Results
2017-16-03: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. (Piper) Model PA-46-600TP (M600) airplanes. This AD requires inspection of the aft wing spars with repair as necessary. This AD was prompted by a report from Piper of the aft wing spar cracking during wing assembly. We are issuing this AD to address the unsafe condition on these products.
87-13-06: 87-13-06 BRITISH AEROSPACE (BAe): Amendment 39-5657. Applies to HP 137 Mk1, Jetstream Series 200, and Jetstream Model 3101 (includes Model 3100) (all serial numbers) airplanes equipped with main landing gear legs, Type Nos. 1863, 1863/4A, 1863/4B, 1863/4C, B00A702850A, and B00A702925A for left-hand installation and Type Nos. 1864, 1864/4A, 1864/4B, 1864/4C, B00A702851A, and B00A702926A for right-hand installation, certificated in any category. Compliance as required in Table 1 below, unless already accomplished: TABLE 1 INSPECTION THRESHOLD CRITERIA CUMULATIVE SERVICE CRITERIA FOR INITIAL INSPECTION CRITERIA FOR RECURRING INSPECT ION Less than 13,229 lb. MGTW* 13,229- 14,550 lb. MGTW* 14,551- 15,322 lb. MGTW* ALL WEIGHTS No record of Landings 9,500 hours 7,000 hours 6,000 hours 500 hours Aircraft Landings Recorded 19,000 Landings 14,000 Landings 12,000 Landings 1,000 Landings Gear Component Landings Recorded 19,000 Landings 14,000 Landings 12,000 Landings 1,000 Landings Installed Overhauled Gear** Within 30 days Within 30 days Within 30 days 1,000 Landings Spare Gear** Prior To Installation Prior To Installation Prior To Installation 1,000 Landings * Maximum (Certificated) Gross Takeoff Weight ** With No Record of Landings And No Compliance To S/B 32-JA860812 To prevent loss of ground directional control, collapse, or failure of the main landing gear, accomplish the following: (a) Inspect the main landing gear legs using non-destructive test (NDT) procedures described in BAe Air Weapons Division, S/B 32-32 dated July 22, 1986, initially within 30 days after the effective date of this AD or the inspection threshold criteria specified in Table 1 of this AD, whichever occurs later, and thereafter at the recurring interval specified in Table 1 of this AD. (b) If indications of cracks are found, prior to further flight, replace the gear with a serviceable unit. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) The intervals between repetitive inspections required by this AD may be adjusted up to 20 percent of the specified interval to allow accomplishment of these inspections concurrent with other scheduled maintenance of the airplane. (e) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium; Telephone (322) 513.38.30. All persons affected by this directive may obtain copies of the documents referred to herein upon request to British Aerospace plc, Manager, Product Support, Civil Aircraft Division, Prestwick Airport, Ayrshire, KA9 2RW, Scotland; or British Aerospace, Inc., Technical Librarian, Box 17414, Dulles International Airport, Washington, D.C. 20041; or may examine the documents referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on June 30, 1987.
2025-10-02: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model EC225LP helicopters. This AD was prompted by the identification of missing electrical bonding on a certain part-numbered additional and optional search light (search light). This AD requires installing an electrical bonding braid modification. These actions are 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.
2010-25-06: We are adopting a new airworthiness directive (AD) for certain Model 737-200, -300, -400, and -500 series airplanes. This AD requires repetitive inspections for cracking of certain fuselage frames and stub beams, and corrective actions if necessary. This AD also provides for an optional repair, which would terminate the repetitive inspections. For airplanes on which a certain repair is done, this AD also requires repetitive inspections for cracking of certain fuselage frames and stub beams, and corrective actions if necessary. This AD results from reports of the detection of fatigue cracks at certain frame sections, in addition to stub beam cracking, caused by high flight cycle stresses from both pressurization and maneuver loads. We are issuing this AD to detect and correct fatigue cracking of certain fuselage frames and stub beams and possible severed frames, which could result in reduced structural integrity of the frames. This reduced structural integrity can increase loading in the fuselage skin, which will accelerate skin crack growth and could result in rapid decompression of the fuselage.
