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70-16-07: 70-16-07 HUGHES: Amendment 39-1059. Applies to Model 369 Series helicopters, certificated in all categories, which incorporate P/N 369A1100 and P/N 369A1100-501 main rotor blade serial numbers listed in Hughes Service Information Notice No. HN-8, dated November 19, 1969, or later FAA approved revision and serial numbers listed in OH-6A Information Notice Numbers, 120, 120A, and 120B dated October 24, 1969; November 5, 1969; and December 19, 1969, respectively. Compliance required as indicated: To prevent failure of the main rotor blade P/N 369A1100 and P/N 369A1100-501 accomplish the following or an equivalent inspection procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region: Within 25 hours time in service after the effective date of this AD, unless already accomplished, determine the identification notation on the blade top and bottom doublers in accordance with the procedures in Part I a, b, and c of Hughes Service Information Notice No. HN-8, dated November 19, 1969, or later FAA approved revision. (a) For blades displaying "PR-12" ink stamps or blades lacking ink stamps below the part number on either of the doublers: (1) Inspect prior to further flight in accordance with Part I d of Hughes Service Information Notice No. HN-8, above. (2) If indications of cracks or doubler peeling or separation are found, remove the blade from service prior to further flight. (3) If indications of cracks or doubler peeling or separation are not found, repeat the inspection required under (1) above, at periods not to exceed 25 hours time in service from the last inspection until the blades are removed from service as specified in (4), below. (4) Remove from service prior to the accumulation of 100 hours time in service from the effective date of this AD. (b) Blades displaying ink stamp letters and numerals other than "PR-12" below the part number on both doublers may be returned to service with no further inspection, following refinishing and identification per Hughes Service Information Notice No. HN-8, dated November 19, 1969, or later FAA approved revision. This amendment becomes effective August 8, 1970.
91-09-12: 91-09-12 BOEING: Amendment 39-6976. Docket No. 90-NM-245-AD. \n\n\tApplicability: All Model 737-300, 737-400, and 737-500 series airplanes, certificated in any category. \n\n\tCompliance: Required within the next 36 months after the effective date of this AD, unless previously accomplished. \n\n\tTo preclude cross connection of the engine fire extinguishing wiring and plumbing during maintenance, accomplish the following: \n\n\tA.\tFor airplanes listed in Boeing Service Bulletin 737-26-1067, dated June 28, 1990: Modify the engine fire extinguishing system wiring and plumbing in accordance with the service bulletin. Accomplishment of this modification constitutes terminating action for the repetitive inspections and functional tests required by Airworthiness Directive 89-03-51, Amendment 39-6213, on Boeing Model 737-300, 737-400, and 737-500 airplanes following maintenance on the engine fire extinguishing wiring and plumbing. \n\n\tB.\tFor airplanes line position 1890 and subsequent on which PRR 34774 or an equivalent modification was incorporated during production: The repetitive inspections and functional tests required by Airworthiness Directive 89-03-51, Amendment 39-6213, are terminated. \n\n\tC.\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO.\n \n\tD.\tSpecial 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. \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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. \n\n\tThis amendment (39-6976, AD 91-09-12) becomes effective on May 28, 1991.
2014-04-11: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS350B, BA, B1, B2, B3, and D, and Model AS355E, F, F1, F2, and N helicopters with certain tail rotor (T/R) blades. This AD requires installing additional rivets to secure each T/R blade trailing edge tab (tab), and inspecting for evidence of debonding of the tab after the rivets are installed. This AD was prompted by reports of T/R blade tab debonding. The actions of this AD are intended to prevent loss of a T/R blade tab, which could result in excessive vibration and loss of control of the helicopter.
2014-05-02: We are superseding Airworthiness Directive (AD) 2002-10-11, which applied to certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2002-10-11 required repetitive inspections for cracking and corrosion of the aft pressure bulkhead, and corrective actions if necessary; and, for certain airplanes, enlargement of frame chord drain holes, and repetitive inspections of the frame chord drain path for debris, and corrective actions if necessary. This new AD specifies a drain path inspection for all airplanes. For certain airplanes, this new AD reduces the repetitive inspection interval; and adds repetitive inspections of the frame chord drain path for obstructions and debris, and corrective actions if necessary. This AD was prompted by three reports of severe corrosion in the area affected by AD 2002-10-11. We are issuing this AD to detect and correct corrosion or cracking of the aft pressure bulkhead, which could result in loss of the aft pressure bulkhead web and stiffeners, and consequent rapid decompression of the airplane.
