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2015-05-03: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by reports of cracking on the skin panels and skin splice joints and angles at certain stringers at various locations between certain fuselage stations. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new or revised maintenance requirements and airworthiness limitations, and incorporating structural repairs and modifications to preclude widespread fatigue damage (WFD). We are issuing this AD to detect and correct WFD, which could adversely affect the structural integrity of the airplane.
2010-12-51: This document publishes in the Federal Register an amendment adopting Emergency Airworthiness Directive (AD) 2010-12-51, which was sent previously to all known U.S. owners and operators of the specified Agusta model helicopters by individual letters. This AD requires, before further flight, removing the forward boot from the hub-locking nut (nut) and inserting a gauge between the tail rotor control rod (rod) and nut until the gauge stops. This AD then requires, depending on the depth measurement from the face of the nut, either reidentifying the tail rotor gearbox (TGB) with a new part number (P/N) or replacing the TGB and the associated parts with airworthy parts. This AD is prompted by a report of a missing rod bushing (bushing) from a 90- degree TGB installed on a Model AW119 MKII helicopter. The Agusta Model A119 helicopters also have the affected TGB installed; therefore, they are also included in the applicability of this AD. The actions specified by this AD are intendedto detect a missing bushing in the TGB and to prevent abnormal vibration, damage to the tail rotor system, loss of the yaw control function, and subsequent loss of control of the helicopter.
2000-08-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Lockheed Model L-1011-385 series airplanes, that requires modification of the high pressure bleed valve controller of each engine. This amendment is prompted by reports of failure of the bleed air system components such as the thermal compensators and bleed air ducts. The actions specified by this AD are intended to prevent such failures of the bleed air system components, which could result in high temperature air leaking into the cabin and/or cargo areas and could possibly require an emergency landing and evacuation.
81-01-08: 81-01-08 ISRAEL AIRCRAFT INDUSTRIES, LIMITED (formerly Aero Commander, North American Rockwell Corporation): Amendment 39-4011. Applies to certain Model 1121, 1121A, 1121B, 1123, and 1124 airplanes, certificated in all categories. Compliance required as indicated. To preclude the possibility of structural failure of the 25 percent wing spar, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD, unless already accomplished, or the modification required by paragraph (b) of this AD has been accomplished, install a placard in clear view of the pilots in accordance with the instructions in PART A: PLACARD INSTALLATION, of the appropriate Israel Aircraft Industries, Limited, Service Bulletin, as indicated in the following list: (1) No. CJ-25A, Revision No. 1, dated March 31, 1980, or an FAA-approved equivalent, for Models 1121, 1121A, and 1121B airplanes, serial numbers 94 through 106 and 108 through 150, the placard to read as follows: "MAXIMUM OPERATING SPEED LIMITS (VMO/MMO) - Below 26,000 FT - 315 Kts CAS - Above 26,000 FT - 0.765 M"; (2) No. WW-23A, Revision No. 1, dated March 31, 1980, or an FAA- approved equivalent, for Model 1123 airplanes, serial numbers 107, 151, 153, 155 through 180, and 182 through 186, the placard to read as follows: "MAXIMUM OPERATING SPEED LIMITS (VMO/MMO) - With or without fuel in tip tanks: Below 22,500 FT - 315 Kts CAS Above 22,500 FT - 0.710 M - With autopilot engaged and without fuel in tip tanks: Below 26,000 FT - 315 Kts CAS Above 26,000 FT - 0.765 M"; or (3) No. WW-24-17A, Revision No. 1, dated March 31, 1980, or an FAA- approved equivalent, for Model 1124 airplanes, serial numbers 152, 154, 181, 187 through 260, 262 through 264, and 266 through 269, the placard to read as follows: "MAXIMUM OPERATING SPEED LIMITS (VMO/MMO) - With autopilot disengaged: Below22,500 FT - 315 Kts CAS Above 22,500 FT - 0.710 M - With autopilot engaged: Below 26,000 FT - 315 Kts CAS Above 26,000 FT - 0.765 M". (b) Within the next 600 hours time in service or the next 90 days after the effective date of this AD, whichever occurs first, unless already accomplished, install additional rivets in the 25 percent wing spar between wing stations Xw-33 and Xw-47.5, left and right, in accordance with the instructions in PART B: RIVET INSTALLATION, of the appropriate Israel Aircraft Industries, Limited, Service Bulletin, as indicated in the following list: (1) No. CJ-25A, Revision No. 1, dated March 31, 1980, or an FAA-approved equivalent, for Models 1121, 1121A, and 1121B airplanes, serial numbers 94 through 106 and 108 through 150; (2) No. WW-23A, Revision No. 1, dated March 31, 1980, or an FAA- approved equivalent, for Model 1123 airplanes, serial numbers 107, 151, 153, 155 through 180, and 182 through 186; or (3) No.WW-24A, Revision No. 1, dated March 31, 1980, or an FAA- approved equivalent, for Model 1124 airplanes, serial numbers 152, 154, 181, 187 through 260, 262 through 264, and 266 through 269. (c) The placard required by paragraph (a) may be removed when the modification required by paragraph (b) is completed. (d) If an equivalent means of compliance is used in complying with paragraphs (a) or (b) of this AD, that equivalent must be approved by the Chief, Aircraft Certification Staff, AEU- 100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. This amendment becomes effective January 16, 1981.