2001-26-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 series airplanes, that requires removal of the shear pins that keep the rear fixed panels on the center landing gear closed and installation of new solid shear pins. This amendment is prompted by issuance of mandatory continuing airworthiness information from a foreign airworthiness authority. This action is intended to prevent the shear pins on the rear fixed panels of the center landing gear from failing, which could result in loss of the panels during flight with consequent injury to people on the ground. This action is intended to address the identified unsafe condition.
82-24-01: 82-24-01 ENSTROM HELICOPTER CORPORATION: Amendment 39-4497. Applies to Model F-28A, F-28C, F-28F, 280, 280C, and 280F helicopters certificated in all categories. Compliance required as indicated unless already accomplished. To prevent possible in-flight drivebelt clutch disengagement, accomplish the following: (a) Before further flight after the effective date of this AD, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection: (1) Inspect the drivebelt clutch mechanism, in accordance with Enstrom Service Information Letter 0080, Revision A, dated August 4, 1982, or FAA approved equivalent, and the Maintenance/Manual Supplement for the respective Models, to ascertain that the mechanism is properly rigged. NOTE: When properly rigged the clutch actuating cable should move freely allowing full clutch engagement. Clutch mechanisms experiencing binding of the clutch actuating cable, although properly rigged and lubricated, may have lubricant hardened in the cable assembly due to engine heat. (2) Replace any cable found to bind, preventing full clutch engagement, prior to further flight with suitable airworthy parts. (3) Lubricated the clutch actuating cable with Aero Shell 14 or FAA approved equivalent. (b) Within the next 25 hours' time in service after the effective date of this AD, unless already accomplished, install clutch cable heat shield P/N 28-16542-11 in accordance with Enstrom Service Directive Bulletin 0055, Revision A, dated April 2, 1982, or FAA approved equivalent. NOTE: Enstrom Helicopter Models equipped with right pilot-in-command kits P/N 28- 01002 or P/N 28-01012; or electric clutch actuator kit P/N 28-01005 are exempt from this paragraph. (c) Within the next 50 hours' time in service after the effective date of this AD, unless already accomplished, install clutch engagement overcenter lock warning light kit P/N 28- 19035-3 in accordance with EnstromService Directive Bulletin 0061 dated September 20, 1982, or FAA approved equivalent. (d) Any equivalent method of compliance with this AD must be approved by the Manager, Chicago Aircraft Certification Office, Federal Aviation Administration, 2300 East Devon Avenue, Des Plaines, Illinois 60018. (e) In accordance with FAR 21.197, flight is permitted to a base where the inspection required by this AD may be accomplished. This amendment becomes effective November 30, 1982.
87-16-07: 87-16-07 (HONEYWELL, INC., SPERRY COMMERCIAL FLIGHT SYSTEMS DIVISION (formerly Sperry Corporation, Aerospace and Marine Group): Amendment 39-5696. Applies to all digital and analog Electronic Flight Instrument Systems (EFIS) Models EDZ 601, 603, 801, 803, 611, and 811 installations, which include a multifunction display symbol generator. Compliance required within 30 days after the effective date of this AD, unless previously accomplished. To eliminate erroneous display of the angle of attack fast/slow presentation, accomplish the following: A. For the analog type EFIS equipment: Exchange Multifunction Display Symbol Generator (MG) P/N's 7007061-603, -803, -601, -801, and 901 with the same part numbers which have Modification (Mod) K or subsequent incorporated; accomplish this in accordance with Paragraph 2, "Accomplishment Instructions of Honeywell Service Bulletin 21-1986-200, dated January 20, 1987. B. For the digital type EFIS equipment: Exchange MG P/N's7007321-811 and -611 with the same part numbers which have Modification (Mod) L or subsequent incorporated; accomplish this in accordance with Paragraph 2, "Accomplishment Instructions" of Honeywell Service Bulletin 21-1987-06, dated May 15, 1987. C. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to ferry aircraft to a maintenance 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 the Honeywell Inc., Sperry Commercial Flight System Division, P.O. Box 29000, Phoenix, Arizona 85038-9000. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at Western Aircraft Certification Office, 15000 Aviation Boulevard, Hawthorne, California. This Amendment becomes effective August 20, 1987.
