Results
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.
81-18-08 R3: 81-18-08 R3 BEECH: Amendment 39-4196 as amended by Amendments 39-4233 and 39-4235 is further amended by Amendment 39-4273. Applies to Models 99, 99A, A99A and A99 (Serial Numbers U-1 through U-145 and U-147) and Model B99 (Serial Numbers U-146, U-148 and subsequent) airplanes certificated in all categories. COMPLIANCE: Required as indicated, unless previously accomplished. To preclude operations with inoperative systems which are required to be functioning for safe flight, within the next 100 hours time-in-service after the effective date of this AD, accomplish the following: A) Make the following revisions to the applicable approved Airplane Flight Manual (AFM) and operate the airplane in accordance with the revised manual. 1. In P/N 99-590012-1D, FAA Approved Airplane Flight Manual for Beechcraft 99 Airliner: a) Delete from page 4-1 the entry "Minimum Equipment List...4- 35" and the entry "Configuration Deviation List...4-44." b) Remove and destroy pages 4-35 through 4-46. 2. In P/N 99-590019-1C, FAA Approved Flight Manual for the Beechcraft 99A Airliner: a) Delete from page 4-1 the entry "Minimum Equipment List...4- 31" and the entry "Configuration Deviation List...4-40." b) Remove and destroy pages 4-31 through 4-42. 3. In P/N 99-590019-13, FAA Approved Flight Manual for the Beechcraft 99 or 99A Airliners which have been modified in accordance with either Beech Kit 99-5014-1 or 99-5014-3, as applicable: a) Delete from page 4-1 the entry "minimum Equipment List...4- 33" and the entry "Configuration Deviation List...4-44." b) Remove and destroy pages 4-33 through 4-44. 4. In P/N 99-590023-1, FAA Approved Flight Manual for the Beechcraft A99A Airliner: a) Delete from page 4-1 the entry "Minimum Equipment List...4- 33" and the entry "Configuration Deviation List...4-42." b) Remove and destroy pages 4-33 through 4-44. 5. In P/N 99-590024-1, FAA Approved Flight Manual for the Beechcraft A99 Airliner: a) Delete from page 4-1 the entry "Minimum Equipment List...4- 29" and the entry "Configuration Deviation List...4-38." b) Remove and destroy pages 4-29 through 4-40. 6. In P/N 99-590026-1, FAA Approved B99 Airliner Airplane Flight Manual: a) Delete from page 4-1 the entry "Minimum Equipment List...4- 33" and the entry "Configuration Deviation List...4-42." b) Remove and destroy pages 4-33 through 4-44. B) In the applicable FAA Approved Airplane Flight Manual identified in paragraph A of this AD: 1. In Section 1, Limitations, delete in its entirety, the paragraph which reads as follows: "This airplane is approved for the following types of operation when required equipment is installed and operational as defined herein. 1. VFR day and night. 2. IFR day and night. 3. Known icing conditions. 4. FAR 135 operations when all pertinent limitations and performance considerations are complied with. 5. FAR 91 operations when all pertinent limitations and considerations are complied with." 2. In Section 1, Limitations, insert the Kinds of Operations Equipment List (KOEL), a copy of which is attached hereto and identified as Appendix I, Revision 1, dated September 25, 1981, for temporary insertion until an identical permanent list is provided by the manufacturer, and operate the airplane in accordance with that Equipment List. C) This AD may be accomplished by the holder of at least a private pilot certificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operated by that person provided the airplane is not used in air carrier service. An entry must be made in the Aircraft Maintenance Records indicating compliance with this AD. Amendment 39-4196 became effective December 2, 1981. Amendment 39-4233 became effective upon receipt. This Amendment 39-4273 becomes effective upon receipt and extendsthe effective date of Amendment 39-4235 to February 16, 1982. 81-18-08 APPENDIX I KINDS OF OPERATIONS EQUIPMENT LIST (KOEL) This airplane may be operated in day or night VFR, day or night IFR and icing conditions when the appropriate equipment is installed and operable. The following equipment list identifies the systems and equipment upon which type certification for each kind of operation was predicated and must be installed and operable for the particular kind of operation indicated. However, certain operations may be authorized with certain listed equipment and/or systems inoperative under certain conditions and under provisions defined by a current Minimum Equipment List (MEL) approved by the FAA which is dated concurrently with or after this AFM revision and authorized under an operating regulation which provides for use of an MEL. VFR Day VFR Night IFR Day IFR Night Icing Electrical Power 1. Battery 1 11 1 1 2. D.C. Generator 2 2 2 2 2 3. D.C. Loadmeter 2 2 2 2 2 4. D.C. Generator Warning Light 2 2 2 2 2 5. Invertor 2 2 2 2 2 6. Invertor Warning Light 1 1 1 1 1 7. Feeder Limiter Warning Light 1 1 1 1 1 8. Battery Monitor System 1 1 1 1 1 9. AC Volt Meter (If installed) 1 1 1 1 1 Equipment/Furnishings 1. Exit Signs - Self-Illuminated 4 4 4 4 4 Fire Protection 1. Engine Fire Detector System 2 2 2 2 2 2. Firewall Fuel Shutoff System 2 2 2 2 2 Icing Flight Controls 1. Flap System 1 1 1 1 1 2. Flap Position Indicator 1 1 1 1 1 3. Horizontal Stabilizer Trim System - Main 1 1 1 1 1 4. Horizontal Stabilizer Trim System - Standby 1 1 1 1 1 5. Stabilizer out-of-trim Aural Warning Indicator 1 1 1 1 1 6. Trim-in-Motion Aural Indicator 1 1 1 1 1 7. Horizontal Stabilizer Position Indicator 1 1 1 1 1 8. Stall Warning Horn 1 1 1 1 1 9. Trim Tab Indicator - Rudder 1 1 1 1 1 10. Trim Tab Indicator Aileron 1 1 1 1 1 Fuel 1. Fuel Boost Pumps (4 are installed) PER AFM Limitations 2. Fuel Quantity Indicator 2 2 2 2 2 3. Fuel Quantity Gauge Selector Switch 1 1 1 1 1 4. Nacelle Not-Full Warning Light 2 2 2 2 2 5. Crossfeed Light 1 1 1 1 1 6. Fuel Boost Pump Low Pressure Warning Light 2 2 2 2 2 7. Fuel Flow Indicator 2 2 2 2 2 8. Jet Transfer Pump 2 2 2 2 2 Ice And Rain Protection 1. Engine Inlet Scoop Deicer Boot 2 2 2 2 2 2. Indicator - Propeller/Inlet Deicer 1 1 1 1 1 3. Engine Inertial Anti-Icing System 2 2 2 2 2 4. Pitot Heat 0 0 2 2 2 5. Alternate Static Air Source 0 0 1 1 1 6. Engine Auto-Ignition System (If Installed) 2 2 2 2 2 7. Propeller Deicer System 0 0 0 0 1 8. Windshield Heat (Left) 0 0 0 0 1 9. Surface Deicer System 0 0 0 0 1 10. Stall Warning Mounting Plate Heater 0 0 0 0 1 11. Wing Ice Light (Left) 0 0 0 0 1 12. Windshield Wiper (Left) 1 1 1 1 1 Landing Gear 1. Landing Gear Position Indicator Lights 3 3 3 3 3 2. Landing Gear Handle Light 1 1 1 1 1 3. Flap-Controlled Landing Gear Aural Warning 1 1 1 1 1 4. Nose Steering Disconnect Actuator 1 1 1 1 1 5. Landing Gear Hydraulic Pump (If Installed) 1 1 1 1 1 Lights 1. Cockpit and Instrument (Required Illumination) 0 1 0 1 0 2. Anti-Collision 0 2 0 2 0 3. Landing Light Bulbs (any 2 of 4 bulbs) 0 2 0 2 0 4. Position Lights 0 3 0 3 0 5. Cabin Door Warning Light (Note) 1 1 1 1 1 6. Baggage Door Warning Light (Note) 1 1 1 1 1 Note: Where combined into one cabin/baggage annunciator - one (1) is required for all conditions. Navigation (Instrument) 1. Altimeter (left) 1 1 1 1 1 2. Airspeed (left) 1 1 1 1 1 3. Magnetic Compass 1 1 1 1 1 4. Outside Air Temperature 1 1 1 1 1 Vacuum System 1. Suction or Pressure Gauge 1 1 1 1 1 2. Instrument Air System 1 1 1 1 1 Propeller 1. Autofeather System 2 2 2 2 2 2. Low Pitch light (PT6A-20 Engine Only) 2 2 2 2 2 3. Do not Reverse Warning Light 1 1 1 1 1 4. Propeller Reversing 2 2 2 2 2 Engine Indicating 1. Tachometer Indicator (Propeller) 2 2 2 2 2 2. Tachometer Indicator (Gas Generator) 2 2 2 2 2 3. ITT Indicator 2 2 2 2 2 4. Torque Indicator 2 2 2 2 2 Engine Oil 1. Oil Temperature Indicator 2 2 2 2 2 2. Oil Pressure Indicator 2 2 2 2 2 3. Low Oil Pressure Light 2 2 2 2 2 4. Engine Chip Detector System 2 2 2 2 2 Note 1: The zeros (0) used in the above list mean that the equipment and/or system was not required for type certification for that kind of operation. Note 2: The above system and equipment list is predicted on a crew of one pilot. Note 3: Equipment and/or systems in addition to those listed above may be required by operating regulations (FAR Part 135) that may specify certain items of equipment for more than one pilot. Note 4: The above system and equipment list does not include specific flight instruments and communications/navigation equipment required by the FAR Part 91 and 135 operating requirements.
2015-01-02: We are adopting a new airworthiness directive (AD) for certain Mitsubishi Heavy Industries, Ltd. Models MU-2B-30, MU-2B-35, MU-2B-36, MU-2B-36A, and MU-2B-60 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 stress corrosion cracking in the flanges of the airframe at stations 4610 and 5605. We are issuing this AD to require actions to address the unsafe condition on these products.
2000-07-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777 series airplanes, that requires replacement of the clevis ends on the tie rods for the center stowage bin supports with improved clevis ends. This amendment is prompted by a report that, under ultimate load conditions, the aluminum clevis ends on the tie rods for the center stowage bin supports can break. The actions specified by this AD are intended to prevent broken tie rods, which could result in the center stowage bins dropping onto the passenger seats below, causing possible injury to the occupants.
2000-07-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200 and -200PF series airplanes, that requires repetitive detailed visual inspections to detect loose fuse pins in the outboard beam attachment and forward trunnion support on the main landing gear (MLG) and to detect corrosion on the structure adjacent to the fuse pin; and corrective actions, if necessary. This amendment also requires eventual replacement of the fuse pins with new corrosion resistant steel (CRES) fuse pins, which constitutes terminating action for the repetitive inspections. This amendment is prompted by a report of damaged fuse pins caused by corrosion. The actions specified by this AD are intended to prevent corroded fuse pins, which could result in the MLG separating from the wing, and consequent damage to the airplane and possible rupture of the wing fuel tank.
2000-07-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes, that requires modification of wing center box angle fittings at frame 47. 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 reduced structural integrity of the wing center box angle fittings at frame 47 due to fatigue cracking.