Results
97-01-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100 and -200 series airplanes, that requires replacing the aileron (lateral) control transfer mechanism with a new modified mechanism, or reworking the existing mechanism. This amendment is prompted by a review of the design of the flight control systems on Model 737 series airplanes. The actions specified by this AD are intended to prevent unexpected, significant control wheel forces and reduced travel of a control wheel due to mechanical interference within the lateral control system transfer mechanism during a jam override condition.
82-12-01: 82-12-01 BRITISH AEROSPACE (formerly Hawker Siddeley Aviation, Ltd.): Amendment 39-4391. HS/BH/DH-125 series airplanes certificated in all categories up to and including series 700 which have not been modified in accordance with Modification 252837. Compliance is required within 100 flight hours time in service after the effective date of this AD, unless already accomplished. To prevent blocking of the main landing gear restrictor valves, accomplish the following: 1. Disassemble the main landing gear restrictor valves and inspect for debris contamination, reassemble, and install in-line filters in accordance with British Aerospace Aircraft Group 125 Series Aircraft Service Bulletin 32-190 dated August 28, 1981. 2. 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 this AD. 3. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). This amendment becomes effective June 8, 1982.
2023-06-02: The FAA is adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model CL-600-1A11 (600), CL-600-2A12 (601), and CL- 600-2B16 (601-3A, 601-3R, and 604 Variants) airplanes. This AD was prompted by a determination that, due to a lack of flightcrew awareness, smoke hoods with a certain part number installed throughout the airplane could be mistaken for protective breathing equipment (PBE). This AD requires an inspection or records review to determine if any smoke hood with a certain part number is installed in any location on the airplane and, depending on the results, removing the smoke hood and associated placards and installing new placards. The FAA is issuing this AD to address the unsafe condition on these products.
81-06-02: 81-06-02 FROST ENGINEERING DEVELOPMENT CORPORATION: Amendment 39-4059. Applies to emergency descent devices installed on Boeing 747, Lockheed L-1011, and Airbus Industrie A-300 airplanes. \n\n\tCompliance required as indicated. To prevent failure of emergency descent devices accomplish the following: \n\n\tA.\tWithin 30 days from the effective date of this AD, unless already accomplished, inspect Frost Engineering descent devices for broken handle straps in accordance with paragraph 2, steps (1), (2), and (4) of Frost Engineering Development Corporation Service Bulletin 379103-25-002 dated September 29, 1980, or in a manner approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region. \n\n\tB.\tDescent devices found to have a broken handle strap must be modified in accordance with paragraph 2, steps (6) through (9) of Frost Engineering Development Corporation Service Bulletin 379103-25-002 dated September 29, 1980, or in a manner approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region. \n\n\tC.\tWithin 120 days from the effective date of this AD, unless already accomplished, modify the descent devices found to have a magnetic handle strap in accordance with paragraph 2, steps (5) through (9) of Frost Engineering Development Corporation Service Bulletin 379103-25-002 dated September 29, 1980, or in a manner approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region. \n\n\tD.\tWithin 120 days from the effective date of this AD, replace descent devices P/N 379103-1, serial numbers 1 through 0134, with other FAA approved descent devices. \n\n\tE.\tUpon the request of the operator, and subject to prior approval by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region, an FAA Aviation Safety Inspector may adjust the compliance times if the request contains substantiating data to justify the change. \n\n\tThe manufacturer's specification and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer, may obtain copies upon request to Frost Engineering Development Corporation, P.O. Box 1294, Englewood, Colorado 80150. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective March 19, 1981.
2004-25-17: The FAA adopts a new airworthiness directive (AD) for certain LETECKE ZAVODY Model L 23 SUPER--BLANIK sailplanes. This AD requires you to do a repetitive, non-destructive magnetic test (NDMT) inspection on the elevator rocker lever (part number A 730 201 N) for cracks. If cracks are found, this AD also requires you to return the part to the manufacturer. The manufacturer will send you a replacement part for installation. Installing the improved replacement part terminates the need for the repetitive inspections. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the Czech Republic. We are issuing this AD to prevent failure of the elevator rocker lever caused by cracks that resulted from a defect in prior manufacturing procedures. Such failure could lead to loss of control of the sailplane.