2017-15-09: We are adopting a new airworthiness directive (AD) for certain Diamond Aircraft Industries GmbH Model DA 42 airplanes. This AD requires installing engine exhaust pipe clamps with spring washers, repetitively inspecting the engine exhaust pipe clamps for cracks, and replacing the clamps if found cracked. This AD was prompted by cracks in the affected engine exhaust pipes, which could cause failure of the propeller regulating valve because of hot exhaust gases coming from the fractured pipes. We are issuing this AD to correct the unsafe condition on these products. [[Page 35631]]
2001-26-19: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767 series airplanes. This action requires a one-time inspection for missing, damaged, or incorrectly installed parts in the separation link assembly on the deployment bar of the emergency escape system on the entry or service door, and installation of new parts, if necessary. This action is necessary to prevent failure of an entry or service door to open fully in the event of an emergency evacuation, which could impede exit from the airplane. This condition could result in injury to passengers or crewmembers. This action is intended to address the identified unsafe condition.
75-07-07: 75-07-07 SIKORSKY AIRCRAFT: Amendment 39-2139. Applies to S-58B, S-58D, S- 58E, S-58F, S-58H, S-58J, S-58BT, S-58DT, S-58ET, S-58FT, S-58HT, S-58JT helicopters certificated in all categories, including Military Type HSS-1, HSS-1F, HSS-1N, HUS-1, HUS- 1A, HUS-1AN, HUS-1G, HUS-1Z, H-34A, H-34C, H-34J, CH-34A, CH-34C, HH-34F, SH-34G, SH-34H, SH-34J, UH-34D, UH-34E, UH-34G, UH-34J, VH-34C, VH-34D, equipped with P/N S14-50-1015 luminescent markers, used to help locate emergency hatch handles in an emergency. Compliance required within the next 30 calendar days after the effective date of this AD, unless already accomplished. To prevent operation with leaking luminescent markers, accomplish the following: (a) Visually inspect emergency hatches in accordance with Section 2., Paragraph A.(1) of Sikorsky Service Bulletin No. 58B50-1A, dated January 14, 1975, to determine if P/N S14-50-1015 luminescent markers are installed. If P/N S14-50-1015 luminescent markers are installed, accomplish paragraphs (1) through (4) below utilizing authorized personnel. Contact one of the following Energy Research and Development Administration (formerly U.S. Atomic Energy Commission, AEC now ERDA) Regional Coordinating Offices for radiological assistance and sources of authorized personnel: Regional Coordinating Office Post Office Address Telephone for Assistance Brookhaven Area Office Upton, L.I. New York 11973 516-345-2200 Oak Ridge Operations Office P.O. Box E Oak Ridge Tennessee 37830 615-483-8611, Ext. 3-4510 Savannah River Operations Office P.O. Box A Aiken, S.C. 29801 N. Augusta, S.C. 803-824-6331, Ext. 3333 Albuquerque Operations Office P.O. Box 5400 Albuquerque, New Mexico 57115 505-264-4667 Chicago Operations Office 9800 S. Cass Ave. Arconne, Illinois 60439 312-739-7711 Ext. 2111 Idaho Operations Office P.O. Box 2108 Idaho Falls, Idaho 83401 208-526-0111 Ext. 1515 San Francisco Operations Office 1333 Broadway Oakland, California 94612 415-273-4237 Richland Operations Office P.O. Box 550 Richland, Washington 99352 509-942-7381 (1) Conduct radiation survey for contamination and leakage in accordance with Section 2., Paragraph A(2) of the above service bulletin. (2) Remove markers in accordance with Section 2., Paragraph A(3) of the above service bulletin. (3) If contamination is found, decontaminate aircraft in accordance with Section 2., Paragraph A(4) of the above service bulletin. (4) Dispose of markers and contaminated material, if any, in accordance with Section 2, Paragraph A(5) of the above service bulletin. (b) Replace luminescent marker P/N S14-50-1015 with a new luminescent U.S. Radium Corp. Luminescent Marker LAB 659(S)-1, or Military Standard Marker MS39099-1 or an FAA approved equivalent part. Install the aforementioned markers at Fuselage Stations 176.0 and 210.0, in accordance with Figure 2, of the above service bulletin. Trim upholstery around the part for adequate clearance. Other equivalent markers and installations may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, New England Region. (c) The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Sikorsky Aircraft, Stratford, Connecticut 06602. These documents may also be examined at the Office of Regional Counsel, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment becomes effective April 8, 1975.
