Results
2000-07-29: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300, A310, and A300-600 series airplanes, that currently requires a one-time operational test of the fire shut-off valves (FSOV) to determine if the FSOV's are functioning correctly, and replacement of failed parts with new or serviceable parts. This amendment requires repetitive performance of the operational test. This amendment also limits the applicability to airplanes installed with certain FSOV's. 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 detect and correct failure of the FSOV's to close, which could result in failure of the engine fire shut-off system, and consequent inability to extinguish an engine fire.
80-06-05: 80-06-05 SLICK ELECTRO, INC.: Amendment 39-3718. Applies to the following Slick magneto models and associated serial and impulse coupling numbers: MAGNETO MODEL NO. (1) SERIAL NO. (1) (2) IMPULSE COUPLING NO. (1) 447 & 447R 9040001 thru 9040049 M2374 662 & 662R 9020462 thru 9070000 M2362 664 & 664R 9040001 thru 9040086 M2370 680 & 680R 9020462 thru 9070000 M2369 4151 & 4151R 9020017 thru 9070000 M1709 4152 & 4152R 9020017 thru 9070000 M1709 4181 & 4181R 9020017 thru 9070000 M1709 4201 & 4201R 9020210 thru 9070000 M3007 4251 & 4251R 9030001 thru 9070000 M3163 4281 & 4281R 9030001 thru 9070000 M3007 4230 & 4230R 9040001 thru 9040197 M3068 6210 8090073 thru 9070000 M3050 6214 8050001 thru 9070000 M3089 (3) M2371, M3100, & M3165 NOTES: (1) Any of the units listed were manufactured subsequent to January 1979. (2) Any magneto serial numbers between and including the lower and upper limits as shown are affected by this AD. (3) These coupling numbers are for parts used as spares and also must be tested. The magneto models as listed above are installed on, but not limited to, the following engines: Lycoming AEIO-360 AEIO-320 IO-320 O-235 O-320 O-360 Continental A-65-8 A-75-8 C-85-8 C-90-8 O-200-A O-300-A, -B, -C, -D O-470-U IO-360-KB IO-470 IO-520-A, -B, -F TSIO-470 TSIO-520-T Compliance is required as indicated unless already accomplished. To prevent a possible magneto failure and subsequent engine or accessory malfunction, accomplish the following: Prior to the next ten (10) hours of aircraft time in service, or within the next thirty (30) calendar days from the date of this AD, whichever occurs first, complete the following comparative hardness test procedures: 1. Remove the impulse coupling magneto(s) from the engine per engine manufacturer's instructions. 2. Remove the impulse coupling assembly from the magneto frame per Slick's maintenance and overhaul instructions. 3. Establish a reference level of acceptable metal hardness by sliding a fine cut mill file over the flat surface of either pawl. The file will slide freely and will only burnish the hard surface of the pawl. 4. By a similar filing action, test for the hardness of each of the two rivet heads. 5. If there is resistance to sliding and material is removed from the rivet head, the rivet has not been heat treated and the coupling assembly must be replaced. Return the defective coupling assembly to a Slick Electro, Inc. distributor. 6. If hardness of the rivet heads and pawls are equivalent, reassemble and identify AD compliance by metal stamping a letter "C" on the Slick insignia located on the side of the magneto identification plate. 7. If the results of the comparative hardness test on the rivet(s) are questionable, the coupling assembly must be replaced. This amendment becomes effective March 28, 1980, as to all persons except those to whom it was made immediately effective by the airmail letter dated February 4, 1980, which contained this amendment.
2000-07-25: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Gulfstream Model G-IV series airplanes. This action requires modification of the power feeder cable assemblies of the left and right engine alternators. This amendment is prompted by an incident of an in-flight engine fire on a Model G-IV series airplane due to chafing of the power feeder cable assembly of an engine alternator. The actions specified in this AD are intended to prevent interference and chafing between the alternator power feeder cables and adjacent structure, which could result in an electrical short circuit and consequent fire ignition source in the engine compartment.
