reinstall control cable. Tighten the swivel fitting nut to draw the core wire into the recess 1/2 its diameter. (10) Reinstall carburetor heat and induction air hoses on air box and secure with clamps. (11) Replace cowling and metal bottom panel. Piper Service Bulletin 474 also pertains to this same subject. This amendment becomes effective July 30, 1975.
2002-06-14: This amendment adopts a new airworthiness directive (AD) applicable to certain McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F (KC-10A and KDC-10), -40, and -40F series airplanes; and Model MD-10-10F and MD-10-30F series airplanes. This action requires an inspection of the parallel power feeder cables of the number 2 generator for chafing or structure damage; repositioning of the cables; and repair, if necessary. This action is necessary to prevent wire chafing of the parallel power feeder cables of the number 2 generator, which, if not corrected, could result in electrical arcing and damage to adjacent structure, and consequent smoke and/or fire in the aft door panel area. This action is intended to address the identified unsafe condition.
75-11-05: 75-11-05 PIPER: Amendment 39-2205. Applies to model PA-23-250 Airplane Serial Numbers 27-7554001 through 27-7554060, certificated in all categories. Unless already accomplished, within the next 50 hours in service after the effective date of this AD, accomplish the following: Replace the existing instrument glare shield panel in accordance with the installation instructions in Piper Kit No. 760 932 or with equivalent parts which 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 time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Service Bulletin No. 452 pertains to the same subject. This amendment is effective May 20, 1975.
2023-05-11: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by a report that in case of a flap, slat, or slat- flap failure in flight, resetting the slat flap control unit (SFCU) to clear the error using the airplane flight manual (AFM) could result in the stall protection computer (SPC) setting the low-speed cue to the most conservative stall advance mode. This AD requires revising the non-normal procedures section of the existing AFM to provide the flightcrew with procedures for addressing failure warnings in the slat and flap control systems. The FAA is issuing this AD to address the unsafe condition on these products.
75-09-18:
2002-06-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 and -300 series airplanes. This action requires replacement of the switch guard on the switch used to control the passenger and/or therapeutic oxygen system with a new, improved switch guard. This action is necessary to prevent displacement of the passenger/therapeutic oxygen switch, which could result in the unavailability of supplemental/therapeutic oxygen and possible incapacitation of passengers during flight. This action is intended to address the identified unsafe condition.
75-12-10: 75-12-10 COLLINS: Amendment 39-2232. Applies to Collins AP106 Autopilots which may be installed on Aero Commander Models 500S and 690A; Beech Models 60, A60, B60, 95-C55, 95-C55A, D55, D55A, E55, E55A and A36; DeHavilland Model DHC-6; Piper Models PA 31-350 and PA 31-325; and Swearingen Models SA 226-AT and SA 226-TC, airplanes. Compliance: Required as indicated, unless already accomplished. To prevent failure in multiple servos, accomplish the following: A. Within the next 10 hours" time in service after the effective date of this AD, check the modification information plate on the 161H-1 programmer (P/N 622-1036-001), which is part of the AP106 Autopilot, to determine if the unit has been modified in accordance with Collins Service Bulletin No. 6, or approved revisions. If so modified, make an appropriate entry in the aircraft records indicating compliance with this AD. B. If the 161H-1 programmer has not been modified in accordance with Collins Service Bulletin No. 6, or approved revisions, prior to further flight, disable the roll and pitch servo axes by placing a collar over the circuit breakers, if installed, or remove and tie back the connector from the roll and pitch servos, and in either case install a placard in plain view of the pilot which reads: "DO NOT ENGAGE AUTOPILOT" and operate the aircraft in accordance with this limitation. C. On or before December 1, 1975, modify all the 161H-1 programmers in accordance with Collins Service Bulletin No. 6. D. Any alternate means of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective June 11, 1975, to all persons except those to whom it was made effective earlier by air mail letter issued May 15, 1975.
2023-05-14: The FAA is superseding Airworthiness Directive (AD) 2022-06- 02, which applied to all Airbus SAS Model A318-111, and -112 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2022-06-02 required new repetitive inspections of the 80 view unit (80VU) rack lower lateral fittings, lower central support, upper fittings, central post, and shelves attachments for discrepancies, and corrective actions if necessary. This AD was prompted by a determination that the compliances times must be revised to address the unsafe condition. This AD continues to require the actions in AD 2022- 06-02 with revised compliance times, 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.