2001-26-10: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A319, A320, and A321 series airplanes. This action requires an in-situ one-time detailed visual inspection of Draeger Type I oxygen containers, located in the passenger service units, and Draeger Type II oxygen containers, located in the utility areas, for the presence of foam pads. This action also requires the installation of a new foam pad, if necessary; and other actions to ensure proper operations of the masks. This action is necessary to prevent failure of the oxygen containers to deliver oxygen to the passengers in the event of a rapid decompression or cabin depressurization. This action is intended to address the identified unsafe condition.
2017-15-10: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-9 airplanes. This AD was prompted by a determination that the shoulder bolt used on the outboard clevis of the forward support fitting of the ram air turbine (RAT) might not be long enough to allow for proper installation of the RAT; therefore, the clevis of the joint could be clamped together, resulting in reduced fatigue life and possible fracture of the clevis. This AD requires inspecting for cracking of the clevis of the forward support fitting of the RAT, installing a longer shoulder bolt, and replacing the forward support fitting if any cracking is found. We are issuing this AD to address the unsafe condition on these products.
2001-25-09: This amendment adopts a new airworthiness directive (AD) that applies to all Dornier Luftfahrt GmbH (Dornier) Model 228-212 airplanes that have a certain brake assembly installed. This AD requires you to inspect the brake housing subassembly for cracks, nicks, or corrosion (referred to as damage). This AD also requires you to replace damaged brake housing assemblies and modify the torque take-out cavity. 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 detect and correct damage to the brake housing assembly, which could result in failure of this assembly. Such failure could lead to loss of braking action on landing and possible loss of control of the airplane.
2017-15-16: We are adopting a new airworthiness directive (AD) for all Empresa Brasileira de Aeronautica S.A. (Embraer) Model EMB-135ER, - 135KE, -135KL, -135LR, -145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes. This AD was prompted by a report of airplanes with modified gust lock levers that prevented the thrust lever's full excursion, thus limiting the engine power. This AD requires replacing a certain gust lock lever. We are issuing this AD to address the unsafe condition on these products.
77-15-02: 77-15-02 HAWKER SIDDELEY AVIATION, LIMITED: Amendment 39-2972. Applies to Model HS-748, Series 2A airplanes, certificated in all categories. Compliance is required as indicated. To prevent a possible loss of aileron control, accomplish the following: (a) Within the next 100 hours time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 100 hours time in service from the last inspection, visually inspect the aileron hinge structures of the right and left wings in the areas of the outer and center hinges for damage, in accordance with the instructions set forth in Part 2A of the section entitled "Accomplishment Instructions" of Hawker Siddeley Service Bulletin No. 57/25, dated October 15, 1973, or an FAA-approved equivalent. (b) If, as a result of an inspection required by paragraph (a) of this AD, damage, in the form of cracks, loose rivets, or corroded support bearings or pivot bolts is found in any of the areas specified in paragraph (a) of this AD, before further flight, perform an internal inspection of the aileron hinge ribs where they attach to the rear spar of the wing in accordance with the instructions set forth in Part 2B of the section entitled "Accomplishment Instructions" of Hawker Siddeley Service Bulletin No. 57/25, dated October 15, 1973, or an FAA- approved equivalent. (c) If, as a result of an inspection required by either paragraph (a) or (b) of this AD, damage, in the form of cracks, loose rivets, or corroded support bearings or pivot bolts is found, before further flight, replace or repair the damaged, loose, or corroded parts in accordance with Part 2C of the section entitled "Accomplishment Instructions" of Hawker Siddeley Service Bulletin No. 57/25, dated October 15, 1973, or an FAA-approved equivalent, and continue to inspect in the areas specified and at the intervals established in paragraphs (a) and (b) of this AD, as required. (d) Within the next 1000 hours time in service after the effective date of this AD, unless already accomplished, install strengthened gusset plates to reinforce the outer and center aileron hinge ribs at both the right and left wings, in accordance with Modification 4873 as described in Part 2, entitled "Accomplishment Instructions" of