Results
88-07-04: 88-07-04 BOEING: Amendment 39-5881. Applies to Model 737 series airplanes, as listed in Boeing Service Bulletin 737-32-1202, dated August 27, 1987, certificated in any category. Compliance required within the next six months after the effective date of this AD, unless previously accomplished.\n \n\tTo prevent damage to the hydraulic systems and loss of brakes and nose wheel steering, accomplish the following: \n\n\tA.\tInstall left and right main landing gear brake metering valve tire burst guards in accordance with Boeing Service Bulletin 737-32-1202, dated August 27, 1987, or later FAA- approved revision. \n\n\tB.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective May 1, 1988.
2020-12-07: The FAA is adopting a new airworthiness directive (AD) for certain Hamilton Sundstrand Corporation (Hamilton Sundstrand) 54H60 model propellers. This AD was prompted by the failure of a propeller blade that resulted in the loss of the airplane. This AD requires initial and repetitive eddy current inspections (ECIs) of the affected propeller blades and replacement of the propeller blades that fail the inspection. The FAA is issuing this AD to address the unsafe condition on these products.
94-02-04: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 727 series airplanes, that requires inspections of certain fuselage frames for cracks, and modification, if necessary; inspections to detect cracks in certain frame gussets, and replacement, if necessary; and inspections at certain body stations to detect open pilot holes and to detect cracks in any open pilot hole found, and repair and modification, if necessary. This amendment is prompted by reports of cracked frames and open pilot holes. The actions specified by this AD are intended to prevent frame failures and consequent rapid decompression of the cabin.
2005-11-08: The FAA adopts a new airworthiness directive (AD) for all GROB-WERKE (GROB) Model G120A airplanes. This AD requires you to replace the main landing gear front and rear spherical bearings with improved spherical bearings. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to replace front and rear main landing gear bearings that are susceptible to damage when exposed to high axial loads, which could result in failure of the landing gear bearing. This failure could lead to loss of control on landing.
60-24-05: 60-24-05 SUPERIOR (Culver): Amdt. 223 Part 507 Federal Register November 15, 1960. Applies to All Superior (Culver) V and V2 Aircraft. Compliance required as indicated. To prevent fuel cell failures, the following must be accomplished: (a) Within the next 25 hours of operation, but not later than the next periodic or progressive inspection, install a nonicing and nonwater accumulating fuel cell vent outlet (Superior P/N 12270 or equivalent) that will provide positive pressure within the vapor spaces of the cells during normal flight conditions. (b) Inspect the attachment of the fuel cells to the wing structure at the time of the vent outlet modification and at each succeeding 100-hour inspection (if required by CAR 43.22) and each periodic aircraft inspection. Any attachment areas that are found to have failed must be recemented prior to the next flight. (Superior Aircraft Company Service Bulletin No. 25 covers this subject.) This directive effectiveDecember 13, 1960.
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.
2020-12-01: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd. & Co KG (RRD) Trent XWB-75, XWB- 79, XWB-79B, and XWB-84 model turbofan engines. This AD was prompted by analysis by the manufacturer of the low-pressure compressor (LPC) outlet guide vane (OGV) assembly and LPC OGV outer mount ring assembly. The analysis predicted that when the front engine mount is in the fail- safe condition, the most highly stressed LPC OGV outer mount ring assembly has a life that could be substantially less than one shop visit interval. This AD requires initial and repetitive inspections of the LPC OGV outer mount ring assembly and, depending on the results of the inspections, possible replacement of the LPC OGV outer mount ring assembly. The FAA is issuing this AD to address the unsafe condition on these products.
94-01-09: This amendment adopts a new airworthiness directive (AD) that is applicable to Canadair Model CL-600-2B19 "Regional Jet" Series 100 airplanes. This action requires a revision to the Airplane Flight Manual (AFM) to limit altitude and airspeed operations of the airplane under certain conditions of hydraulic system failure. This amendment is prompted by a report of sheared- off shear pins found on one airplane's elevator dampers. The actions specified in this AD are intended to prevent undampened vibration of the elevators in normal cruise conditions when combined with hydraulic system failures, a condition which could result in reduced controllability of the airplane.
