Results
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.
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.
2002-06-13: This amendment adopts a new airworthiness directive (AD) applicable to certain McDonnell Douglas MD-90-30 airplanes. This action requires inspection of the power feeder cables on the left and right side of the aft cargo compartment between certain stations for minimum clearance from the adjacent structure and for the presence of a grommet in the lightening hole through the floor cusp, and corrective actions, if necessary. The actions specified by this AD are intended to detect and correct inadequate clearance of the power feeder cables on the left and right side of the aft cargo compartment, the lack of a grommet in the lightening hole through the floor cusp, and improper installation of the cabin sidewall grill during production. These conditions could lead to chafing of the power feeder cables, resulting in electrical arcing and possibly in a fire in the cargo compartment of the airplane. This action is intended to address the identified unsafe condition.
75-02-03: 75-02-03 PIPER AIRCRAFT CORPORATION: Amendment 39-2066. Applies to Piper Models PA-28-140, PA-28-150, PA-28-160, PA-28-180, PA-28-235, PA-32-260 and PA-32-300 airplanes, modified by installing a large nose wheel fork (Tibbetts-Herre Airmotive P/N PA-32-1) and an 8.00-6 nose wheel tire in accordance with Supplemental Type Certificate SA281AL, certificated in all categories. Compliance is required prior to the accumulation of 25 landings after the effective date of this AD, unless already accomplished. To prevent possible failure of the nose wheel fork assembly, accomplish the following: (a) Visually inspect the nose wheel fork for bends in the legs which are not part of the STC design. (b) Straighten any bends found in the inspection required by paragraph (a) of this AD, prior to the inspection required by paragraph (c) of this AD. (c) Inspect those nose wheel forks that have at any time been straightened in the past for cracks in the vicinity of the nosewheel axle holes, using a standard dye or fluorescent penetrant inspection procedure. To determine whether a nose wheel fork has been straightened in the past - (1) Check the aircraft maintenance records; and (2) Visually inspect the fork for any evidence of it having been straightened. (d) If no cracks are found in the inspection required by paragraph (c) of this AD, or the nose wheel fork is a fork excepted from the inspection required by paragraph (c) of this AD, chamfer and heat treat the nose wheel fork before further flight in accordance with paragraphs (f) and (g) of this AD. (e) If cracks are found in the inspection required by paragraph (c) of this AD, before further flight, replace the nose wheel fork with a serviceable nose wheel fork of the same part number which has been chamfered and heat treated in accordance with paragraphs (f) and (g) of this AD. (f) Chamfer the outside edge of each nose wheel fork axle hole at 45 degrees to a minimum depthof 1/32-inch prior to heat treating. (g) Heat treat the nose wheel fork to Ftu of 180,000 PSI in accordance with MIL-H- 6875 or an FAA approved equivalent. (h) Permanently stamp the letter "H" on each nose wheel fork heat treated in accordance with paragraph (g) of this AD, adjacent to the serial and part number stamps. (i) Replace each Piper P/N 20825-00 cap assembly with a Tibbetts-Herre P/N PA- 32-5 cap assembly or an equivalent approved by the Chief, Engineering and Manufacturing Field Office, FAA, Alaskan Region. (j) Replace the Tibbetts-Herre P/N PA-32-4 axle rod with a Tibbetts-Herre P/N PA- 32-6 axle rod or equivalent approved by the Chief, Engineering and Manufacturing Field Office, FAA, Alaskan Region, using AN365-624 nuts and AN960-616 washers. Note: For the purpose of complying with this AD, subject to acceptance by the assigned FAA Maintenance Inspector, the number of landings may be determined by dividing each airplane's hours' time in service bythe operator's fleet average time from takeoff to landing for the airplane type. This amendment is effective upon publication in the Federal Register as to all persons except those persons to whom it was made effective upon receipt of the airmail letter dated November 26, 1974, that contained this amendment.
2017-25-09: We are superseding Airworthiness Directive (AD) 2012-21-04, which applied to all Airbus Model A300 series airplanes; Model A310 series airplanes; and 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). AD 2012-21-04 required repetitive inspections for, and replacement of, any cracked hood halves of fuel pump canisters. Since we issued AD 2012-21-04, we allowed inspections of the wing-outer tank and trim tank fuel pump canister hood halves to be terminated. This new AD retains the requirements of AD 2012-21-04, reinstates the terminated inspections, and adds optional terminating actions. This AD was prompted by reports of cracked fuel pump canister hoods located in fuel tanks and new in-service events of wing-outer tank fuel pump canister hood cracking. We are issuing this AD to address the unsafe condition on these products.
2002-06-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2002-06-51 that was sent previously to all known U.S. owners and operators of certain Bombardier Model CL-600-2C10 (Regional Jet Series 700 and 701) series airplanes by individual notices. This AD requires revising the Airplane Flight Manual to provide procedures for addressing uncommanded transfer of fuel from wing fuel tanks to center fuel tank. This action also requires revising the Minimum Equipment List (MEL); limiting operation of the airplane to flight within 60 minutes of a suitable alternative airport; and ensuring that normal mission fuel requirements are increased by 3,000 pounds. This action was prompted by reports of uncommanded fuel transfer between the wing fuel tanks and the center fuel tank. The actions specified by this AD are intended to ensure that the flight crew has the procedures necessary to address such uncommanded fuel transfer, which could cause the center tank to overfill, and fuel to leak from the center tank vent system or to become inaccessible, and result in engine fuel starvation.
63-17-02: 63-17-02 FAIRCHILD: Amdt. 602 Part 507 Federal Register August 14, 1963. Applies to Model F-27 Series Aircraft on which a Walter Kidde Spur Gear Nose Wheel Steering Actuator Assembly, P/N 891800 (STC SA1-574), has been installed. Compliance required as indicated. Due to failures of the mounting bolts, P/N's 244241 and 245804 in the nose gear pivot bracket, accomplish the following: (a) On all affected aircraft that have not had the subject steering actuator assembly modified in accordance with Walter Kidde and Company, Inc., Service Bulletin No. 143 dated October 1962, or FAA approved equivalent, accomplish the following within the next 250 hours' time in service after the effective date of this AD and at intervals thereafter not to exceed 250 hours' time in service from the last inspection: (1) Inspect the 4 mounting bolts, P/N's 244241 and/or 245804, for cracks using dye penetrant methods in conjunction withat least a 10-power magnifying lens, or FAA approved equivalent inspection. Give particular attention to the necked-down area of the bolt where the shank meets the threads. Inspection may be accomplished without jacking-up the aircraft only if one bolt at a time is removed, inspected, and then replaced and properly torqued, before inspection of the second bolt is attempted. (b) If a crack is found, accomplish one of the following before further flight except that a ferry flight may be made in accordance with the provisions of CAR 1.76. (1) Replace any cracked bolt with a new one of the same type or an FAA approved equivalent and continue inspecting in accordance with (a) or (2) Modify the subject steering actuator assembly in accordance with Walter Kidde and Company, Inc., Service Bulletin No. 143 dated October 1962, or an FAA approved equivalent. (c) The repetitive inspections of the steering actuator assembly, as prescribed in (a) may be discontinued on aircraft modified in accordance with (b)(2) or an FAA approved equivalent. (d) 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. (Walter Kidde and Company, Inc. Service Bulletin No. 143 dated October, 1962, covers this subject.) This directive effective September 13, 1963.