67-32-04: 67-32-04 PILATUS: Amdt. 39-525, Part 39, Federal Register December 12, 1967. Applies to Model PC-6 Series Airplanes. Compliance required as indicated. (a) To prevent the possibility of stabilizer trim control cable clamps jamming with the cable guide tubes at bulkhead No. 8, accomplish the following: (1) Within the next 50 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 50 hours' time in service from the last inspection, inspect guide tubes, P/N 6232.208, for signs of movement or wear in accordance with Pilatus Service Bulletin No. 72, dated June 1967, or later Swiss Federal Air Office-approved revision, or an FAA-approved equivalent. (2) If signs of movement or wear are detected during the inspection required by paragraph (a)(1), before further flight incorporate the modification required by paragraph (a)(3). (3) If no signs of movement or wear are detected during the inspections required by paragraph (a)(1), within the next 200 hours' time in service after the effective date of this AD, modify guide tubes, P/N 6232.208, and install an additional support, P/N 6232.468, in accordance with Pilatus Service Bulletin No. 72, dated June 1967, or later Swiss Federal Air Office-approved revision, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. (b) To prevent excessive rubbing of the rudder control cable with its fairlead at bulkhead No. 2, accomplish the following: (1) Within the next 100 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, inspect the rudder cable phenolic fairlead for signs of wear in accordance with Pilatus Service Bulletin No. 74, dated June 1967, or later Swiss Federal Air Office-approved revision, or an FAA-approved equivalent. (2) If signs of wear are detected during the inspection required by paragraph (b)(1), within the next 25 hours' time in service replace worn fairlead with a serviceable fairlead. (3) Within the next 600 hours' time in service after the effective date of this AD, replace the pulley and fairlead assembly with a double pulley assembly in accordance with Pilatus Service Bulletin No. 74, dated June 1967, or later Swiss Federal Air Office-approved revision, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. (c) To prevent excessive rubbing of the stabilizer trim control cable with its pulley at bulkhead No. 11, accomplish the following: (1) Within the next 100 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, inspect the cable and its pulley for signs of wear, in accordance with Pilatus Service Bulletin No. 74, dated June 1967, or later Swiss Federal Air Office-approved revision or an FAA-approved equivalent. (2) If signs of wear are detected during the inspection required by paragraph (c)(1), within the next 25 hours' time in service replace worn cable or pulley with a serviceable cable or pulley. (3) Within the next 600 hours' time in service after the effective date of this AD, modify the double pulley in accordance with Pilatus Service Bulletin No. 74, dated June 1967, or later Swiss Federal Air Office-approved revision, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. (d) The repetitive inspections required by paragraphs (a)(1), (b)(1), and (c)(1) may be discontinued following the incorporation of the applicable modification in accordance with paragraphs (a)(3), (b)(3), and (c)(3), respectively. This amendment effective December 17, 1967.
2011-23-07: We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace LP (type certificate previously held by Israel Aircraft Industries, Ltd.) Model Galaxy and Gulfstream G150 airplanes; and Gulfstream Aerospace LP Model Gulfstream 200 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: A broken aileron servo actuator centering spring rod was discovered on a model G100 aircraft during a routine scheduled maintenance inspection. * * * This latent failure of a centering spring rod, if not detected and corrected, in conjunction with the disconnection of the normal mechanical control system of the same servo actuator would lead to loss [of] control of the flight control surface [aileron or elevator]. This condition would reduce the control capability of the airplane and imposes a higher workload on the flight crew reducing their ability to cope with adverse operating conditions. We are issuing this AD to require actions to correct the unsafe condition on these products.
