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80-04-02: 80-04-02 PRATT & WHITNEY AIRCRAFT OF CANADA, LTD.: Amendment 39-3693. Applies to Pratt & Whitney Aircraft of Canada, Ltd. (P&WACL) PT6A-6A, -6B, -6/C20 and -20 turboprop engines. Compliance required within the next 10 hours in service after the effective date of this AD unless already accomplished and every time the propeller reversing interconnect linkage is disconnected. To insure adequate engagement of push-pull control terminal P/N 3010175 into the clevis P/N 3010622 or 3012419, inspect for a maximum of three threads outside the locknut. If more than three threads are visible, re- rig the linkage in accordance with P&WACL Maintenance Manual, P/N 3015422 Part 3, Paragraph 91 and the appropriate aircraft maintenance manual or equivalent inspection or procedure. For clevises incorporating witness holes, a safety wire inserted through one hole should not be able to exit through the opposite hole. Where the safety wire passes through both holes, re-rig in accordance withP&WACL Maintenance Manual, P/N 3015422 Part 3, Paragraph 91 and the appropriate aircraft maintenance manual or equivalent inspection or procedure. Aircraft may be flown to a base for performance of maintenance required by this AD per FAR 21.197 or FAR 21.199. All equivalent inspections and procedures must be approved by the Chief, Engineering & Manufacturing Branch of the Eastern Region of the FAA. (DeHavilland Service Bulletin Nos. A6/387 and ATB/50 pertain to this subject.) This amendment is effective February 8, 1980.
2000-04-07: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace BAe Model ATP airplanes, that requires a one-time detailed visual inspection to detect incorrect installation or discrepancies (damage, bending, overheating, discoloration) of the circuit breaker and the cable terminations of the circuit breaker of the engine de-ice panel. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the engine intake de-icing system, which could result in loss of engine intake de-icing capability, accretion of ice in the intake duct, ice ingestion, and consequent engine flameout.
2004-23-17: The FAA is adopting a new airworthiness directive (AD) to supersede Airworthiness Directive 91-03-15, which applies to certain Mooney Airplane Company, Inc., (Mooney) Model M20M airplanes. AD 91-03- 15 currently requires you to replace the tailpipe coupling with improved tailpipe coupling. Since we issued AD 91-03-15, a fire erupted in the lower left cockpit area on one of the airplanes affected by AD 91-03-15. The V-clamp that attaches the exhaust tailpipe to the turbocharger fell off, which allowed the exhaust tailpipe to detach from the turbocharger. Hot exhaust gases from the turbocharger outlet blasted the lower left firewall. This AD requires you to replace the existing radiant heat shield with the new improved design heat shield, deflector kit; replace the existing exhaust tailpipe-to-turbocharger V- band clamp with the new design V-band clamp; and modify the hydraulic brake fluid poly line. We are issuing this AD to prevent the V-clamp from detaching from the turbocharger and to prevent exposure of the firewall to hot exhaust gases, which could result in an in-flight fire. An in-flight fire could lead to loss of control of the airplane and passenger injury.
2000-04-10: This amendment adopts a new airworthiness directive (AD) that is applicable to Hoffmann Propeller Co. HO27( ) and HO4/27 series propellers. This action requires installing improved propeller mounting bolts to a higher torque value, operating the airplane for one flight, checking the torque, and retorquing, as required, to the correct torque value. This amendment is prompted by reports of insufficient torque of propeller mounting bolts due to operating conditions, loads, and environmental conditions such as humidity and temperature. The actions specified in this AD are intended to prevent propeller mounting bolt failure, which could result in propeller separation and loss of control of the airplane.
2014-03-02: We are adopting a new airworthiness directive (AD) for certain Airbus Model AS332C, AS332L, AS332L1, AS332L2, and SA330J helicopters. This AD requires inspecting the crimping of the ball joint of the upper- and lower- end-fittings of the main servo-control and, depending on findings, replacing the main servo-control or repairing the ball joint. This AD was prompted by incidents of missing crimping on the ball joints of servo-control end-fittings. The actions of this AD are intended to prevent failure of a main servo-control upper end fitting, and subsequent failure of the flight controls and loss of control of the helicopter.
2000-04-01: This amendment adopts a new airworthiness directive (AD) that applies to certain Cessna Aircraft Company (Cessna) Models 172R, 172S, 182S, 206H, and T206H airplanes. This AD requires that you accomplish the following: - inspect the oil pressure switch to determine if the oil pressure switch is part-number (P/N) 77041 or P/N 83278; and - replace any P/N 77041 oil pressure switch with a P/N 83278 switch. This AD is the result of reports of failure of the oil pressure switch diaphragm. The actions specified by this AD are intended to prevent loss of engine oil through the failure of the oil pressure switch diaphragm, which could result in partial or complete loss of engine power.
