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2020-12-10: The FAA is superseding Airworthiness Directive (AD) 2011-12-08 for Bell Helicopter Textron Inc. (Bell), Model 205A, 205A-1, 205B, 212, 412, 412CF, and 412EP helicopters. AD 2011-12-08 required a one-time inspection of the tail rotor (T/R) blade for corrosion and pitting. This new AD retains the requirements of AD 2011-12-08 while excluding certain T/R blades from the applicability. This AD was prompted by new manufacturing and inspection procedures implemented by Bell that correct the unsafe condition on more recently manufactured T/R blades. The actions of this AD are intended to address an unsafe condition on these products.
94-02-06: 94-02-06 Wytwornia Sprzetu Komunikacyjnego "PZL-RZESZOW": Amendment 39-8804. Docket 92-ANE-21. Supersedes AD 91-18-12, Amendment 39-8120. Applicability: Wytwornia Sprzetu Komunikacyjnego "PZL-RZESZOW" PZL-3S Second Series reciprocating engines installed on but not limited to Grumman AG CAT aircraft. Compliance: Required as indicated, unless accomplished previously. To prevent separation of the propeller and loss of the aircraft, accomplish the following: (a) For pistons that have been modified and assembled with compression ring, part number (P/N) JRS 123421, scraper ring, P/N JRS 123423, and oil control ring, P/N JRS 123424, prior to further flight: (1) Remove these pistons from service and replace with serviceable parts. (2) Remove, clean, and visually inspect using 10x magnification the propeller to engine propeller-flange attachment bolts for evidence of cracking or failure, and perform the following: (i) For engines with bolts found to be cracked or broken, replace with new bolts and disassemble and visually inspect for distress of the rear crankshaft, rear counterweight, and rear counterweight pins. (A) If any distress is found in the rear crankshaft, rear counterweight, or rear counterweight pins, replace distressed parts with new parts. (B) Distress is defined as any evidence of wear, galling, pitting, or scoring, and includes discoloration (blue color) of the counterweight pins. (ii) For engines with bolts found not to be cracked, inspect the engine propeller-flange retaining nut for looseness and perform the following: (A) Retorque the propeller-flange retaining nut if found loose in accordance with Section 3.3.4 of the PZL-3S Engine Servicing Instructions, revised March 1984. (B) Replace all propeller to engine propeller-flange attachment bolts with new bolts. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used ifapproved by the Manager, Engine Certification Office. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Engine Certification Office. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the aircraft to a location where the requirements of this AD can be accomplished. (d) This amendment becomes effective on February 28, 1994.
2008-13-26: We are adopting a new airworthiness directive (AD) for certain Lockheed Model 1329 series airplanes. This AD requires determining the part number on the steering cylinder assembly for the nose landing gear (NLG), determining the total flight cycles accumulated on the NLG steering cylinder assembly, repetitively replacing the assembly, inspecting for missing tow turning limit markings, and performing corrective actions if necessary. This AD results from reports of numerous failures of the NLG steering cylinder. We are issuing this AD to prevent the loss of hydraulic pressure and steering control.
2008-13-30: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Two of the fasteners used to attach the "scissors'' to the horizontal and the vertical stabilizers were found broken during routine maintenance. The highest loads on the "scissors'' occur when using high reverse thrust. Therefore, the reverse thrust must be limited to idle in order to keep the loads at a sufficiently low level to preclude any structural problem. * * * Failure of the attachment fasteners could result in possible in-flight loss of a horizontal or vertical stabilizer and consequent loss of control of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
62-09-02: 62-09-02 R1 CANADAIR: Amdt. 430 Part 507 Federal Register April 25, 1962. Applies to all Model CL-44D4 aircraft equipped with Rolls Royce Tyne Engines. Compliance required within next 15 hours' time in service and at each 15 hours' time in service thereafter. To preclude further cases of bearing failure inspect the magnetic plug and the filter in the scavenge oil line from the high pressure turbine bearing for deposits of hard carbon as specified in the note under paragraph 2B of Rolls Royce Tyne Alert Service Bulletin No. A.Ty.79-12. The engine is to be removed from service and repaired in accordance with approved maintenance procedures if such deposits are present. Upon request of the operator, an FAA maintenance inspector subject to prior approval of the Chief, Engineering and Manufacturing Branch, International Division, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator ifthe request contains substantiating data to justify the increase for such operator. (Rolls Royce Tyne Alert Service Bulletin No. A.Ty.79-12 dated March 30, 1962, covers this same subject.) This directive effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated April 6, 1962. Revised May 2, 1962.
2020-03-50: The FAA is adopting a new airworthiness directive (AD) for certain Cirrus Design Corporation (Cirrus) Model SF-50 airplanes. This AD was sent previously as an emergency AD to all known U.S. owners and operators of these airplanes. This AD requires disconnecting and removing the headset amplifier and microphone interface circuit card assemblies for the 3.5 mm audio and microphone jacks. This AD was prompted by a cabin fire incident that occurred on a Cirrus Model SF50 airplane during ground operations where the operator observed smoke exiting from behind the right sidewall interior panel. The FAA is issuing this AD to address the unsafe condition on these products. This AD is effective June 11, 2020 to all persons except those persons to whom it was made immediately effective by Emergency AD 2020- 03-50, issued on February 14, 2020, which contained the requirements of this amendment.