2023-06-12: The FAA is superseding Airworthiness Directive (AD) 2021-08- 08, which applied to all Airbus SAS Model A350-941 and -1041 airplanes. AD 2021-08-08 required replacing affected bleed duct assemblies and bleed gimbals at the wing-to-pylon interface, and prohibited the installation of affected parts. This AD was prompted by a report of a welding quality issue in the gimbal joint of the air bleed duct at each wing-to-pylon interface and the consequent deformation of the gimbal inner ring, and by new findings that affected bleed gimbals were found on certain airplanes that did not have any maintenance record of affected part replacement. This AD continues to require the actions in AD 2021-08-08 and, for certain airplanes, requires inspection of the bleed gimbals to determine the part number, and replacement if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
84-23-07: 84-23-07 SHORT BROTHERS LTD.: Amendment 39-4950. Applies to Model SD3-60 airplanes as listed in Short Brothers Service Bulletin SD360-71-05, dated March 1984, certificated in all categories. Compliance is required as indicated unless previously accomplished. To prevent icing of the oil cooler air intake scoop, accomplish the following: A. Within 60 days after the effective date of this airworthiness directive (AD), install the "D" type oil cooler air intake scoop on both intake cowls in accordance with Short Brothers Ltd. Service Bulletin SD360-71-05, dated March 1984. B. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. C. 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 and/or modifications required by this AD. This amendment becomes effective December 15, 1984.
96-26-01: This amendment adopts a new airworthiness directive (AD), applicable to General Electric Aircraft Engines (GE) CT7 series turboprop engines, that requires replacement of the gas generator turbine stage 2 forward cooling plates prior to the published cyclic life limits. The AD also defines the new, reduced cyclic life limits for the affected forward cooling plates. This amendment is prompted by reports of gas generator turbine stage 2 forward cooling plate failures. The actions specified by this AD are intended to prevent gas generator turbine stage 2 forward cooling plate failure, which could result in an uncontained engine failure.
2004-25-18: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney Canada (PWC) PT6A-60A and PT6A-65B turboprop engines. This AD requires replacing Woodward propeller governor assemblies, part number (P/N) 8210-212H. This AD results from six incidents during airplane acceptance flight testing where directional control of the airplane was difficult to maintain during landing. We are issuing this AD to prevent loss of directional control and damage to the airplane.
84-18-03 R1: 84-18-03 R1 GARLICK HELICOPTERS, HAWKINS AND POWERS AVIATION, INC., WILCO AVIATION, CALIFORNIA DEPARTMENT OF FORESTRY, PILOT PERSONNEL INTERNATIONAL, INC., AND INTERNATIONAL HELICOPTER, INC. (BELL HELICOPTER TEXTRON, INC.): Amendment 39-4899 as amended by Amendment 39-4997. Applies to Model UH-1 series helicopters certificated in the restricted category. Compliance is required within 10 hours time in service, unless already accomplished, after September 6, 1984, for Garlick Helicopters, Hawkins and Powers Aviation, Inc., and Wilco Aviation UH-1 series helicopters. Compliance is required within 10 hours time in service, unless already accomplished, after the effective date of this amendment for California Department of Forestry, Pilot Personnel International, Inc., and International Helicopter, Inc., UH-1 series helicopters. To detect any improperly repaired or cracked main rotor pitch change link clevis and to prevent possible failure of a clevis, accomplish the following one-time inspection of each clevis, P/N 204-011-136-1 (FSN 5340-00-839-3934). (a) Visually inspect the exposed surfaces of the clevis using a 5-power or higher magnifying glass. If any surface with pits has a golden or silver color within a pit, the clevis has been replated and must be removed before further flight. (b) Visually inspect the exposed threaded area of the clevis shank, above the jam nut, for crack indications. If a crack indication is found, the part must be removed and additionally inspected for cracks using magnetic particle or equivalent inspection method. (c) If a clevis has been replated or has a crack, the clevis must be removed before further flight. Install a serviceable clevis as prescribed in the appropriate military model maintenance or overhaul manual. (d) Compliance with UH-1 series aircraft military message dated July 13, 1984, from Commander AVSCOM satisfies this AD. Amendment 39-4899 became effective September 6, 1984.This Amendment 39-4997 becomes effective on February 22, 1985.
