Results
75-24-08: 75-24-08 CANADAIR: Amendment 39-2431. Applies to all CL-44D4 and CL-44J airplanes, certificated in all categories, but not altered in accordance with Canadair Service Bulletin 44-478. Compliance required within the next 25 landings, unless already accomplished within the last 275 landings, and thereafter at subsequent intervals not to exceed 300 landings, after the effective date of this AD. To detect fretted, pitted or cracked main landing gear actuator attachment bolts, P/N SD300-55880, SD300-65779 or SD300-65779-12S, inspect and, if necessary, replace bolts in accordance with Canadair Service Information Circular 328-CL44D4, Issue 2 or an approved equivalent inspection and part replacement. Bolts found to be in good condition may be reinstalled provided: (a) they are of a type specified for replacement in the Canadair SIC 328-CL44D4 or are approved equivalent bolts; (b) they have not exceeded the life limits specified in Canadair SIC 328-CL44D4; and (c)they have not been reworked. Equivalent inspection or parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Upon request, with substantiating data submitted through an FAA maintenance inspector, the compliance time of this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective November 25, 1975.
2012-06-22: We are adopting a new airworthiness directive (AD) for all Airbus Model A340-500 and Model -600 series airplanes. This AD requires performing repetitive high frequency eddy current inspections of the external radius on upper horizontal cruciform fitting at frame (FR) 47 on the left- and right-hand sides for cracks, and repairing the cracks if necessary. This AD was prompted by reports that during fatigue testing, damages occurred in the external radius on the upper horizontal cruciform fitting at FR47 on the left- and right-hand sides. We are issuing this AD to detect and correct fatigue cracking, which could adversely affect the structural integrity of the airplane.
2012-06-18: We are adopting a new airworthiness directive (AD) for all Pratt & Whitney PW4050, PW4052, PW4056, PW4060, PW4060A, PW4060C, PW4062, PW4062A, PW4152, PW4156, PW4156A, PW4158, PW4160, PW4460, PW4462, and PW4650 turbofan engines, including models with any dash number suffix. This AD was prompted by reports of five engine in-flight shutdowns and seven unplanned engine removals. This AD requires inspections, cleaning, and engine modifications to address coking in the No. 4 bearing compartment and in the oil pressure and scavenge tubes. We are issuing this AD to prevent an engine fire, a fractured fan drive shaft, and damage to the airplane.
75-17-04: 75-17-04 LOCKHEED: Amendment 39-2300 as amended by Amendment 39-3185. Applies to all Model 382 series airplanes, serial numbers 3946 and 4101 through 4751, certificated in all categories. Compliance required within the next 325 hours' time in service on airplanes which have accumulated 10,000 or more flight hours and thereafter at each "C" check inspection. (a) To detect cracks in the main frames, inspect the frames in accordance with Lockheed Service Bulletin A382-189, or later FAA approved revision, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. (b) In the event a crack or cracks are found, before further flight, contact the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, P.O. Box 20636, Atlanta, Georgia 30320. (c) The inspection required by the A.D. may be discontinued on those airplanes which have been repaired in accordance with Lockheed Service Bulletin A382-189, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. Amendment 39-2300 became effective August 8, 1975. This Amendment 39-3185 becomes effective April 21, 1978.
2012-06-08: We are adopting a new airworthiness directive (AD) for certain Airbus Model A340-211, -212, -311, and -312 airplanes. This AD requires repetitive inspections for cracking at the fastener hole area just above stringer 28, of both left- and right-hand fuselage frame 39.1, and repair if necessary. This AD was prompted by a determination that certain airplanes were not included in a certain airworthiness limitation item (ALI) task (inspections for cracking of the fuselage frame 39.1) and that the inspections must be done to address the identified unsafe condition. We are issuing this AD to detect and correct cracking in the fuselage that could result in reduced structural integrity of the airplane.
68-17-06: 68-17-06 BEECH: Amendment 39-641. Applies to Models 23, A23 and A23A, Serial Numbers M-1 through M-1034; Model A23-19, Serial Numbers MB-1 through MB-264; Model A23-24, Serial Numbers MA-1 through MA-233. Compliance: Required as indicated. To prevent inadvertent engagement of parking brake, in flight, accomplish the following: (A) For Models 23, A23 and A23A, Serial Numbers M-555 through M-1034; Model A23-19, Serial Numbers MB-1 through MB-264; and Model A23-24, Serial Numbers MA-1 through MA-233 modify the master brake cylinders as set forth in (C) or (D). (B) For Models 23, A23 and A23A, Serial Numbers M-1 through M-554, inspect the left master brake cylinder. If brake cylinder Part No. 169-380006 is installed no further action is required. If brake cylinders Part No. VHR-625NL are installed modify as set forth in (C) or (D). (C) Remove the steel ball Part No. A134-9 from the parking brake check valve on both left and right master brake cylinders soas to disengage the parking brake and thereafter operationally check the brakes to assure proper operation; or, (D) Modify the left master brake cylinder in accordance with either Beech Class 1, Service Instruction 0092-220 and drill out the floor board beneath the left brake pedal in accordance with procedures set forth in the aforesaid Beech Service Instruction, or install the improved braking system provided by Beech Service Letter No. 67-12, Revision 1. (E) The foregoing modification must be accomplished prior to further flight except the airplane may be flown in accordance with Federal Aviation Regulation 21.197 to a base where the repair can be performed. This amendment becomes effective August 27, 1968.