88-05-02: 88-05-02 BRITISH AEROSPACE (BAe) PLC: Amendment 39-5858. Applies to Model DH/BH/HS 125 series airplanes listed in BAe 125 Service Bulletins 57-67 and 53-63, both dated February 27, 1987, certificated in any category. Compliance is required as indicated, unless previously accomplished. To detect fatigue cracking in the airplane structure, which could result in the inability of the structure to meet required loads, accomplish the following: A. For airplane serial numbers as listed in BAe-125 Service Bulletin 57-67 dated February 27, 1987: Prior to the accumulation of 12,000 flights, or within 8 months after the effective date of this AD, whichever occurs later, visually inspect the wing bottom skin for cracks at the flap outboard hinge fitting in accordance with that service bulletin. Repair detected cracks prior to further flight in accordance with an FAA approved method. B. For airplane serial numbers as listed in BAe-125 Service Bulletin 53-63, dated February27, 1987: Prior to the accumulation of 7,500 flights, or within 6 months after the effective date of this AD, whichever occurs later, visually inspect the fuselage skin beneath the canopy blister for cracks in accordance with that service bulletin. Repair detected cracks prior to further flight in accordance with an FAA approved method. C. An 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. D. Special 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 required by 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, Inc., Service Bulletin Librarian, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. 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. This amendment becomes effective April 6, 1988.
2000-07-21: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires a general visual inspection of wiring behind the control panel of the auxiliary power unit (APU) located in the cockpit to detect chafing; repair if necessary; and modification of the wiring. This amendment is prompted by an incident of chafing of wire bundles of the control module of the APU. The actions specified by this AD are intended to prevent such chafing and resultant arcing due to insufficient clearance between the wire bundles and the airplane structure, which could result in smoke and fire in the flight deck.
2015-02-08: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Corporation (RRC) AE 2100 series turboprop engines and AE 3007A and 3007C series turbofan engines. This AD was prompted by reports of pitting in the wheel bores and subsequent RRC analysis that concluded that lower life limits are needed for the affected turbine wheels. This AD requires a reduction for the approved life limits of the affected turbine wheels. This AD also requires an eddy current inspection (ECI) of certain RRC engines with affected turbine wheels. We are issuing this AD to prevent uncontained failure of the turbine wheels, damage to the engine, and damage to the airplane.
2000-07-23: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100 series airplanes, that requires changing the power supply for the thunderstorm lights from the left secondary bus to the left essential bus. 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 a failure of the thunderstorm lights in the cockpit after loss of all generated electrical power. This condition could result in the cockpit instruments not being visible to the flight crew during certain emergency procedures, and consequent reduced controllability of the airplane.
49-38-01: 49-38-01 CONVAIR: Applies to All Model 240 Aircraft Incorporating Original Type Nose Strut Outer Cylinder, Bendix P/N 156842. To be accomplished on No. 1 inspection on all nose landing gear struts whose total operating time exceeds 1,000 hours. Cracking of the nose gear landing struts in the areas directly below the drag link attachment legs, has been experienced on some CV-240 service aircraft whose total time exceeds approximately 1,000 hours. These cracks appear to be the result of repeated loadings experienced by the gear during landings. In order to insure the continued airworthiness of the aircraft, the nose landing gear shall be examined closely, using visual means, for evidence of any cracks in the areas directly below the drag strut attachment lugs. When cracks are found, it may be possible to repair the damage by grinding, blending and polishing, depending upon the extent and depth of the cracks. All struts not eligible for such repairs are to be retired from service. (Bendix Service Bulletin L. G. 509 covers the subject.) The above-described inspection may be discontinued on those struts which have been reinforced by the addition of a support clamp and eyebolts, or their equivalent, to alleviate the loading condition which caused the development of cracks. Struts reworked in accordance with Bendix Service Bulletin L.G. 511 and incorporating a support clamp and eyebolts in accordance with Bendix Service Bulletin L.G. 510 are eligible for service and do not require the above inspection. (Bendix Service Bulletin L.G. 310 covers this same subject.)
2015-02-27: We are superseding Airworthiness Directive (AD) 2013-19-19 for certain Eurocopter France Model AS332C, AS332L, AS332L1, AS332L2, and EC225LP helicopters. AD 2013-19-19 required replacing certain serial- numbered main gearbox (MGB) bevel gear vertical shafts and inspecting and replacing, if necessary, each MGB bevel gear vertical shaft (shaft). This new AD requires the same actions as AD 2013-19-19 but corrects an error in the term used to identify an inspection qualification and updates the type certificate holder's name. This AD is prompted by two incidents of emergency ditching after warning indications of loss of MGB oil pressure. These actions are intended to detect a cracked shaft, which could result in loss of MGB oil pressure, loss of the MGB lubrication system, and subsequent loss of control of the helicopter.
2000-07-16: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F series airplanes, that currently requires modification of the external power feeder cable clamping installation. This amendment also requires a detailed visual inspection of the external power feeder cables to detect chafed or damaged wires; and repair, if necessary. This amendment is prompted by reports of damage to the external power feeder cables located under the forward cargo compartment floor, which was caused by excessive cable length and/or maintenance personnel stepping on the cables. The actions specified by this AD are intended to prevent arcing from occurring under the forward cargo compartment floor as a result of damaged external power feeder cables, a situation that could lead to a fire at this location.
70-16-01: 70-16-01 WOODWARD: Amdt. 39-1054. Applies to Woodward Governor Company primary turbo propeller governors mounted on United Aircraft of Canada PT6A series engines installed in airplanes incorporating propeller reversing provisions and Woodward Governor Company overspeed turbo propeller governors mounted on United Aircraft of Canada PT6A series engines installed in airplanes having auto feathering provisions. Compliance: Required within the next 50 hours' time in service after the effective date of this AD, unless previously accomplished. To prevent uncontrolled feathering accomplish the following or an equivalent procedure approved by the Chief, Engineering & Manufacturing Branch, FAA, Central Region. A) On primary propeller governors inspect for safety wire security the three coil retaining screws on the lock pitch solenoid valve, Woodward P/N 1310-506 or 1310-511. B) On overspeed propeller governors inspect for safety wire security the three coil retaining screws on the autofeathering solenoid valve, Woodward P/N 1310-110 or 1310-115. C) If screws inspected in accordance with Paragraphs A and B are not secured by safety wire, prior to return to service, replace said screws with socket head screws, Woodward P/N 1039-240, torque 18 to 22 lb. in., and secure by AMS 5685 0.024 to 0.026 in. dia. safety wire. Screws must be removed, replaced and torqued one at a time to avoid valve disassembly. NOTE: It may be necessary to remove two solenoid valve base retaining screws, Woodward P/N 33048-201 to gain access to the coil retaining screws. Removal and replacement of these two screws should be accomplished in the manner prescribed for the coil retaining screws. Woodward Service Bulletin 33532B, Supplement 1 and United Aircraft of Canada, Limited, Engine Service Bulletin No. 198 pertain to this subject. The inspections and modifications prescribed in this AD may be accomplished by a certified mechanic with a powerplant rating.NOTE: Governors to which this AD applies are known to be installed on the following airplanes, but this listing is not necessarily all inclusive: Primary propeller governors - Beech Models 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, B90, 99, 99A, 100; DeHavilland Models 1, 100, 200, 300; Helio Models HST-550, HST-550A; Swearingen Model SA26-5; Pilatus Model PC-6/B-H2, PC-6/B1-H2; McKinnon Models G21C, G21D, G21E, G21G; Grumman Model G21A (Serial Number B52 only); and Beech 18 series airplanes modified per STC SA 1016 WE. Overspeed propeller governors - Beech Model 65-A90-1, 68-A90-2, 65-A90-3, B90, 99, 99A and 100 airplanes. This amendment shall become effective August 4, 1970.
2015-02-18: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-201, -202, -203, -301, -302, and -303 airplanes. This AD requires a one-time ultrasonic inspection for fractures of all aft mount-pylon bolts of each engine. This AD was prompted by a report of one bolt on the aft engine mount upper beam found totally broken. We are issuing this AD to detect and correct fracture of the aft mount- pylon bolts, which could result in failure of the engine mount and consequent detachment of the engine.
2000-07-18: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F series airplanes, that requires a one-time detailed visual inspection of the generator power feeder wires to detect chafed or damage wires; repair, if necessary; and a modification of the generator power feeder wire installation. This amendment is prompted by reports of generator power feeder wire chafing on the closeout rib of the wing leading edge at a certain station due to insufficient clearance between the generator power feeder wires and the closeout rib. The actions specified by this AD are intended to prevent chafed and burnt generator power feeder wires, which could result in arcing damage to a certain closeout rib of the wing leading edge and fire damage to the wing structure, and consequent reduced structural integrity of the wing.
2000-07-17: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires a general visual inspection to verify that the circuit breaker panel fully opens, follow-on inspections, and corrective actions, if necessary. This amendment is prompted by an incident of an operator not being able to fully open the observer's upper main circuit breaker panel due to a certain cable being too short. The actions specified by this AD are intended to ensure that the upper main circuit breaker panel opens fully. If the panel does not open fully, maintenance activities may be hindered and cause damage to the circuit breaker panel and wiring, which could result in electrical arcing and consequent smoke and fire in the flight compartment.
2015-02-03: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-601, B4-603, B4-605R, F4-605R, and C4-605R Variant F airplanes. This AD was prompted by reports of cracking found in the pylon box, which was due to the stresses resulting from the pressure applied by the thrust reverser cowl bumpers. This AD requires repetitive high frequency eddy current (HFEC) inspections for cracking; and replacement of all fittings if necessary, which terminates the repetitive HFEC inspections for the modified side only. We are issuing this AD to detect and correct cracks of the pylon rib 5, which could result in reduced structural integrity of the airplane.
2015-02-05: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 717-200 airplanes; Model DC-10-10, DC-10-10F, DC- 10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40 and DC-10-40F airplanes; Model MD-10-10F and MD-10-30F airplanes; Model DC-9-81 (MD- 81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes; Model MD-88 airplanes; and Model MD-90-30 airplanes. This AD was prompted by reports of latent air data transducer degradation. This AD requires revising the maintenance or inspection program, as applicable, to incorporate special compliance items (SCIs). We are issuing this AD to prevent erroneous air data information, which could lead to a mid- air collision within reduced vertical separation minimum (RVSM) airspace.
2000-08-02: This amendment adopts a new airworthiness directive (AD) applicable to Agusta Model A109A, A109AII, and A109C helicopters. This action requires inspecting the main transmission to determine if certain Gleason crowns are installed and replacing any unairworthy Gleason crown with an airworthy Gleason crown. This amendment is prompted by the discovery of a cracked Gleason crown during an unscheduled transmission inspection prompted by abnormal noises coming from the transmission during main rotor deceleration. The actions specified in this AD are intended to prevent failure of the main transmission, loss of rotor drive, and subsequent loss of control of the helicopter.
2015-02-09: We are adopting a new airworthiness directive (AD) for Costruzioni Aeronautiche Tecnam srl Model P2006T 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 cracking found in the engine exhaust pipe. We are issuing this AD to require actions to address the unsafe condition on these products.
2000-07-20: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires electrical resistance measurements of the ground studs of the No. 2 generator in the electrical power center of the center accessory compartment for proper electrical bonding and of the ground studs and circuit breaker terminations in the forward cargo compartment to detect looseness and for proper electrical bonding; and corrective actions, if necessary. This amendment is prompted by an incident of charred insulation blankets in the forward cargo compartment in the area of the external ground power receptacle and the galley external power circuit breakers, and another incident of a No. 2 "generator off" alert while the generator was still on line. The actions specified by this AD are intended to prevent arcing and overheating of terminals and consequent smoke and fire in the forward cargo compartment due to improper bonding of groundstuds in the forward cargo compartment and in the electrical power center and due to improper installation of circuit breaker terminations.
93-19-08: 93-19-08 AEROSPATIALE: Amendment 39-8707. Docket 93-NM-13-AD. Supersedes AD 91-08-10, Amendment 39-6953. Applicability: Model ATR42-200 and -300 series airplanes on which Modification 03226 (as described in Aerospatiale Service Bulletin ATR42-32-0040, dated February 24, 1992, and Revision 1, dated January 18, 1993) has not been accomplished; certificated in any category. Compliance: Required as indicated, unless accomplished previously. NOTE 1: Paragraphs (a), (a)(1), and (a)(2) of this AD restate the initial and repetitive inspection requirements of AD 91-08-10, Amendment 39-6953, paragraphs A., A.1., and A.2. As allowed by the phrase, "unless accomplished previously," if the initial and repetitive inspections required by AD 91-08-10 have been accomplished previously, paragraphs (a), (a)(1), and (a)(2) of this AD do not require that those inspections be repeated. To prevent inadvertent retraction of the main landing gear (MLG), accomplish the following:(a) Perform an ultrasonic inspection of the MLG side brace lower arm in accordance with Aerospatiale Service Bulletin ATR42-32-0036, Revision 1, dated February 15, 1991, and Messier-Bugatti Service Bulletin 631-32-070, Revision 1, dated February 12, 1991, at the thresholds given in paragraphs (a)(1) and (a)(2) of this AD. Repeat the ultrasonic inspections thereafter at intervals not to exceed 1,000 landings until the inspection required by paragraph (b) of this AD is accomplished. (1) For airplanes that have accumulated 6,000 or more total landings on either the left or right MLG side brace lower arms as of May 6, 1991 (the effective date of AD 91- 08-10, Amendment 39-6953): Perform the initial inspection prior to the accumulation of 8,000 total landings on either the left or right MLG side brace lower arms, or within 14 days after May 6, 1991 (the effective date of AD 91-08-10, Amendment 39-6953), whichever occurs later. (2) For airplanes that have accumulated less than 6,000 total landings on either the left or right MLG side brace lower arms as of May 6, 1991 (the effective date of AD 91- 08-10, Amendment 39-6953): Perform the initial inspection prior to the accumulation of 6,000 total landings on either the left or right MLG side brace lower arms, or within 90 days after May 6, 1991 (the effective date of AD 91-08-10, Amendment 39-6953), whichever occurs later. (b) For those airplanes that previously have accomplished the ultrasonic inspections in accordance with paragraph (a) of this AD: Within 1,000 landings after the last inspection required by paragraph (a) of this AD, or within 90 days after the effective date of this AD, whichever occurs later, perform the ultrasonic inspection procedure in accordance with Aerospatiale Service Bulletin ATR42-32-0036, Revision 3, dated December 12, 1991. Repeat this inspection thereafter at intervals not to exceed 1,000 landings. Accomplishment of the requirements of this paragraph constitutes terminating action for the repetitive ultrasonic inspections in accordance with Revision 1 of that service bulletin required by paragraph (a) of this AD. (c) For those airplanes that have not previously accomplished the ultrasonic inspections in accordance with paragraph (a) of this AD: Prior to the accumulation of 6,000 total landings on either the left or right MLG side brace lower arms, or within 90 days after the effective date of this AD, whichever occurs later, perform an ultrasonic inspection of the MLG side brace lower arm in accordance with Aerospatiale Service Bulletin ATR42-32-0036, Revision 3, dated December 12, 1991. Repeat this inspection thereafter at intervals not to exceed 1,000 landings. (d) If any ultrasonic inspection result exceeds the acceptance criteria specified in Aerospatiale Service Bulletin ATR42-32-0036, Revision 1, dated February 15, 1991, or Revision 3, dated December 12, 1991, prior to further flight, replace the discrepant MLG side brace lowerarm with a new or serviceable part, in accordance with either service bulletin. Following replacement of discrepant parts, continue to repeat the ultrasonic inspection procedure in accordance with Aerospatiale Service Bulletin ATR42-32-0036, Revision 3, dated December 12, 1991, at intervals not to exceed 1,000 landings. (e) Prior to the accumulation of 15,000 total landings, or within 12 months after the effective date of this AD, whichever occurs later, install Modification 03226, in accordance with Aerospatiale Service Bulletin ATR42-32-0040, dated February 24, 1992, or Revision 1, dated January 18, 1993. Installation of Modification 03226 constitutes terminating action for the repetitive ultrasonic inspections of the MLG side brace lower arm required by this AD. (f) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (g) 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. (h) The actions shall be done in accordance with Aerospatiale Service Bulletin ATR42-32-0036, Revision 1, dated February 15, 1991; Aerospatiale Service Bulletin ATR42-32-0036, Revision 3, dated December 12, 1991; Aerospatiale Service Bulletin ATR42-32-0040, dated February 24, 1992; Aerospatiale Service Bulletin ATR42-32-0040, Revision 1, dated January 18, 1993; and Messier-Bugatti Service Bulletin 631-32-070, Revision 1, dated February 12, 1991. The incorporation by reference of Aerospatiale Service Bulletin ATR42-32-0036, Revision 1, dated February 15, 1991, and Messier-Bugatti Service Bulletin 631-32-070, Revision 1, dated February 12, 1991, was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51 as of May 6, 1991 (56 FR 14462, April 10, 1991). The incorporation by reference of the remainder of the service documents listed above is 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (i) This amendment becomes effective on December 22, 1993.
2000-06-12: This amendment adopts a new airworthiness directive (AD), applicable to Turbomeca Artouste III series turboshaft engines, that requires smoke emissions checks after every ground engine shutdown. If smoke is detected, this AD would require inspecting for fuel flow. If fuel flow is not detected, the engine may have injection wheel cracks, which would require removing the engine from service for repair. If fuel flow is detected, the engine may have a malfunctioning electric fuel cock, which would require removing the electric fuel cock from service and replacing it with a serviceable part. This action is prompted by reports of cracked injection wheels. The actions specified by this AD are intended to prevent injection wheel cracks, which could result in an in-flight engine shutdown.
85-22-06 R1: 85-22-06 R1 FAIRCHILD AIRCRAFT CORPORATION (formerly Swearingen Aviation Corporation): Amendment 39-5158 as revised by Amendment 39-6675. Docket No. 85-CE-11- AD. Applicability: Models SA226-T (Serial Numbers (S/N) T201 thru T275, T277 thru T291); SA226-AT (S/N AT001 thru AT419, AT003E, AT038E, AT062E, AT064E); SA226-TC (S/N TC201 thru TC419, TC208E, TC211E, TC211EE, TC211EEE, TC211EEEE, TC222E, TC227E, TC228E, TC229E, TC234E, TC237E, TC238E, TC239E, TC331E, TC334E;) SA226- T(B) (S/N T(B)276, T(B)292 thru T(B)417, T(B)303E); SA227-AC (S/N AC406, AC415, AC416, AC420 thru AC601, AC603); SA227-TT (S/N TT421 thru TT535, TT537 thru TT541); SA227-AT (S/N AT423 thru AT526, AT528, AT530 thru AT535, AT537 thru AT585) airplanes certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD unless previously accomplished in accordance with AD 85-22-06, Amendment 39-5158, and thereafter as indicated below, at thenext scheduled interval. To assure proper operation of the Stall Avoidance System (SAS), accomplish the following: (a) Except as noted in paragraph (b) of this AD, modify and/or inspect the applicable airplanes in accordance with the manufacturer's service bulletins, at the initial and repetitive time- in-service intervals, as specified for the model and serial numbered airplanes, set forth in Table 1 below: Table 1 When performing a functional check of the SAS Servo (Bendix only) allow the servo to run for a minimum of 5 minutes prior to accomplishing the functional check. If the temperature is below 0oC, allow the servo (Bendix only) to run for a minimum of 10 minutes prior to accomplishing the functional check. Model Serial Number Fairchild Service Bulletin Compliance Interval Hrs-Time in Service SA226-T T201 thru T275 226-A27-024 one time only T277 thru T291 226-A27-028 one time only 226-27-038 Para. 2.A 200 Para. 2.B 500 Para. 2.C. 500 Para. 2.D. 800 SA226-AT AT001 thru AT073, 226-A27-024 one time only AT003E, AT038E, AT062E, AT064E 226-27-038 Para. 2.A 200 Para. 2.B 500 Para. 2.C. 500 Para. 2.D. 800 AT074 thru AT419 226-27-038 Para. 2.A 200 Para. 2.B 500 Para. 2.C. 500 Para. 2.D. 800 SA226-TC TC201 thru TC314, 226-A27-024 one time only TC208E, TC211E, TC211EE, TC211EEE, 226-27-038 TC211EEEE, TC222E Para. 2.A 200 TC227E, TC228E Para. 2.B 500 TC229E, TC234E, Para. 2.C. 500 TC237E, TC238E Para. 2.D. 800 TC239E TC315 thru TC419 226-27-038 TC331E, TC334E Para. 2.A 200 Para. 2.B 500 Para. 2.C. 500 Para. 2.D. 800 SA226-T(B) T(B)276, 226-A27-028 one time only T(B)292 thru 226-A27-033 one time only T(B)391 226-27-037 Para. 2.A 200 Para. 2.B 500 Para. 2.C. 2000 T(B)392 thru 226-27-033 one time only T(B)417, 226-27-037 T(B)303E Para. 2.A 200 Para. 2.B 500 Para. 2.C. 2000 SA227-AC AC420 thru AC551 227-A27-004 one time only 227-27-006 Para. 2.A 200 Para. 2.B 500 Para. 2.C. 2000 AC406, AC415, 227-27-006 AC416, AC552 thru Para. 2.A 200 AC601, AC603 Para. 2.B 500 Para. 2.C. 2000 SA227-TT TT421, thru TT526, 227-A27-004 one time only TT528, TT530 thru 227-27-006 TT535 Para. 2.A 200 Para. 2.B 500 Para. 2.C. 2000 TT527, TT529, 227-27-004 one time only TT536 thru TT541 SA227-AT AT423 thru AT526 227-A27-004 one time only AT528, AT530 thru 227-27-006 AT535, AT537 thru Para. 2.A 200 AT549 Para. 2.B 500 Para. 2.C. 2000 AT550 thru AT585 227-27-006Para. 2.A 200 Para. 2.B 500 Para. 2.C. 2000 (b) Modify and/or inspect those Model SA226 and SA227 series airplanes which are equipped with the Conrac SAS system (per STC SA4725SW) in accordance with Table 2 as follows: Table 2 When performing a functional check of the SAS Servo (Bendix only) allow the servo to run for a minimum of 5 minutes prior to accomplishing the functional check. If the temperature is below 0oC, allow the servo (Bendix only) to run for a minimum of 10 minutes prior to accomplishing the functional check. Model Serial Number Fairchild Service Bulletin Compliance Interval Hrs-Time in Service 226-27-037 Para. 2.A 200 Para. 2.B 500 Any applicable Model SA226 and SA227 airplanes incorporating STC SA4725SW Para. 2.C 2000 NOTE 1: The current issue date and subject matter of the Service Bulletins specified in Table 1 are as follows: (1) 226-A27-024 - "Flight controls - Elevator," dated 11/13/79. (2) 226-A27-028 - "Flight controls - Rudder and Elevator," dated 12/11/80. (3) 226-A27-033 - "Flight controls - Elevator," dated 12/3/82, revised 1/6/83. (4) 227-A27-004 - "Flight controls - Elevators," dated 12/3/82, revised 1/6/83. (5) 226-27-037 - "Conrac SAS System - Inspection and Recalibration," dated 2/15/85, revised 4/15/88. (6) 226-27-038 - "Rosemount SAS System - Inspection and Recalibration," dated 2/15/85, revised 1/16/90. (7) 227-27-006 - "Conrac SAS System - Inspection and Recalibrations," dated 2/15/85, revised 4/15/88. (c) If the inspections specified in paragraphs (a) and (b) of this AD necessitate replacement of the servo pusher, assure that the replacement unit is either new, overhauled, or meets the limits of the electrical test specified in the above revised service bulletins. (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 initial or repetitive compliance times which provides an equivalent level of safety may be approved by the Manager, Airplane Certification Office, Fort Worth, Texas 76193-0150; Telephone (817) 624-5150. NOTE 2: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Airplane Certification Office, Fort Worth, Texas. All persons affected by this directive may obtain copies of the documents referred to herein upon request to the Fairchild Aircraft Corporation, P.O. Box 790490, San Antonio, Texas 78279- 0490; or may examine these documents at the FAA, Central Region, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. Airworthiness Directive 85-22-06 R1 revises AD 85-22-06, Amendment 39-5158. This amendment (39-6675, AD 85-22-06 R1) becomes effective on October 19, 1990.
2000-07-06: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires repetitive inspections to detect cracking of the lower corners of the door frame and cross beam of the forward cargo door, and corrective actions, if necessary. This AD also requires eventual modification of the outboard radius of the lower corners of the door frame and reinforcement of the cross beam of the forward cargo door, which would constitute terminating action for the repetitive inspections. This amendment is prompted by reports indicating that fatigue cracks have been detected in the lower corners of the door frame and cross beam of the forward cargo door. The actions specified by this AD are intended to prevent fatigue cracking of the lower corners of the door frame and cross beam of the forward cargo door, which could result in rapid depressurization of the airplane.
49-07-03: 49-07-03 CONVAIR: Applies to All BT-13 Series Aircraft. Compliance required not later than April 1, 1949. Several accidents have occurred in the above model aircraft from engine stoppage on take-offs and landings when operating on the right tank standpipe outlet with the fuel in the tank down to the level of the standpipe. Such engine stoppages have occurred because pilots not fully familiar with the fuel system have misinterpreted the right tank fuel gage as indicating total available fuel quantity with selector valve on Right Hand Main (standpipe) position, unaware that the change to Reserve or Left Hand Main position must be made before the fuel level in the right tank drops to 17 gallons. To preclude the possibility of pilot error with regard to the foregoing, the following placard shall be installed with each cockpit: "CAUTION: Unless Right Tank is full, use Reserve or Left Tank for Takeoff and Landing."
2000-07-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes, that requires repetitive structural inspections of certain aging airplanes, and repair, if necessary. This amendment also provides for optional terminating action for the repetitive inspections. This amendment is prompted by reports of incidents involving fatigue cracking and corrosion in transport category airplanes that are approaching or have exceeded their economic design service goal. The actions specified by this AD are intended to prevent degradation of the structural capabilities of the affected airplanes. This AD relates to the recommendations of the Airworthiness Assurance Task Force assigned to review Model 727 series airplanes, which indicate that, to assure long term continued operational safety, various structural inspections should be accomplished.