2023-04-10: The FAA is superseding Airworthiness Directive (AD) 2020-26- 07, which applied to all Dassault Aviation Model MYSTERE-FALCON 900 airplanes. AD 2020-26-07 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that a new airworthiness limitation is necessary. This AD continues to require the actions in AD 2020-26-07, and also requires revising the existing maintenance or inspection program, as applicable, to incorporate a new airworthiness limitation; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
86-23-02: 86-23-02 PILATUS BRITTEN-NORMAN LIMITED: Amendment 39-5452. Applies to Pilatus Britten-Norman Limited (PBN) Models BN-2 and BN-2A Islander airplanes certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished by incorporation of Modification NB/M/99O as noted in Britten-Norman Service Bulletin (S/B) No. BN.2/SB.113, Issue 2, dated April 14, 1986. To prevent undesirable oscillations, flutter or control system wear, accomplish the following: (a) Shake the elevator and aurally (by ear) determine if the mass balance weight is loose. Examine for any sign of movement, i.e., rust marks or grey lead deposits. In cases of uncertainty drill a small hole (5/32 in. dia) in the lower case and insert a probe to feel for lead movement. Alternatively dismantle the trimming weight assembly by removal of the blind riveted end covers and by removing the balance discs (note position and sequence for re- assembly). (1) If a loose balance weight is found prior to further flight, accomplish the following: (i) Remove the elevator; (ii) Drill out rivets, remove the trim weight assembly and detach the complete case from the tip rib. (iii) Lift out the profiled lead block. (iv) Clean the case internally to remove any corrosion by the use of emery cloth. Keep clean; do not wipe with oily or greasy rag or bond of adhesive will be impaired. (v) Clean the lead block to obtain a corrosion free face to the steel case and permit free fit into the case with an approximate 0.020 in. to 0.030 in. clearance. (vi) Prepare and apply a quantity of 3M's EC2216 epoxy adhesive to the case and press in the weight to obtain a layer of adhesive all around to fill the gap between the case and lead. Allow to cure approximately 12 hours at 60 degrees to 65 degrees Fahrenheit and re-assemble to the elevator structure. (vii) Re-assemble trim weights and check elevator balance, adjust trim weights if necessary to restore CAA-UK approved manufacturer's correct balance. NOTE: EC2216 may be substituted by similar "low flow" epoxy adhesive provided that the gap can be adequately sealed. (2) If no defect is found, reassemble and return the airplane to service. (b) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. All persons affected by this directive may obtain copies of the documents, referred to herein upon request to Pilatus Britten-Norman Limited, Bembridge, Isle of Wight, England; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on December 8, 1986.
97-01-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Textron Lycoming reciprocating engines. This action requires removal from service of defective piston pins, and replacement with serviceable parts. This amendment is prompted by a report of failure of a piston pin. The actions specified in this AD are intended to prevent piston pin failure, which could result in engine failure.
2004-23-01: The FAA adopts a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Model PC-7 airplanes with any Lear Romec RR53710B type or Lear Romec RR53710K fuel booster pump (Pilatus part number 968.84.11.401; 968.84.11.403; or 968.84.11.404) installed. This AD requires you to check the airplane logbook to determine whether any installed fuel booster pump has been modified with spiral wrap to protect the wire leads and has the suffix letter "B" added to the serial number of the fuel booster pump identification plate. If any installed fuel booster pump has not been modified, you are required to inspect any installed fuel booster pump wire lead for defects; if defects are found, replace the fuel booster pump with a modified fuel booster pump with spiral wrap that protects the wire leads; or if no defects are found, install spiral wrap to protect any wire leads and add the suffix letter "B" to the serial number of the fuel booster pump identification plate. The pilot is allowed to do the logbook check. If the pilot can positively determine that the fuel booster pump wire leads with spiral wrap are installed following the service information and that the suffix letter "B" is included in the serial number of the fuel booster pump identification plate, no further action is required. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to detect and correct any defects in the leads of any fuel booster pump, which could result in electrical arcing. This failure could lead to a fire or explosion in the fuel tank.
85-19-06: 85-19-06 BURKHART GROB: Amendment 39-5131. Applies to model G102 Astir CS Gliders (serial numbers 1001 through 1536 inclusive) certificated in any category. Compliance is required as indicated unless already accomplished. To Prevent failure of the air brake locking levers, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD cut inspection holes in the wing root ribs and inspect the air brake levers (P/Ns 102-4123 and 102- 4124) in accordance with Instruction 1 of Grob-Werke Technical Information TM 306-26, dated March 25, 1985. (b) If solid cast aluminum levers are found, accomplish paragraph (d). (c) If cast aluminum levers with a centerhole are found, accomplish the following: (1) Install inspection windows in the wing and replace page 3 and add page 26a to the flight manual in accordance with Instruction 2 of Grob-Werke Technical Information TM 306-26, dated March 25, 1985, no later than March 31, 1986. (2) Within the next 10 hours time in service after the effective date of this AD and thereafter at intervals not to exceed 10 hours, inspect the airbrake locking levers for cracks in accordance with Instruction 3 of Grob-Werke Technical Information TM 306-26, dated March 25, 1985, until accomplishment of Instruction 4 of Grob-Werke Technical Information TM 306-26, dated March 25, 1985. If cracks are found, replace airbrake locking lever with a serviceable part before further flight. (d) Replace the cast aluminum airbrake levers with the sheet aluminum airbrake levers in accordance with Instruction 4 of Grob-Werke Technical Information TM 306-26, dated March 25, 1985, no later than 3000 hours time in service. NOTE: Dimensions shown in TM 306-26 are in millimeters. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Aircraft Certification Office, AEU-100, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium 09667-1011, telephone 513.38.30. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Brussels Aircraft Certification Office may adjust the compliance time specified in this AD. Grob-Werke GmbH Technical Information TM 306-26 dated March 25, 1985, is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request to Burkhart Grob of America Incorporated, 1070 Navajo Drive, Bluffton Airport Complex, Bluffton, Ohio 45817. These documents also may be examined at the Office of the Regional Counsel, FAA, New England Region, Room 311, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment becomes effective on September 19, 1985.
2023-04-16: The FAA is superseding Airworthiness Directive (AD) 2020-21- 20, which applied to certain Dassault Aviation Model FALCON 900EX airplanes. AD 2020-21-20 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive maintenance requirements and/or airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2020-21-20 and requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive airworthiness limitations; as specified in European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2004-25-05: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747- 200C, 747-200F, 747-300, 747SP, and 747SR series airplanes. This AD requires repetitive inspections to detect cracks and fractures of the strut front spar chord assembly at each strut location, and repair if necessary. This AD is prompted by a report of a fractured front spar chord assembly for strut No. 3, which resulted in the loss of the strut upper link load path. We are issuing this AD to prevent loss of the strut upper link load path and consequent fracture of the diagonal brace, which could result in in-flight separation of the strut and engine from the airplane.
81-14-02: 81-14-02 MAULE AIRCRAFT CORPORATION: Amendment 39-4146. Applies to M-4 and to M-5 series airplanes certificated in all categories. M-4 Series. M-4, S/N 4 through 94, 1001 through 1045, 1S through 3S, 1T through 3T, 1C through 11C; M-4-210C, S/N 1001C through 1117C; M-4-220S, S/N 2001S; M-4-220C, S/N 2001C through 2190C; M-4-180C, S/N 3001C through 3006C. M-5 Series. M-5-220C, S/N 5001C through 5057C; M-5-210C, S/N 6001C through 6204C; M-5-235C, S/N 7001C through 7254C; M-5-180C, S/N 8001C and M-5-210TC, S/N 9001C. Compliance is required as indicated, unless already accomplished. To prevent failure of the rudder pedal V-bar and associated structure of the rudder bar, within 25 hours time in service after the effective date of this AD accomplish the following: (a) Visually inspect the rudder pedal V-bar tube for cracks with at least a 10-power magnifying glass. NOTE: Instructions for access to the rudder bar are outlined in Maule Aircraft Corporation Service Bulletin No. 2, dated 2/17/81. (b) If no cracks are found, modify the rudder bar assembly in accordance with the Maule Service Bulletin #2, dated 2/17/81. (c) If a crack is found, prior to further flight accomplish either 1 or 2 below, as appropriate: 1. If the crack is one inch or less in length, install modified rudder bar, P/N 4130F-12, in accordance with the instructions contained in Maule Service Bulletin #2, dated 2/17/81, or stop drill at the end of the crack, weld and reinforce in accordance with the instructions provided in the Maule Service Bulletin #2, dated 2/17/81, and Advisory Circular 43.13-1A, Chapter 2, Aircraft Metal Structure, Section 2, Welding. 2. If the crack exceeds one inch in length, install modified rudder bar, P/N 4130F-12, in accordance with the instructions contained in Maule Service Bulletin #2, dated 2/17/81. (d) Make appropriate maintenance record entry. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. This amendment becomes effective July 1, 1981.
2014-08-11: We are superseding Airworthiness Directive (AD) 2009-24-07 for certain the Boeing Company Model 737-600, -700, -700C, and -800 series airplanes. AD 2009-24-07 required repetitive lubrications of the right and left main landing gear (MLG) forward trunnion pins. AD 2009-24-07 also required an inspection for discrepancies of the transition radius of the MLG forward trunnion pins, and corrective actions if necessary. For certain airplanes, AD 2009-24-07 required repetitive detailed inspections for discrepancies (including finish damage, corrosion, pitting, and base metal scratches) of the transition radius of the left and right MLG trunnion pins, and corrective action if necessary. Replacing or overhauling the trunnion pins terminates the actions required by AD 2009-24-07. This new AD adds airplanes to the applicability of AD 2009-24-07. This AD was prompted by reports of corrosion protection damage to the forward trunnion pin on additional airplanes. We are issuing this AD to prevent stress corrosion cracking of the forward trunnion pins, which could result in fracture of the pins and consequent collapse of the MLG.
2023-04-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A310 series airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
81-17-03: 81-17-03 HILLER AIRCRAFT: Amendment 39-4187. Applies to Model UH-12 all series helicopters, certified in all categories, including Soloy Conversions STCs SH177WE and SH178WE, equipped with Main Transmission P/Ns 23500-3 and 23700-3, -5, -7 or -9. Compliance required as indicated, unless already accomplished. To prevent failure of the main transmission, accomplish the following: (a) Within 25 hours' additional time in service from the effective date of this AD, inspect the main transmission oil filter and chip detector according to paragraph 2 of Hiller Service Notice No. 23-2, dated 28 July 1981. (1) If magnetic chips or a quantity of gold colored flecks are present in the filter bowl, open transmission, inspect planetary system and replace worn parts per Hiller Overhaul Manual, before further flight. (2) If no chips are present on the magnetic chip detector, and only a trace of gold flecks is found in the filter bowl, clean filter and bowl, replace andmake detailed log book entry of the condition. If gold flecks are found after an additional 25 hours' time in service during an inspection per (a) above, replace with like serviceable part(s) per (a)(1), above, before further flight. (b) After completion of (a) (1) or (2) above, inspect, every 25 hours' time in service for turboshaft powered aircraft and 50 hours' time in service for reciprocating engine powered aircraft, according to (a) above. (c) Prior to 1200 hours' time in service or within the next 100 hours, after the effective date of this AD, remove P/N 23586-3 spacers from service and replace with serviceable parts. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate aircraft to a base for the accomplishment of inspections or modifications required by this AD. (e) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineeringand Manufacturing Branch, FAA Western Region. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made apart hereof pursuant to 5 U.S.C. 552(a(1). All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Hiller Aviation, 2075 W. Scranton Avenue, Porterville, California 93257. These documents may also be examined at FAA Western Region Office, 15000 Aviation Boulevard, Hawthorne, California 90261 and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA at its Headquarters in Washington, D.C. and at FAA Western Region Office. This amendment becomes effective August 24, 1981.
96-26-07: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 737 series airplanes. This action requires revising the FAA-approved Airplane Flight Manual (AFM) to include procedures that will enable the flight crew to take appropriate action to maintain control of the airplane during an uncommanded yaw or roll condition, and to correct a jammed or restricted flight control condition. This amendment is prompted by an FAA determination that such procedures currently are not defined adequately in the AFM for these airplanes. The actions specified in this AD are intended to ensure that the flight crew is advised of the potential hazard associated with a jammed or restricted flight control condition and of the procedures necessary to address it.
84-07-01: 84-07-01 SHORT BROTHERS LTD: Amendment 39-4835. Applies to SD3-60 airplanes as listed in Short Brothers Service Bulletin SD360-55-02, dated November 1983, certificated in all categories. Compliance is required as indicated unless previously accomplished. To prevent vibration in the event of an elevator tab drive system failure, accomplish the following: A. Within 60 days after the effective date of this AD, modify the elevator and elevator tab mass balance weights in accordance with Short Brothers Ltd. Service Bulletin SD360- 55-02 dated November 1983. B. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. C. 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 and/or modifications required by this AD. This amendment becomes effective April 9, 1984.