2015-05-01: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 757-200, -200PF, -200CB, and -300 series airplanes; and Model 767-200, -300, -300F, and -400ER series airplanes. This AD was prompted by reports indicating that the counterweights in some hub assemblies of the ram air turbine (RAT) could be understrength and fracture when the RAT is rotating, and that some RAT hub assemblies were delivered with balance washer retention screws that were incorrectly heat-treated, and therefore, susceptible to fracture and cracking. This AD requires a part number and serial number inspection to determine if certain RAT hub assemblies are installed; and, for affected RAT hub assemblies, doing an inspection for missing and fractured balance washer screws, and replacement or rework if necessary. We are issuing this AD to prevent an inoperative RAT, which, following a dual engine shutdown in flight, will cause loss of all hydraulic power to the primary flight controls, resulting in subsequent loss of control of the airplane.
2015-05-07: We are superseding Airworthiness Directive (AD) 2015-02-06 for certain Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant) airplanes. AD 2015-02-06 required a revision to the airplane flight manual, a revision to the maintenance or inspection program, as applicable, and replacement of horizontal stabilizer trim actuators (HSTAs) having certain part numbers. This new AD continues to require those actions and corrects certain typographical errors. This AD was prompted by the discovery of three typographical errors in AD 2015-02-06. We are issuing this AD to detect and correct loose spur gear bolts on the HSTA, which, if combined with the failure of the primary load path, could lead to failure of the HSTA and subsequent loss of the airplane.
99-24-13: This amendment adopts a new airworthiness directive (AD) that is applicable to all EMBRAER Model EMB-135 and EMB-145 series airplanes. This action requires a revision to the Airplane Flight Manual (AFM) to prohibit in-flight operations of the autopilot coupled to flight director #2 during certain conditions; and installation of an associated warning placard. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent failure of the autopilot to automatically disconnect from flight director #2, as intended, at a low altitude during windshear conditions. Such failure could result in reduced controllability of the airplane.
85-15-01 R2: 85-15-01 R2 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (AEROSPATIALE): Amendment 39-5093 as amended by Amendment 39-5679 is further amended by amendment 39-6021. Applies to Aerospatiale Model SA 365 series helicopters, certificated in any category, when equipped with main rotor masts with Part Numbers 365A31- 1060-23 or -25, or 365A31-1179-03, -20, or -21. Compliance with this amendment to the AD is required as indicated after the effective date of this amendment, unless already accomplished. To prevent possible failure of the main rotor mast, accomplish the following: (a) For helicopters which have 250 hours or more time in service on the main rotor mast on the effective date of this AD, inspect in accordance with paragraph (d) within 50 hours time in service. (b) For those helicopters which have less than 250 hours time in service on the main rotor mast on the effective date of this AD, inspect in accordance with paragraph (d) before reaching 300 hourstime in service. (c) For those helicopters exhibiting a severe tracking defect, inspect in accordance with paragraph (d) before further flight. (d) Remove the main rotor hub from the main rotor mast and inspect the mast in accordance with Service Bulletin No. 05.08 (for Model SA 365C series helicopters) and Service Bulletin No. 05.04 (for Model SA 365N helicopters) or FAA-approved equivalent, as appropriate. (e) Replace any cracked mast with a serviceable part. (f) Reinstall the main rotor hub in accordance with Service Bulletin No. 05.08, Service Bulletin 05.04, or FAA-approved equivalent, after completion of the inspection and rework of paragraphs (d) and (e). (g) Conduct the following repetitive inspections: (i) Repeat the inspections of paragraph (d) at intervals not to exceed 300 hours time in service from the last inspection. (ii) Visually inspect the upper mast flange-to-shaft radius within the next 50 hours time in service from the effective date of this amendment and thereafter at intervals not to exceed 50 hours time in service from the last inspection. Inspect for finish deterioration, corrosion, or cracks. Use a 10-power glass in areas of suspected surface cracks. Conduct magnetic particle or dye penetrant inspections of all areas where finish deterioration is found. Remove polyurethane shock-proofing coating of the upper main rotor shaft, if installed, to allow more effective inspections of this area (Service Bulletin SA 365 No. 01-17 provides information concerning the shock-proofing coating and its removal). (h) (Removed) (i) Any equivalent method of compliance with this AD must be approved by the Manager, Aircraft Certification Division, FAA, P.O. Box 1689, Fort Worth, Texas 76101, or by the Manager, Brussels Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium, APO NY 09667. (j) In accordance with FAR Sections 21.197 and 21.199, flight is permitted to a base where the inspections required by this AD may be accomplished. This amendment, 39-6021, becomes effective October 19, 1988. This amendment, 39-6021, further amends Amendment 39-5093 (50 FR 29649; July 22, 1985), AD 85-15-01, as amended by Amendment 39-5679 (52 FR 27787; July 24, 1987) AD 85- 15-01 R1.
2015-03-03: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 series airplanes, Model A300 B4-600, B4-600R, and F4- 600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). This AD was prompted by a report of chafing found on the overflow sensor harness of the surge tank, and subsequent contact between the electrical wiring and fuel tank structure. This AD requires a one-time inspection for chafing of the overflow sensor harness, and repair if necessary. This AD also requires modification of the sensor harness. We are issuing this AD to prevent chafing of the harness and subsequent contact between the electrical wiring and fuel tank structure, which could result in electrical arcing and a fuel tank explosion and consequent loss of the airplane.
2000-08-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -300, -400, and -500 series airplanes, that requires repetitive inspections to detect damage of certain taxi light assemblies, and replacement with a new or serviceable part, if necessary. This AD also requires eventual replacement of certain taxi light assemblies with improved parts, which constitutes terminating action for the repetitive inspections. This amendment is prompted by a report that a damaged taxi light detached from an airplane and was ingested into the airplane engines. The actions specified by this AD are intended to prevent damage to the taxi light assembly, which could result in detachment of the taxi light assembly from the airplane, ingestion of taxi light debris into an engine, and consequent loss of thrust from one or both engines.