Hawker Siddeley Service Bulletin No. 57/28, dated January 2, 1974, or an FAA-approved equivalent. (e) Within the next 1000 hours time in service after the effective date of this AD, unless already accomplished, install reinforcing straps at the top and bottom surfaces of the aileron spar area of both the right and left wings at the outboard aileron hinge positions, in accordance with Modification 4874 as described in Part 2, entitled "Accomplishment Instructions" of Hawker Siddeley Service Bulletin No. 57/27, dated January 2, 1974, or an FAA-approved equivalent. (f) Within the next 1000 hours time in service after the effective date of this AD, unless already accomplished, install the reinforcing plates on the right and left wing tips on the rear diaphragm in accordance with Modification 4875 as described in Part 2, entitled "Accomplishment Instructions" of Hawker Siddeley Service Bulletin No. 57/26, dated January 2, 1974, or an FAA-approved equivalent. (g) Upon accomplishment of the modifications specified in paragraphs (d), (e), and (f) of this AD, the inspections required by paragraphs (a) and (b) of this AD, may be terminated. This amendment becomes effective August 15, 1977.
2001-26-07: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Gulfstream Model G-IV series airplanes. This action requires an inspection of the electrical connections for the fire extinguisher bottles; an inspection after any subsequent maintenance affecting the fire extinguisher bottles; and corrective action, if necessary. This action is prompted by a report indicating that the electrical connections for the fire extinguisher bottle squibs had been improperly installed either during manufacturing or during subsequent maintenance. This action is necessary to prevent fire extinguishing agent from being discharged into the wrong location, which could result in failure to extinguish an in-flight fire on an affected engine and jeopardize operation of the opposite engine.
2010-05-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2010-05-51, which was sent previously to all known U.S. owners and operators of ECF Model EC120B helicopters by individual letters. This AD requires, at specified intervals, inspecting the main rotor head rotor hub (rotor hub) for a crack. If you find scoring, paint flaking or left-over identification plate adhesive, the AD requires sanding the area until the primer coat becomes visible and inspecting the rotor hub for a crack. If you find a crack, the AD requires, before further flight, replacing the rotor hub with an airworthy rotor hub. This amendment is prompted by a mandatory continuing airworthiness information (MCAI) AD issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI AD states that ECF has been informed of an emergency landing due to excessive vibrations originating from the main rotor. After an investigation, it was determined that the main rotor head rotor hub (rotor hub) had failed in the attachment area of one of the three drag damper fittings. The actions specified by the AD are intended to prevent failure of a hub, excessive vibrations, loss of a main rotor blade, and subsequent loss of control of the helicopter.
2017-14-03: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This AD requires an inspection and reduces the retirement lives of certain landing gear components. This AD is prompted by a revised analysis of the fatigue life of the landing gear. The actions of this AD are intended to prevent an unsafe condition on these products.
2001-26-08: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 B2 series airplanes and Model A300 B4-2C, B4-103, and B4-203 series airplanes, that requires identifying the types and areas of repairs on the airplane between frame 10 and frame 80, and performing follow-on actions for certain repairs. These actions are necessary to detect and correct fatigue cracking of certain repairs of the fuselage between frame 10 and frame 80, which could result in reduced structural integrity of the airplane. These actions are intended to address the identified unsafe condition.
2001-26-03: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes that have been converted from a passenger-to a cargo-carrying ("freighter") configuration. This amendment requires, among other actions, modification of the main deck cargo door structure and fuselage structure; modification of a main deck cargo door hinge; modification of the main deck cargo floor; and installation of a main deck cargo 9g crash barrier. These actions are necessary to prevent opening of the cargo door while the airplane is in flight or collapse of the main deck cargo floor, and consequent rapid decompression of the airplane including possible loss of flight control or severe structural damage. These actions are intended to address the identified unsafe condition.