89-03-08: 89-03-08 EMPRESA BRASILEIRA DE AERONAUTICA, S.A. (EMBRAER): Amendment 39-6129. Applicability: Model EMB-120 series airplanes, as listed in Embraer Service Bulletin 120-024-0031, dated October 21, 1988, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent the loss of essential navigation systems, accomplish the following: A. Within the next 25 hours time-in-service after the effective date of this AD, accomplish the following, in accordance with Embraer Service Bulletin 120-024-0031, dated October 21, 1988: 1. Install self-locking nuts, P/N LN9161-05, to secure the No. 1 and No. 2 auxiliary generator control voltage sensor wires to the connecting bars at relays K0035 and K0036. 2. Install placard 120-47147-001 on the left-hand relay box cover. The placard shall state, "USE LN9161-05 NUTS FOR K0035 AND K0036 IN PLACE OF ORIGINAL NUTS. SEE MAINTENANCE MANUAL 24-52-00." B. An alternate means of complianceor adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Atlanta Aircraft Certification Office, FAA, Central Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Atlanta Aircraft Certification Office. C. 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 EMBRAER, 276 S.W. 34th Street, Fort Lauderdale, Florida 33315. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, Central Region, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta,Georgia. This amendment (39-6129, AD 89-03-08) becomes effective February 15, 1989.
80-01-03: 80-01-03 RAVEN INDUSTRIES, INC.: Amendment 39-3648. Applies to model S-50A, serial no. S50A-275, model S-55A, serial nos. S-55A-330 to S-55A-624, and model S-60A, serial nos. S-60A-102 to S-60A-138 hot air balloons certificated in all categories which have installed the parachute top vent. Compliance required before further flight unless already accomplished. To allow proper release of the parachute top, accomplish the following or an equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA Rocky Mountain Region: Remove all but the middle 1 inch of the length of the "Velcro" tape "hooks" on each of the 24 4-inch long tapes found on the envelope by use of a razorblade or sharp knife. Raven Service Bulletin No. 111 dated December 19, 1979, covers this same subject. This amendment becomes effective January 7, 1980
84-09-06: 84-09-06 DeHAVILLAND: Amendment 39-4858. Applies to all Models DHC-2 MK. I (L-20A, YL-20, U-6 and U-6A), MK. II Beaver and MK. III Turbo Beaver series airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent the failure of the horizontal torque tube at the base of the control column which may cause loss of airplane control, accomplish the following: (a) Within the next 5O hours time-in-service after the effective date of this AD, unless accomplished within the last 150 hours time-in-service, and subsequently at intervals thereafter not to exceed 200 hours time-in-service from the last inspection, visually inspect the control column lower sub-assembly, P/N C2CF843A (single control column) and C2CF1977AND (dual control column) for cracks in accordance with DeHavilland Service Bulletin No. 2/28, Revision B, dated May 13, 1983, Section ACCOMPLISHMENT INSTRUCTIONS paragraphs 1a, lb, 1c and If or an FAA approvedequivalent. (b) If no cracks are found, return the airplane to service and repeat the inspections required by paragraph (a) of this AD. (c) If cracks 0.5 inches or less in length in the weld area are found in the control column assembly P/N C2CF843A (single control column) and C2CF1977AND (dual control column), repair the above-noted assembly prior to further flight as instructed in the ACCOMPLISHMENT INSTRUCTIONS Section of Service Bulletin No. 2/28 Revision B. (d) If cracks longer than 0.5 inches are found in the control column assembly P/N C2CF843A (single control column) and C2CF1977AND (dual control column), replace the assembly prior to further flight as instructed in the ACCOMPLISHMENT INSTRUCTIONS Section of Service Bulletin No. 2/28 Revision B. (e) Aircraft maintenance record entries shall be made and a report in writing of the initial inspection findings, positive or negative, shall be made to the FAA, New York Aircraft Certification Office, New England Region, Attention: ANE-172, 181 South Franklin Avenue, Valley Stream, New York 11581. A negative finding report shall include the time-in-service of the aircraft and of the component. A positive finding report shall include the above information and state the location and length of any crack found. Reports may be submitted by letter to the New England Region, or through the Malfunction or Defect (M or D) procedure. (The paper work reporting requirement has been cleared by the Office of Management and Budget under Clearance Number 2100 0056.) (f) The airplane may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (g) Alternate methods of compliance with this AD may be used when they provide an equivalent level of safety and are approved by the Manager, New York Aircraft Certification Office, FAA New England Region, 181 South Franklin Avenue, Valley Stream, New York 11581. (h) The repetitive inspection intervalrequired by (a) may be increased by the Manager, New York Aircraft Certification Office, FAA New England Region upon receipt of substantiating data submitted through an FAA Maintenance Inspector. This amendment becomes effective on May 10, 1984.
2023-02-05: The FAA is adopting a new airworthiness directive (AD) for all General Electric Company (GE) CF34-8C1, CF34-8C5, CF34-8C5A1, CF34- 8C5B1, CF34-8C5A2, CF34-8C5A3, CF34-8E2, CF34-8E2A1, CF34-8E5, CF34- 8E5A1, CF34-8E5A2, CF34-8E6, and CF34-8E6A1 model turbofan engines. This AD was prompted by a predicted reduction in the cyclic life of the combustion chamber assembly aft flange. This AD requires revisions to the airworthiness limitations section (ALS) of the existing engine manual (EM) and the operator's existing approved maintenance or inspection program, as applicable, to incorporate initial and repetitive fluorescent penetrant inspections (FPIs) of the combustion chamber assembly. The FAA is issuing this AD to address the unsafe condition on these products.