94-02-02: This amendment adopts a new airworthiness directive (AD) that applies to Rockwell International/Air Transport Division (Collins) DME-700 distance measuring equipment (DME) installed on aircraft. This action requires modifying these DME units to ensure they are functioning properly. Several reports of the affected DME units failing to process and update distance outputs, and reports of these units establishing a continuous restart mode upon power application prompted this AD. The actions specified by this AD are intended to prevent improper operation of this equipment, which could result in navigational errors.
75-26-05: 75-26-05 BELL: Amendment 39-2457. Applies to Bell Models 204B, 205A-1, and 212 helicopters certificated in all categories. (a) Compliance required as follows: (1) For main rotor blades having 12 or more months' installed time on a helicopter, on the effective date of this AD, conduct inspections within 90 days' time unless already accomplished. (2) For main rotor blades having less than 12 months' installed time on a helicopter on the effective date of this AD, conduct inspections prior to attaining 15 months' installed time on a helicopter. (3) Conduct repetitive inspections at intervals not to exceed 12 months' installed time from the last inspection. (b) To detect possible cracks and corrosion and to prevent further corrosion in the main rotor blade inboard portion, accomplish the following: (1) Remove the main rotor blades from the helicopter and prepare the blades for inspection as noted in Bell Helicopter Company Service Bulletin No. 205-75-5, revision A, dated October 22, 1975, or later approved revisions, Part III, paragraph A. (2) Inspect the blades as noted in Service Bulletin No. 205-75-5, revision A, or later approved revisions, Part III, paragraph A. Blades with cracks or adhesive voids exceeding the limits specified in Service Bulletin No. 205-75-5, revision A, Part III, paragraph A, may not be returned to service. (3) Repair discrepant blades as specified in Service Bulletin No. 205-75-5, revision A, or later approved revisions, Part III, paragraph A. Refinish discrepant blades as specified in Part III, paragraph B. (4) Install blades on the helicopter in accordance with the applicable model maintenance and overhaul information manual and balance and track the blades. (c) Equivalent means of compliance with paragraph (b) of this AD may be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. Bell Service Bulletins No. 204-75- 1, revision A, dated October 22, 1975, No. 212-75-6, revision A, dated October 22, 1975, or later FAA-DER approved revisions to these bulletins are approved as equivalent means of compliance with paragraph (b). (d) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, Flight Standards Division, FAA, Southwest 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 that operator. (e) 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 Service Manager, Bell Helicopter Company, P.O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas. This amendment becomes effective January 19, 1976.
90-21-22: 90-21-22 BRITISH AEROSPACE: Amendment 39-6772. Docket No. 90-NM-136-AD. Applicability: All Model BAe 125-800A series airplanes, on which British Aerospace Modification 253244A has not been incorporated, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent failure of a link pin and subsequent reduced structural integrity of the main landing gear (MLG), accomplish the following: A. Within 30 days after the effective date of this AD, with the airplane on wheels, lubricate the right and left MLG upper and lower torque link pivots (three per landing gear), in accordance with British Aerospace Service Bulletin 32-222, dated November 10, 1989. 1. If grease does appear in all places indicated in the service bulletin, no further action in accordance with this AD is required and the airplane may be returned to service. 2. If grease does not appear in all places indicated in the service bulletin, prior to further flight, disassemble that MLG, perform visual and dye penetrant inspections to detect defects (scoring, wear, necking, ovality, and/or blocked grease holes) and cracks in the pivot pins and bolts, and hand lubricate the torque link pivots, in accordance with the service bulletin. a. If the condition of the torque link pin or bolt reveals defects or cracks, prior to further flight, replace it with a serviceable part in accordance with the service bulletin. b. If the clearance between any torque link and the MLG is less than 0.002 inch, carefully abrade the surfaces of the bushes in the torque link to achieve the required .002 inch minimum/.0l0 inch maximum condition, in accordance with the service bulletin. c. At intervals not to exceed 50 landings, disassemble and repeat the special hand lubrication of the MLG upper and lower torque links, in accordance with the service bulletin. B. Incorporation of Modification 253244A, in accordance with British Aerospace Service Bulletin 32-222-3244A, Revision 1, dated March 5, 1990, constitutes terminating action for the repetitive lubrication procedures required by paragraph A.2.c. of this AD. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Standardization Branch, ANM-113. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6772, AD 90-21-22) becomes effective on November 19, 1990.
2020-12-02: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model EC120B helicopters. This AD was prompted by a report that a changed manufacturing process for the tail rotor blades (TRB) was implemented, affecting the structural characteristics of the blades and generating a new part number for these blades. This AD requires re-identifying each affected TRB having a certain part number and serial number and establishing a life limit for the new part numbers. This AD also prohibits installation of any affected TRB identified with the old part number on any helicopter. The FAA is issuing this AD to address the unsafe condition on these products.