2014-03-01: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB139 and AW139 helicopters with a certain wire strike protection system (WSPS) top cable cutter assembly installed. This AD requires reworking or replacing the top cable cutter assembly to increase clearance between the WSPS and the main rotor (M/R) blades and requires that the reworked or replaced part be marked at the end of the part number to reflect the field modification. This AD was prompted by a report of in-flight contact between the top cable-cutter assembly and two M/R blades. The actions of this AD are intended to prevent damage to the M/R blades and subsequent loss of helicopter control.
91-15-22: 91-15-22 MCDONNELL DOUGLAS: Amendment 39-7087. Docket No. 91-NM-18-AD. \n\n\tApplicability: McDonnell Douglas Model DC-10-40 series airplanes, as listed in McDonnell Douglas Service Bulletin 71-154, dated January 18, 1991, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent fuel line and engine fuel shutoff cable damage and possible fire caused by an uncontained engine failure, accomplish the following: \n\n\tA.\tWithin one year after the effective date of this AD, replace the fuel line shield on the left side of the number 2 engine bellmouth panel, and install an additional plate, as applicable, in accordance with the accomplishment instructions of McDonnell Douglas DC-10 Service Bulletin 71-154, dated January 18, 1991. \n\n\tB.\tAn 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, Los Angeles Aircraft Certification Office (AC0), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may concur or comment and then send it to the Manager, Los Angeles ACO. \n\n\tC.\tSpecial 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. \n\n\tD.\tThe replacement and installation requirements shall be done in accordance with McDonnell Douglas DC-10 Service Bulletin 71-154, dated January 18, 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 McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: DC-10 Technical Publications, Technical Administrative Support C1-L5B. Copies may be inspected at the FAA, Transport Airplane Directorate, Renton, Washington; or at the LosAngeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. \n\n\tThis amendment (39-7087, AD 91-15-22) becomes effective on September 9, 1991.
2014-03-03: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 310, 320, 340, 401, 402, 411, 414, and 421 airplanes. This AD was prompted by an investigation of recent and historical icing-related accidents and incidents for the products listed above. This AD requires either having the supplemental airplane flight manual/airplane flight manual supplement (SAFM/AFMS) inside the airplane and accessible to the pilot during the airplane's operation or installing a placard that prohibits flight into known icing conditions and installing a placard that increases published airspeed on approach at least 17 mph (15 knots) in case of an inadvertent encounter with icing. We are issuing this AD to correct the unsafe condition on these products.
2014-03-05: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD-700-1A10 airplanes. This AD was prompted by a report that the manufacturer has determined that some completion centers used the heater/brake monitoring unit (HBMU) logic circuit to control the line voltage of the drain mast heaters. Since the drain mast heaters are connected in parallel with the number 2 pitot static (PS) probe heater circuit, a number 2 PS probe heater failure may not be detected by the fault monitoring capabilities of the HBMU. This AD requires modification of the air data probes and sensors. We are issuing this AD to detect and correct an unannunciated failure of two PS probe heaters, which could affect controllability of the airplane in icing conditions.
2014-02-06: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB412 helicopters. This AD requires visually inspecting the main rotor swashplate outer ring (outer ring) for a crack and replacing that outer ring if a crack exists. This AD is prompted by two cases of cracks caused by fatigue on certain outer rings. These actions are intended to prevent the failure of the outer ring, which would lead to loss of main rotor blade pitch control and subsequently loss of helicopter control.
2018-07-16: We are adopting a new airworthiness directive (AD) for all Austro Engine GmbH model E4 and E4P diesel piston engines. This AD requires replacement of the waste gate controller and the control rod circlip. This AD was prompted by reports of broken or disconnected turbocharger waste gate control rods on some engines. We are issuing this AD to address the unsafe condition on these products.