75-06-07: 75-06-07 MCDONNELL DOUGLAS: Amendment 39-2126 as amended by Amendment 39-2605 is further amended by Amendment 39-3227. Applies to Douglas Model DC-10-10, -30, -30F, and -40 series airplanes, certificated in all categories, with factory serial numbers as indicated in Douglas Service Bulletin No. 52-132, Revision 1, dated February 21, 1975, or later FAA-approved revisions. \n\n\tTo insure proper functioning of forward passenger doors during emergency operation, accomplish the following: \n\n\t(a)\tCompliance required within the next 300 hours' time in service after the effective date of this AD, unless already accomplished. \n\n\t\t(1)\tInspect the forward passenger door (L & R) operating mechanisms for proper rigging, broken, damaged, or corroded cables, and adjust rigging or replace cables as required, in accordance with Douglas Service Bulletin No. 52-132, Revision 1, dated February 21, 1975, or later FAA-approved revisions. \n\n\t\t(2)\tAfter accomplishment of the inspection per paragraph (a)(1) above, check pneumatic operation of doors (L & R) from both the inside and outside of the aircraft. \n\n\t(b)\tCompliance required on airplanes with 5,000 hours' or more total time in service after the effective date of this AD, unless already accomplished per paragraph (a) above within the last 1500 hours' time in service, and thereafter at intervals not to exceed 2250 hours' time in service from the last inspection. \n\n\t\t(1)\tReinspect the forward passenger door (L & R) mechanism cables, and replace if required, in accordance with Douglas Service Bulletin No. 52-132, Revision 1, dated February 21, 1975, or later FAA-approved revisions. \n\n\t\t(2)\tIf cable(s) has been replaced, recheck pneumatic operation of applicable door(s) from both the inside and outside of the aircraft. \n\n\t\t(3)\tThe repetitive 2250-hour inspections required by paragraph (b) may be discontinued provided stainless steel cables and swivel clevises are installed in accordance with McDonnell Douglas Service Bulletin No. 52-152, dated February 3, 1976, or later FAA-approved revisions. \n\n\t(c)\tCompliance required within the next 5000 hours' time in service after accomplishment of the inspection per paragraph (a) above, and thereafter at intervals not to exceed 5000 hours' time in service from the last inspection. \n\n\t\t(1)\tReinspect the forward passenger door (L & R) mechanism rigging, and adjust if required, in accordance with Douglas Service Bulletin No. 52-132, Revision 1, dated February 21, 1975, or later FAA-approved revisions. \n\n\t\t(2)\tIf rigging has been adjusted, recheck pneumatic operation of applicable door(s) from both the inside and outside of the aircraft. \n\n\t\t(3)\tThe repetitive 5000-hour inspections required by paragraph (c) may be discontinued provided any one of the following combination of McDonnell Douglas Service Bulletins, or later FAA-approved revisions, has been accomplished: \n\n\t\t\t(i)\tS./B 52-118, Revision 1, dated February 14, 1975, (Installation of new cams on control mechanism), S/B 52-140, Revision 4, dated August 29, 1975, (Installation of return springs on reservoir actuator), S/B 52-146, Revision 1, dated November 21, 1975, (Installation of direct drive visible downlock), S/B 52-152, dated February 3, 1976, (Installation of stainless steel cables and swivel clevises); \n\n\t\t\t(ii)\tS/B 52-118, Revision 1, dated February 14, 1975, S/B 52-146, Revision 1, dated November 21, 1975, S/B 52-152, dated February 3, 1976, and S/B 52-154, Revision 1, dated March 1, 1976, (Installation of new reservoir control assembly) \n\n\t\t\t(iii)\tS/B 52-140, Revision 4, dated August 29, 1975, S/B 52-150, dated September 9, 1975, (Installation of combination up/downlock assembly). S/B 52-152, dated February 3, 1976; or \n\n\t\t\t(iv)\tS/B 52-150, dated September 9, 1975, S/B 52-152, dated February 3, 1976, and S/B 52-154, Revision 1, dated March 1, 1976. \n\n\t\t(4)\tThe repetitive 5000-hour inspection required by paragraph (c) may be replaced by satisfactory accomplishment, at 6000-hour intervals of both electrical and pneumatic door operational checks at applicable doors per Douglas Service Bulletin No. 52-132, Revision 1, dated February 21, 1975, or later FAA approved revisions, provided that all service bulletins except SB 52-152, required by any one of the combination of service bulletins in paragraph (c)(3) have been accomplished. \n\n\t(d)\tThe Chief, Aircraft Engineering Division, FAA Western Region, may approve equivalent inspections and modifications upon submittal of substantiating data. \n\n\t(e)\tAircraft may be flown to a base for accomplishment of the maintenance required by this AD per FAR's 21.197 and 21.199. \n\n\tAmendment 39-2126 became effective April 14, 1975. \n\n\tAmendment 39-2605 became effective May 17, 1976. \n\n\tThis amendment 39-3227 becomes effective July 6, 1978.
2012-06-04: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by reports of difficulties in opening the airstair door. This AD requires inspecting the structure and gearbox drain paths for blockages by sealant, and removing any blockages. We are issuing this AD to detect and correct drain paths blocked by sealant, resulting in an airstair door that is unable to be opened, which could hinder evacuation in the event of an emergency.
2012-06-01: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company Model 560XL airplanes. This AD was prompted by reports of jammed or stiff rudder control due to water freezing on the rudder bias cables and pulleys of the stinger. This AD requires modification of the drain installation of the tailcone stinger on the aft canted bulkhead, inspections for drain holes in the forward and aft frames, and modification of the drain holes. We are issuing this AD to prevent ice accumulation on the cables and pulleys of the stinger, which could result in jamming of the rudder and consequent reduced controllability of the airplane.
2012-05-03: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. This AD was prompted by a design review following a ground fire incident and reports of flammable fluid leaks from the wing leading edge area onto the engine exhaust area. This AD requires modifying the fluid drain path in the leading edge area of the wing. We are issuing this AD to prevent flammable fluid from leaking onto the engine exhaust nozzle, which could result in a fire.