2025-10-12: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320 series airplanes; Model A321-211, -212, -213, - 231, -232, -251N, -251NX, -252N, -252NX, -253N, -253NX, -253NY, -271N, -271NX, -272N, and -272NX airplanes; Airbus SAS Model A330-200 series airplanes; Model A330-300 series airplanes; Model A330-800 series airplanes; Model A330-900 series airplanes; Model A350-941 and -1041 airplanes; and Model A380-800 series airplanes. This AD was prompted by a report of corrosion and cracks on the broadband antenna adapter plate during an inspection. This AD requires repetitive general visual inspections of the broadband antenna adapter plate, skirt, vents, and attachment fittings, and applicable corrective actions, and limits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
75-05-02: 75-05-02 BEECH, CESSNA, NAVION AND PIPER: Amendment 39-2095. Applies to Beech Models 35, A35, B35, C35, D35, E35, F35, G35, 35R, 35-33, 35-A33, 35-B33, 35-C33, 35-C33A, E33, E33A, E33C, F33, F33A, F33C, G33, H35, J35, K35, M35, N35, P35, S35, V35, V35A, V35B, 36, A36 series airplanes; Piper Models PA24, PA24-250, PA24-260 series airplanes; Navion Model Navion A series airplanes; Cessna Models 182, 182A, 182B, 182C, 182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P series airplanes certificated in all categories which have been modified in accordance with STC SA2653WE. Compliance required as indicated unless already accomplished. To prevent loss of engine oil, improper engine lubrication or engine oil contamination, accomplish the following: (a) Within the next 25 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 25 hours' time in service, unless (b) has been accomplished, remove the Beryl Aviation airoil separator Filtrator Assembly and inspect in accordance with the following procedure. (1) Add one quart of clear gasoline to the assembly can and plug or cap the ends of all tubes. (2) Hold the assembly can upright and shake vigorously for about two minutes. (3) Completely drain the gasoline from the 1/8 inch oil return tube through a paint strainer or similar fine mesh strainer and check for the presence of polyester urethane particles that have broken off of the internal screen material. (4) If screen particles are present, accomplish (b). (5) If screen particles are not present, install a 1/8 inch rivet in the top center of the assembly can to fasten the inside center cone to the outside can. Seal the rivet with an oil and fuel resistant type sealant if required. After assuring that cleaning agent has evaporated, reinstall the filtrator assembly. (b) Within the next 100 hours' time in service after the effective date of this AD, unless alreadyaccomplished, accomplish (1), (2), or (3). (1) (i) For Beech Models 35, A35, B35, C35, D35, E35, F35, G35 and 35R Series Airplanes, remove the Beryl Aviation filtrator assembly P/N B-1119-1 and install either P/N B-1119-M or P/N B-1119-RM. (ii) For Beech Models S35, V35, V35A, V35B, 35C-33A, E33A, E33C, F33A, F33C, 36 and A36 Series Airplanes, remove the Beryl Aviation filtrator assembly P/N B-1116-1 and install either P/N B-1116-M or P/N B-1116-RM. (iii) For Beech Models H35, J35, K35, M35, N35, P35, 35-33, 35-A33, 35-B33, 35-C33, E33, F33 and G33 Series Airplanes, remove the Beryl Aviation filtrator assembly P/N B-1114-1 and install either P/N B-1114-M or P/N B-1114-RM. (iv) For Piper Models PA24, PA24-250, and PA24-260 Series Airplanes, remove the Beryl Aviation filtrator assembly P/N B-1113-1 and install either P/N B-1113-M or P/N B-1113-RM. (v) For Navion Model A Series Airplanes, remove the Beryl Aviation filtrator assembly P/N B-1112-1 and install either P/N B-1112-M or P/N B-1112-RM. (vi) For Cessna Models 182, 182A, 182B, 182C, 182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N and 182P Series Airplanes, remove the Beryl Aviation filtrator assembly P/N B-1114-1 and install either P/N B-1114-M or P/N B-1114-RM. (2) Remove the modification incorporated by STC SA2653WE and return airplane to the standard unmodified configuration. (3) Provide compliance with an equivalent method approved by Chief, Engineering and Manufacturing Branch, Southern Region. Beryl Aviation Specialties, Route 1, Box 127D, Leesburg, Florida 32748, Service Bulletin B-1-1-75-1 also pertains to this subject. This amendment becomes effective February 21, 1975.