Results
2001-26-24: This amendment adopts a new airworthiness directive (AD), applicable to McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes; and C-9 airplanes that requires replacing the transformer ballast assembly in the pilot's console with a new, improved ballast assembly. The actions specified by this AD are intended to prevent overheating of the ballast transformers due to aging fluorescent tubes that cause a higher power demand on the ballast transformers, which could result in smoke in the cockpit. This action is intended to address the identified unsafe condition.
2001-26-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-300 series airplanes, that requires, for certain airplanes, a one-time torque test (inspection) of the attachment bolts of the forward engine mount vibration isolators to determine if the bolts are adequately torqued, and corrective action, if necessary. For all airplanes, this amendment prohibits installation of an attachment bolt on the forward engine mount vibration isolators, unless the attachment bolt is torqued within certain limits. These actions are necessary to prevent failure of the engine mount, which could result in separation of the engine from the airplane. This action is intended to address the identified unsafe condition.
97-21-01 R1: 97-21-01 R1 MT-PROPELLER ENTWICKLUNG GMBH: Amendment 39-11206. Docket 97-ANE-36-AD. Revises AD 97-21-01, Amendment 39-10154. Applicability: MT-Propeller Entwicklung GMBH Model MTV-3-B-C/L250-21 propellers. These propellers are installed on but not limited to Sukhoi 29 aircraft. Note 1: This airworthiness directive (AD) applies to each propeller identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For propellers that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent propeller hub cracks, which could result in propeller blade separation and possible loss of control of the airplane, accomplish the following: (a) Within 50 hours time-in-service (TIS) after the effective date of this AD, accomplish the following: (1) Perform an initial dye penetrant or eddy current inspection of propeller hub, part number (P/N) B-050 or A-909-A, in accordance with paragraph (a) of MT-Propeller Entwicklung GMBH Service Bulletin (SB) No. 12C, dated March 4, 1998. The dye penetrant inspection may be done on-wing, but the eddy current inspection must be performed in an FAA-approved propeller repair station. (2) If the propeller hub is found to be cracked, prior to further flight, remove the existing propeller hub and replace with a serviceable propeller hub. (3) Rework propeller hubs, P/N B-050, by chamfering the hub bore to 0.08 inch x 45 degrees (for further information, see Detail Y of MT-Propeller Entwicklung GMBH SB No. 12C, dated March 4, 1998). Mark hubs that have been reworked in accordance with AD 97-21-01, or this revised AD, with the letters SB12C using a metal impression stamp (1/8 inch round bottom characters) above the propeller hub serial number and part number, located in the transition area between propeller blades 1 and 2 and the pitch change cylinder. (b) Thereafter, perform dye penetrant or eddy current inspections, in accordance with paragraph (a) of MT-Propeller Entwicklung GMBH SB No. 12C, dated March 4, 1998. The dye penetrant inspection may be done on-wing, but the eddy current inspection must be performed in an FAA-approved propeller repair station: (1) For propellers with hubs, P/N B-050, inspect at intervals not to exceed 50 hours TIS, or 6 months since last inspection, whichever occurs first. (2) For propellers with hubs, P/N A-909-A, inspect at intervals not to exceed 200 hours TIS, or 12 months since last inspection, whichever occurs first. (3) If the propeller hub is found to be cracked, prior to further flight, remove the existing propeller hub and replace with a serviceable propeller hub. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Boston Aircraft Certification Office. Operators shall submit their requests through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Boston Aircraft Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Boston Aircraft Certification Office. (d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the inspection requirements of this AD can be accomplished. (e) The actions required by this AD shall be accomplished in accordance with the following MT-Propeller Entwicklung GMBH SB: Document No. Pages Date 12C 1-3 March 4, 1998 Total pages: 3. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from MT- Propeller Entwicklung GMBH, Airport Straubing-Wallmuhle, D-94348 Atting, Germany; telephone (0 94 29) 84 33, fax (0 94 29) 84 32, Internet: "propeller@aol.com". Copies may be inspected at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. (f) This amendment becomes effective on August 27, 1999.
2017-16-05: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by a report of a Krueger flap bullnose departing an airplane during taxi, which caused damage to the wing structure and thrust reverser. This AD requires a one-time detailed visual inspection for discrepancies in the Krueger flap bullnose attachment hardware, and related investigative and corrective actions, if necessary. We are issuing this AD to address the unsafe condition on these products.
2017-16-11: We are adopting a new airworthiness directive (AD) for certain models of Lycoming Engines reciprocating engines. This AD requires an inspection of connecting rods and replacement of affected connecting rod small end bushings. This AD was prompted by several reports of connecting rod failures resulting in uncontained engine failure and in- flight shutdowns (IFSDs). We are issuing this AD to address the unsafe condition on these products.
2001-26-15: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81, -82, -83, and -87 series airplanes, and Model MD-88 airplanes, that requires a detailed visual inspection of certain wires to detect chafing and preload; repair, if necessary; and modification of certain wire assemblies. This action is necessary to prevent insufficient clearance between wire assemblies and the ice protection airduct and airstair door interlock rod; chafing; and consequent arcing of wire assemblies. Such arcing could result in damage to electronic equipment and adjacent structures, or cause the insulation blankets to ignite, which could result in smoke and fire in the flight deck and main cabin. This action is intended to address the identified unsafe condition.
2001-26-16: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas DC-9-81, -82, -83, and -87 series airplanes, and Model MD-88 airplanes, that requires replacing the interface connectors of the cabin fluorescent lighting ballast in the wiring harness of the overhead stowage compartment with new connectors. In lieu of the required replacement, this AD requires adding interface seals to the existing interface connectors of the cabin fluorescent lighting ballast between certain stations and reidentifying the connector assemblies. This action is necessary to prevent electrical shorting and arcing due to the presence of water in the lighting ballast interface connectors, which could result in smoke in the main cabin. This action is intended to address the identified unsafe condition.
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.