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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.
92-27-05: 92-27-05 PIPER AIRCRAFT CORPORATION: Amendment 39-8438. Docket No. 91- CE-14-AD. \n\n\tApplicability: PA-31 Series airplanes (all models and serial numbers), certificated in any category. \n\n\tCompliance: Required the next time the aileron cables are disconnected for any reason, but no later than 12 calendar months after the effective date of this AD, unless already accomplished. \n\n\tTo prevent improper connection of the aileron control systems, which could result in loss of lateral control of the airplane, accomplish the following: \n\n\t(a)\tUsing red enamel paint, color code the aileron balance cable and the bellcrank lug of both aileron control systems in accordance with Figure 1 of this AD. \n\n\t(b)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished. \n\n\t(c)\tAn alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. \n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. \n\n\t(d)\tAll persons affected by this directive may examine any information that is applicable to this AD at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. \n\n\t(e)\tThis amendment becomes effective on January 29, 1993. \n\n\n\t\t\t\tFIGURE 1 AD 92-27-05\n\t\tVIEW LOOKING THRU TOP WING SKIN (LEFT WING)\n\t\t\t\t RIGHT WING OPPOSITE
76-24-05: 76-24-05 ROLLS-ROYCE (1971) LIMITED: Amendment 39-2781. Applies to Rolls-Royce Bristol Viper Mk 601-22 engines installed, or being held for installation on Hawker Siddeley/Beechcraft Hawker Model DH/BH-125 series airplanes, certificated in all categories. Compliance is required within the next 150 hours time in service after the effective date of this AD, unless already accomplished. To prevent possible turbine disc damage, replace the inner exhaust turbine cone assembly in accordance with the "Accomplishment Instructions" of Rolls-Royce Alert Service Bulletin No. 72-A69, dated May 1976, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, APO New York, N.Y. 09667. This amendment becomes effective December 14, 1976.
92-02-14: 92-02-14 AIRBUS INDUSTRIE: Amendment 39-8150. Docket 91-NM-255-AD. Applicability: Model A320 series airplanes through manufacturer's serial number 175, inclusive, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the overwing emergency escape slides to deploy, accomplish the following: (a) Within 50 hours time-in-service after the effective date of this AD, perform an inspection of the flexible control cables on the right-hand and left-hand overwing emergency escape slides to ensure that the flexible control assembly on each overwing escape slide is correctly installed, in accordance with Airbus Industrie All Operator Telex (AOT) 25-02, dated May 16, 1991. (1) If each flexible control assembly is correctly installed, no further action is required. (2) If a flexible control assembly is incorrectly installed, prior to further flight, reconnect the assembly, in accordance with the AOT.(b) 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. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The inspections and reconnections of the flexible control assemblies and release cable assemblies required by this AD shall be done in accordance with Airbus Industrie All Operator Telex 25-02, dated May 16, 1991. 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. Copies may be inspected at the FAA, Transport Airplane Directorate, Standardization Branch, ANM-113, 1601 Lind Avenue S.W., Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. (e) This amendment (39-8150, AD 92-02-14) becomes effective on March 2, 1992.
77-07-09: 77-07-09 AVIONS MARCEL DASSAULT/BREGUET AVIATION (AMD/BA): Amendment 39-2867. Applies to Falcon 10 airplanes, certificated in all categories, equipped with Grumman tailpipe, P/N F10A5B10003-7, installed without back-up ring, P/N F10A5B10606-11. Compliance is required as indicated, unless already accomplished. To prevent the possible loss of the tailpipe, accomplish the following: (a) For tailpipes having more than 750 hours time in service on the effective date of this AD, comply with paragraph (c) of this AD within 90 days or 150 hours time in service after the effective date of this AD, whichever occurs first. (b) For tailpipes having 750 hours or less time in service on the effective date of this AD, comply with paragraph (c) of this AD prior to the accumulation of 900 hours total time in service. (c) Replace tailpipe, P/N F10A5B10003-7, with a new part of the same part number, or with a serviceable part of improved design, P/N F10A5RDB20217-3, and in either case install with back-up ring P/N F10A5B10606-11. (Falcon 10 Service Bulletin No. 0129, dated December 21, 1976, covers this subject.) This amendment becomes effective April 18, 1977.