95-21-10: This amendment adopts a new airworthiness directive (AD) that is applicable to all Fokker Model F28 Mark 0100 and Model F28 Mark 0070 series airplanes. This action requires revising the Limitations Section of the Airplane Flight Manual to include information that will enable the flightcrew to identify failures of the emergency direct current (DC)/alternating current (AC) bus power supply and to take appropriate corrective actions. This amendment is prompted by one report indicating that a diode failed, which resulted in battery drain and loss of the emergency DC bus power supply; and another report indicating that the circuit breaker of the transformer rectifier unit No. 3 tripped, which resulted in the loss of the emergency DC/AC bus power supply. The actions specified in this AD are intended to ensure that the flightcrew is advised of the potential hazard related to failures of the emergency bus power supply, and the procedures necessary to address it.
78-22-08: 78-22-08 HILLER AVIATION: Amendment 39-3327. Applies to Model UH-12D and UH-12E helicopters, including the UH-12E 4-place configurations, which have been converted to turbine power in accordance with Soloy Conversions, Ltd., STC Nos. SH177WE and SH178WE respectively, certificated in all categories. Compliance required on or before January 1, 1979. To prevent loss of flight control or engine control, accomplish the following: (a) Modify the integrated collective and N2 engine control system in accordance with Soloy Conversions, Ltd., Service Bulletin 06-560 dated October 6, 1978, or later FAA approved revision. (b) Unless already accomplished, remove from service certain N1 and N2 engine control cables as identified in Soloy Conversions, Ltd., Service Bulletin 06-560 dated October 6, 1978, or later FAA approved revisions. Install replacement cables in accordance with the same bulletin. (c) An equivalent modification may be approved by the Chief, Engineering andManufacturing Branch, FAA, Northwest Region. 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 this document from the manufacturer, may obtain copies upon request to Soloy Conversions, Ltd., P.O. Box 60, Chehalis, Washington 98532. This document may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment becomes effective November 30, 1978.
2020-11-11: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD requires a repetitive check of the fuel quantity indicating system (FQIS) fuel quantity calculation for the center wing tank (CWT) fuel quantity, developing a process to provide documentation to the flight crew that this check was done, and revising the existing airplane flight manual (AFM) to incorporate verification procedures and flight crew awareness. This AD was prompted by reports of discrepancies between the FQIS fuel quantity and the refueling truck uploaded fuel amount, followed by certain engine-indicating and crew-alerting system (EICAS) messages. The FAA is issuing this AD to address the unsafe condition on these products.
91-06-19: 91-06-19 AEROSPATIALE (FORMERLY SUD-SERVICE/SUD AVIATION): Amendment 39-6939. Docket No. 91-NM-40-AD. Applicability: Caravelle SE 210 Model I, III, and VIR series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent collapse of the main landing gear (MLG) and consequent structural damage to the airplane, accomplish the following: A. Prior to the accumulation of 50 landings after the effective date of this AD, or within 30 days after the effective date of this AD, whichever occurs first, and thereafter at intervals not to exceed 2,500 landings, perform an ultrasonic inspection of the front hinge beam upper bearings on each MLG, in accordance with Figure 2 on page 18 of Messier-Hispano-Bugatti Service Bulletin 32-083, Revision 4, dated November 28, 1990. B. If defects are found as a result of the inspections required by paragraph A. of this AD, which are outside the limits specified in Messier-Hispano-Bugatti Service Bulletin 32-083, Revision 4, dated November 28, 1990, prior to further flight, remove the damaged MLG and perform an ultrasonic inspection of the hinge beam, an eddy current inspection following removal of the bushings, and a complete geometric check of the MLG, in accordance with the service bulletin. 1. MLG's which have been reconditioned in accordance with these procedures may only be returned to service provided that no defects are found. 2. If defects are found, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, or replace affected part with a serviceable part of same part number. C. If no defects are found as a result of the inspections required by paragraph A. of this AD, and the MLG components have been overhauled, prior to further flight, accomplish the following. 