74-03-04: 74-03-04 GENERAL DYNAMICS: Amdt. 39-1781. Applies to Model 240 series and T- 29B airplanes including those modified for Turbo-propeller power per STC SA1054WE certificated in all categories. Compliance required as indicated. To detect cracks in the Pilot and Copilot direct vision window frame castings, P/N's 240- 3110314-6 and -7 (hereinafter referred to as the casting) which could result in failure in flight and consequent rapid decompression, accomplish the following: (a) Inspect each casting with 4500 or more hours' time in service on the effective date of this AD for cracks in accordance with (c), below, within the next 250 hours' time in service after the effective date of this AD unless already accomplished within the last 750 hours' time in service, and thereafter at intervals not to exceed 1000 hours' time in service from the last inspection. (b) Inspect each casting with less than 4500 hours' time in service on the effective date of this AD for cracks inaccordance with (c), below, prior to the accumulation of 4750 hours' time in service and thereafter at intervals not to exceed 1000 hours' time in service from the last inspection. (c) Inspect the castings in accordance with Paragraph 2B of General Dynamics Service Bulletin 600 (240D), S.B. No. 53-2A, dated December 21, 1973, or later FAA-approved revisions, or by a method approved by the Chief, Aircraft Engineering Division, FAA Western Region. (d) If a crack is found, comply with (1) or (2), below, as appropriate: (1) If the crack completely severs the frame at any point, replace the casting with a new part, P/N 240-3110314-6 or -7, prior to further flight, except that the airplane may be flown with a zero differential cabin pressure in accordance with FAR 21.197 to a base where the replacement can be accomplished. (2) If the crack does not completely sever the frame at any point, replace the casting with a new part, P/N 240-3110314-6 or -7, within 250 hours' time in service after crack discovery, except that, until such time as the casting is replaced, the following shall apply: (i) The airplane must be operated at a zero differential cabin pressure. (ii) Prior to take off after crack discovery, an operating limitation in the form of a placard must be installed in clear view of the pilot stating: "Operation Limitation. Pressurized Flight Prohibited." (e) Operators who have not kept records of hours' time in service of individual castings shall substitute hours' time in service of the airplane in lieu thereof. (f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust the compliance times herein if the request contains substantiating data to justify the increase for that operator. This amendment becomes effective on February 4, 1947.
2001-26-06: This amendment adopts a new airworthiness directive (AD) that is applicable to CFE Company model CFE738-1-1B turbofan engines. This action requires the removal of certain fan rotor disks from service. This amendment is prompted by a report from a forging manufacturer, of a metallurgical inclusion (contaminant) found in a forging made from a certain ingot of titanium. Fan rotor disks for model CFE738-1-1B engines have been manufactured from this same ingot and are suspect for metallurgical inclusions. The actions specified in this AD are intended to remove from service affected fan rotor disks, which if not removed, could result in uncontained engine failure and damage to the airplane.
74-24-03: 74-24-03 BEECH: Amendment 39-2016. Applies to the following models and serial numbered airplanes if equipped with either Grimes P/N 30-0467-1 or Grimes P/N 30-0467-3 strobe light assemblies: F33A, Serials CE-436 through CE-537 V35B, Serials D-9468 through D-9692 A36, Serials E-424 through E-603, E-605 through E-607 95-B55 and 95-B55A, Serials TC-1526 through TC-1804 and TC-1806 through TC-1811 E55 and E55A, Serials TE-904 through TE-1000, TE-1002 and TE-1003 58 and 58A, Serials TH-303 through TH-482, and TH-484 through TH-527 A60 and B60, Serials P-223 through P-307, P-309 and P-310 70, Serial LB-35 B80, Serials LD-441 through LD-490 C90, Serials LJ-502 through LJ-643 E90, Serials LW-1 through LW-117 B99, Serials U-152 through U-159 100 and A100, Serials B-52 through B-204 200, Serials BB-1 through BB-14, BB-16 through BB-21, and BB-29 Compliance: Required as indicated, unless already accomplished. A. To preclude possible ignition of flammablefluids or vapors by arcing between the strobe lights and the aircraft structure, within the next 25 hours' time in service after the effective date of this AD, deactivate the strobe light system in accordance with Beech Service Instruction No. 0655-362, Rev. I, or later approved revisions and add a temporary placard near the strobe light switch stating "STROBE LIGHT SYSTEM DEACTIVATED". This requirement is only applicable until the strobe light system is modified per Paragraph B of this AD. B. To assure proper electrical bonding of the Grimes Strobe light P/N 30-0467-1 or P/N 30-0467-3, to the aircraft structure so as to eliminate a possible ignition source in an area where fuel/fuel vapor can exist, on or before July 1, 1975, modify the strobe light system in accordance with Beech Service Instructions No. 0655-362, Rev. I, or later approved revisions. C. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA,Central Region. If an airplane has been modified by the aircraft manufacturer in accordance with Paragraph B above and the aircraft manufacturer has made an entry in the aircraft permanent maintenance record that the modification was "in accordance with AD 74-20-11, as amended", or words to that effect, such modification meets the requirements of Paragraph B of this AD. This AD supersedes Amendment 39-1980, AD 74-20-11. This amendment becomes effective November 22, 1974.
2017-15-07: We are superseding airworthiness directive (AD) 2017-04-51 for all Safran Helicopter Engines, S.A., Arriel 1A1, 1A2, 1B, 1C, 1C1, 1C2, 1D, 1D1, 1E2, 1K1, 1S, and 1S1 turboshaft engines. AD 2017-04-51 required inspecting, wrapping, and replacing the affected drain valve assembly (DV) installed on these Arriel 1 engines. This AD requires inspecting and wrapping affected DVs and replacing those DVs found to be defective. This AD eliminates the terminating action that existed under AD 2017-04-51 and reduces the population of affected parts. This AD was prompted by reports of additional fuel leaks originating from the DV on certain Arriel engines. We are issuing this AD to correct the unsafe condition on these products.
50-32-01: 50-32-01 CONTINENTAL: Applies to All Airplanes Equipped With Continental Model E185-3 Engines Serially Numbered 4514-D and Below, E185-1 Engines Serially Numbered 4566-D and Below and E165-2 Engines Serially Numbered 10025 and Below. This Includes Navion, Beech Model 35 and Temco (Luscombe) Model 11A Airplanes. Compliance required each 10 hours of operation as indicated. AD 49-02-04 describes an inspection procedure to preclude the possibility of sudden oil pump failure (and almost immediate complete engine failure resulting therefrom) due to shearing of the square corners of the oil pump drive gear shaft. There have been a few recent oil pump failures which could have been avoided by continuation of periodic wear checks of the oil pump drive until the related parts are proven satisfactory by teardown inspection and/or replacement. Therefore, the following should be accomplished on all engines in the serial number ranges indicated above which have not already complied withContinental Service Bulletin No. M48-15: Remove tachometer drive cable and insert tapered flat end of Continental Drive Fit Indicator flat end of Continental Drive Fit Indicator (P/N 530757) in slot of tachometer drive shaft, tapping slightly to be sure it is tight in place. By holding the graduated indicator with one finger, and moving the bar with another, a reading (in degrees) of total backlash is obtained. Total backlash should not exceed 15 degrees. If total backlash does not exceed 15 degrees, the wear check should be repeated at 10-hour intervals until the engine is overhauled and oil pump parts are dimensionally inspected and/or replaced, to determine whether or not excessive wear is accumulating. An accumulation of an additional 5 degrees indicated wear in 20 hours, over the original reading, whether a total of 15 degrees is reached or not, is sufficient to warrant replacement of parts as hereafter noted. A reading of more than 15 degrees on the indicator indicates excessive wear, a potential failure, and requires immediate replacement of worn parts prior to further operation of the airplane. Parts affected include the oil pump drive gear, oil pump housing, accessory case, and cam gear. The cam gear need not be replaced if concentricity check shows total runout of square holes to be less than 0.004 inch. At the time of major overhaul (or first disassembly), oil pump drive parts as per Continental Service Bulletin No. M48-15, should be checked and replaced if necessary. These parts are the oil pump drive gear and cam gear. The wear check can be made at any Continental Authorized Service Station, and involves only a few minutes for accomplishment. (Continental Service Bulletins Nos. M48-14, with supplements Nos. 1 and 2, and M48-15, cover this same subject.) This supersedes AD 49-02-04.