96-26-03: This amendment supersedes an existing airworthiness directive (AD), applicable to all Fokker Model F28 Mark 0070 and 0100 series airplanes, that currently requires a revision to the Airplane Flight Manual (AFM) that will enable the flightcrew to determine if the thrust reversers are properly stowed and locked prior to take-off. In addition, the existing AD requires a revision to the maintenance program to incorporate instructions to perform checks of the thrust reverser system and correct thrust reverser malfunctions. That AD was prompted by results of a review, which indicated that a potential latent failure of the secondary lock actuator switch 1 of the thrust reverser system in the open position may occur, in addition to the potential failure of the secondary lock relay 1 in the energized position. This new AD adds a requirement to accomplish new modifications that will serve as terminating actions for the revisions to the AFM and maintenance program, and new repetitivechecks of the thrust reverser system. The actions specified in this AD are intended to ensure protection against inadvertent deployment of the thrust reversers during flight.
76-07-05: 76-07-05 BOEING: Amendment 39-2569. Applies to all Boeing Model 727 series airplanes, certificated in all categories, which are equipped with Boeing P/N 65-18949-1 nose landing gear release mechanism torsion shafts not affected by AD 73-26-06. Compliance required as indicated. \n\tTo prevent failure of the nose landing gear release mechanism torsion shaft and a resulting possible gear-up landing, accomplish the following: \n\tA.\tWithin the next 750 landings after the effective date of this AD, unless accomplished within the last 750 landings, and thereafter at intervals not to exceed 1,500 landings for shafts inspected in accordance with the ultrasonic inspection procedures or 2,400 landings for shafts inspected in accordance with the magnetic particle inspection procedures, inspect the P/N 65- 18949-1 shafts, reworked and nonreworked, which have accumulated 8,000 or more total landings since reworked or new, respectively, on or after the effective date of this AD, per paragraph Bbelow until the shaft is replaced per paragraph C. \n\tB.\tInspect the torsion shaft bearing surface in accordance with the ultrasonic or magnetic particle inspection procedures specified in paragraph III of Boeing Service Bulletin No. 727-32-238, or later FAA approved revisions, or inspect in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. Shafts found cracked must be replaced prior to further flight, per paragraph C or with either one of the following: \n\t\t1.\tA nonreworked P/N 65-18949-1 shaft which has accumulated less than 8,000 landings. (Upon accumulation of 8,000 landings the inspection requirements of paragraph A above apply); or \n\t\t2.\tAn uncracked shaft, P/N 65-18949-1, which has been reworked once in accordance with Boeing Service Bulletin No. 727-32-203, Revision 3, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. These shafts are subject to the inspection provisions of paragraph A upon accumulation of 8,000 landings after initial rework. Additional rework will not thereafter exempt the shaft from the inspection requirements. \n\tC.\tInstallation of a new improved shaft, P/N 65-86496-1, and associated parts in accordance with Boeing Service Bulletin Nos. 727-32-205, or 727-32-223, or later FAA approved revisions, or an equivalent installation approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, constitutes terminating action of this AD. \n\tD.\tFor the purpose of this AD, when conclusive records are not available to show the number of landings accumulated by a particular shaft, the number of landings may be computed by dividing the airplane time in service since the shaft was installed in the airplane by the operator's fleet average time per flight for his Model 727 airplanes. \n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made apart hereof pursuant to 5 U.S.C. 552(a)(1). \n\tAll persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. The documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98124. The documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington.\n \n\tThis amendment becomes effective May 11, 1976.
90-02-11: 90-02-11 PIPER: Amendment 39-6455. Applicability: Models PA-42, PA-42-720, and PA-42-720R (all serial numbers) airplanes certificated in any category. Compliance: Required within the next 25 hours time-in-service after the effective date of this AD, unless already accomplished. To preclude premature deterioration of the engine which could result in possible engine failure, accomplish the following: (a) Insert a copy of this AD in the Pilots Operating Handbook and FAA Approved Airplane Flight Manual (POH/AFM) for the applicable airplane and operate in accordance with the revised limitation: (1) For the Model PA-42 POH/AFM, revise the POH/AFM as follows: Insert Revision 8 of LK 1213 into the POH/AFM. (2) For the Models PA-42-720 and PA-42-720R, revise the POH/AFM as follows: (i) For the Model PA-42-720, insert Revision 7 of LK 1394 or VB 1314 into the POH/AFM. (ii) For the Model PA-42-720R, insert Revision 6 of LK 1485 into the POH/AFM. (b) The following annotation of the applicable pages of the POH/AFM may be accomplished in lieu of complying with paragraph (a). Locate the paragraph entitled "Fuel Specifications" or "Fuel" in the Limitations Section of the POH/AFM. In the first sentence of this paragraph, block out with permanent black ink the words "hot section inspections." Place 1/6 inch wide white self-adhesive correction tape over these blocked out words and type the following words "engine overhaul periods" on the correction tape. (c) The requirements of this AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operated by this person. The person accomplishing these actions must make the appropriate airplane maintenance record entry as prescribed by FAR 43.9 and FAR 91.173. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (e) An alternate method of compliance or adjustment of the compliance time which provides an equivalent level of safety, may be approved by the Manager, Atlanta Certification Office, Federal Aviation Administration, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. NOTE: The request should be forwarded through an FAA Maintenance Inspector, who will may add comments and send it to the Manager, Atlanta Aircraft Certification Office. All persons affected by this directive may obtain copies of the documents referred to herein upon request to the Piper Aircraft Corporation, 2926 Piper Drive, Vero Beach, Florida 32960, or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment (39-6455, AD 90-02-11) becomes effective on February 8, 1990.