1. Assemble in accordance with Overhaul Manual 32-1-61. 2. Accomplish geometric adjustment in accordance with Repair Document HS RA20017. 3. Accomplish eccentric adjustment in accordance with Repair Document HS RA20017 or Aeroservice Section 1, No. 82. 4. Repeat the inspection required by paragraph A. of this AD prior to the accumulation of 2,500 landings and thereafter at intervals not to exceed 2,500 landings. D. If no defects are found as a result of the inspections required by paragraph A. of this AD, and the MLG components have not been subjected to the procedures identified in paragraphs C.1., C.2., and C.3. of this AD during the last overhaul, repeat the inspection required by paragraph A. of this AD at intervals not to exceed 50 landings until next overhaul, including a complete ultrasonic inspection of the hinge beam, an eddy current inspection following removal of bushings, and a complete geometric check of the MLG. 1. MLG's which have been inspected in accordance with this procedure may only be returned to serviceprovided that no defects are found. 2. If defects are found, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, or replace affected part with serviceable part of same part number. 3. Following overhaul of the MLG components, repeat the inspection required by paragraph A. of this AD at intervals not to exceed 2,500 landings. E. An alternative method 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 forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. F. 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 information from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6939, AD 91-06-19) becomes effective on April 1, 1991.
93-24-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T93-24-51 that was sent previously to all known U.S. owners and operators of all Airbus Model A310 and A300-600 series airplanes by individual telegrams. This AD requires repetitive operational tests of feel and limitation computers (FLC) 1 and 2. This amendment is prompted by a report that the pitch control on a Model A300-600 series airplane operated with stiffness. The actions specified by this AD are intended to prevent stiff operation of the pitch control and undetected loss of rudder travel limitation function.
2008-07-01: The FAA is superseding an existing airworthiness directive (AD) for certain Turbomeca Arriel 1B, 1D, 1D1, and 1S1 turboshaft engines. That AD currently requires initial and repetitive position checks of the gas generator 2nd stage turbine blades on all Turbomeca Arriel 1B, 1D, 1D1, and 1S1 turboshaft engines. That AD also currently requires initial and repetitive replacements of 2nd stage turbines on 1B, 1D, and 1D1 engines only. This AD requires adding a 3,000 hour life limit to Arriel 1B 2nd stage turbine blades. This AD results from reports of failures of second stage turbine blades. We are issuing this AD to prevent failures of the 2nd stage turbine blades, which could result in uncommanded in-flight engine shutdown, and subsequent forced autorotation landing or accident. DATES: This AD becomes effective April 30, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of April 30, 2008.The Director of the Federal Register previously approved the incorporation by reference of Turbomeca Mandatory Alert Service Bulletins A292 72 0809, Update 1, dated October 4, 2005; and A292 72 0810, dated March 24, 2004; as of February 28, 2006 (71 FR 3754, January 24, 2006).
78-12-08: 78-12-08 AVCO LYCOMING: Amendment 39-3239. Applies to O-320-H series engines Serial Numbers L-101-76 through L-3829-76, L-3831-76, L-3843-76 through L-3859-76, L-3864-76, L-3866-76, L-3871-76, L-3902-76 through L-3907-76 and all O-320-H series engines overhauled (Remanufactured by Lycoming) before March 24, 1978. Compliance required within the next 10 hours in service, unless already accomplished. a. To prevent oil pump failures, remove, inspect and alter the oil pump body and replace the oil pump driving impeller with driving impeller P/N LW-15998 and the oil pump driven impeller with driven impeller P/N LW-15999 in accordance with AVCO Lycoming Service Bulletin No. 423 dated March 24, 1978, or FAA approved equivalent. b. Equivalent method of compliance must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective June 20, 1978.
2020-11-06: The FAA is adopting a new airworthiness directive (AD) for Pilatus Aircraft Ltd. Model PC-6, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/ B2-H4, PC-6/C-H2, PC-6/C1-H2, PC-6-H1, and PC-6-H2 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 flap actuator taper pins that were not swaged during the manufacturing process. The FAA is issuing this AD to require actions to address the unsafe condition on these products.