2008-13-02: 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: Cracks have been found in the propeller blades and propeller hubs, for which ongoing controlling actions issued by the propeller TC [type certificate] holder (McCauley Propeller Systems) have been mandated by FAA Airworthiness Directive (AD) action. Current FAA ADs related to this subject are 2003-17-10 (which superseded AD 2003-15-01), 2004-23-16, 2005-24-08 and 2006-15-13. Cracking of the blade or hub can ultimately lead to blade release with potentially catastrophic consequences. * * * * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
90-01-03: 90-01-03 HONEYWELL, INC., SPERRY COMMERCIAL FLIGHT SYSTEMS GROUP, BUSINESS AND COMMUTER AVIATION SYSTEMS DIVISION (Sperry Corporation): Amendment 39-6442. Docket No. 89-NM-98-AD. Applicability: Honeywell AH-600 Attitude and Heading Reference System (AHRS) Strapdown Attitude and Heading Reference Unit (AHRU), part numbers 7003360-931, -932, -933, -934, -935, and -936, with serial numbers 0100 through 0277. Compliance: Required as indicated, unless previously accomplished. NOTE: These systems are known to be installed in, but not limited to, de Havilland Model DHC-8, British Aerospace Model BAe 125-800, Cessna Model 650, and Aerospatiale Model ATR42-300 series airplanes. To eliminate the possibility of the primary attitude and heading displays on both sides of the instrument panel failing simultaneously, accomplish the following: A. Within 10 days after January 9, 1989 (the effective date of Amendment 39-6093), inspect airplanes with Honeywell AH-600 AHRSinstalled to determine the part number, serial number, and Mod Level of the strapdown AHRU installed in the pilot's (Number 1) AHRS. Prior to further flight after inspection, remove all AHRU part numbers 7003360-931, -932, -933, -934, -935, and -936 with serial numbers 0100 through 0277, without Mod Level "F", from service in the pilot's (Number 1) AHRS. Install the same part number with Mod Level "F" incorporated, or modify the AHRU in accordance with Honeywell Inc., Service Bulletin 7003360-34-32, dated August 2, 1988. NOTE: Serial numbers of the strapdown AHRU are eight digit numbers; the first four are date code and the last four are the individual unit identifier. Serial numbers referred to in this AD are the last four numbers of the serial number. B. Within 60 calendar days after the effective date of this amendment, inspect airplanes with Honeywell AH-600 AHRS installed to determine the part number, serial number, and Mod Level of the strapdown AHRU installed in copilot's (Number 2) AHRS and the auxiliary (Number 3) AHRS. Within 45 days after the inspection, remove all AHRU part numbers 7003360-931, -932, -933, -934, -935, and -936, with serial numbers 0100 through 0277, without Mod Level "F", from service in the copilot's (Number 2) AHRS and the auxiliary (Number 3) AHRS. Install the same part number with Mod Level "F" incorporated, or modify the AHRU in accordance with Honeywell, Inc., Service Bulletin 7003360-34-32, dated August 2, 1988. 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, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment, and then send it to the Manager, Los Angeles Aircraft Certification Office. 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 Honeywell Inc., Sperry Commercial Flight Systems Group, Business and Commuter Aviation Systems Division, 5353 West Bell Road, Glendale, Arizona 85308. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. This AD supersedes AD 88-26-05, Amendment 39-6093. This amendment (39-6442, AD 90-01-03) becomes effective on February 5, 1990.
87-08-08 R3: