Results
74-25-09: 74-25-09 HAMILTON STANDARD: Amendment 39-2037. Applies to Hamilton Standard Model 54H60 propellers with the following serial numbers installed on, but not limited to, Lockheed Models L-382 and L-188 type aircraft: Propeller Model 54H60-81 214617, 215113, 215205, 215284, 215443, 215498, 215550, 215551, 216141, 216394, 217337, 223669, 223810 Propeller Model 54H60-91 233124, 233135, 233156 thru 233175, 233210 thru 233221, 233295 thru 233298, 233335 thru 233346 Propeller Model 54H60-117 213240, 215104, 215253, 215442, 217294, 217846, 219020, 219497, 220052, 221334, 221945, 222715, 223351, 223570, 223882, 223885, 224146, 224327, 224724, 224730, 225367, 225514, 225540, 225603, 225634, 225857, 226279, 226480, 227098, 227104, 227212, 227945, 228146, 228304, 228385, 229197, 230076, 230415, 230454, 231098, 231099, 231103, 231247, 231254, 231484, 231825, 231830, 233152 thru 233155, 233186 thru 233209, 233224 thru 233231, 233246 thru 233273, 233299 thru 233334, 234146To preclude failure of undersize oil transfer tubes and possible loss of propeller control remove P/N 536496, oil transfer tube, before further flight, unless already accomplished. Replace with a P/N 536496 oil transfer tube which has been inspected using a Hamilton Standard inspection tool, P/N HSD506611T501, or by FAA approved equivalent method, and which meets or exceeds minimum wall thickness requirements of Hamilton Standard Alert Service Bulletin HS Code 54H60-A68. The manufacturer's specifications identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(i). All persons affected by this directive who have not already received these documents may obtain copies upon request to the Hamilton Standard Division, United Aircraft Corporation, Windsor Locks, Connecticut 06096. These documents may also be examined at FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment becomes effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram.
95-19-16: 95-19-16 DASSAULT AVIATION: Amendment 39-9378. Docket 94-NM-200-AD. Applicability: Model Mystere-Falcon 900 series airplanes having serial numbers 53 through 139 inclusive, equipped with Fairchild Model F800 flight data recorders, installed in accordance with Supplemental Type Certificate (STC) SA7255SW-D; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (c) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent loss of electrical power to the airplane due to generator outage, accomplish the following: (a) At the next scheduled inspection, but no later than 60 days after the effective date of this AD, modify the electrical power installation for the flight data recorder, in accordance with paragraph 3.C.(1), Part 900-54-1, of Falcon Jet Corporation Service Bulletin 900-54 (F900 31-30), dated October 14, 1994, or Revision 1 (F900-31-1), dated November 17, 1994. Prior to further flight subsequent to the accomplishment of this modification, perform the checks and tests in accordance with paragraph 3.D.(1), Part 900-54-1, of either service bulletin.(b) Within 1 year after the effective date of this AD, replace the currently installed socket box for ground power with a reworked socket box, in accordance with paragraph 3.C.(2), Part 900-54-2, of Revision 1 of Falcon Jet Corporation Service Bulletin 900-54 (F900 31-1), dated November 17, 1994. Prior to further flight, subsequent to the accomplishment of this installation, perform the checks and tests, in accordance with paragraph 3.D.(2), Part 900-54-2, of Revision 1 of the service bulletin. (c) 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. (d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The actions shall be done in accordance with Falcon Jet Corporation Service Bulletin 900-54 (F900 31-30), dated October 14, 1994; or Falcon Jet Corporation Service Bulletin 900-54, Revision 1 (F900 31-1), dated November 17, 1994. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Falcon Jet Corporation, P.O. Box 967, Little Rock, Arkansas 72203-0967. 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. (f) This amendment becomes effective on November 2, 1995.
66-05-02: 66-05-02 HAWKER SIDDELEY: Amdt. 39-185, Part 39, Federal Register January 28, 1968. Applies to de Havilland Model 104 Dove Series Airplanes. Compliance required within 150 hours' time in service after the effective date of this AD. As a result of cracking of eye ends used in the rudder and elevator trim tab connecting rod assemblies, accomplish the following unless already accomplished. (a) Remove eye ends, P/N's CM.2A and CM.2B, and inspect for cracks visually or by use of other FAA-approved methods. (b) Replace cracked parts with uncracked parts of the same part number before further flight. (Hawker Siddeley Aviation, de Havilland Division T.N.S. Dove (104) Series CT (104) No. 187 or later ARB-approved issues cover this same subject). This directive effective February 27, 1966.
67-28-03: 67-28-03 de HAVILLAND: Amdt. 39-494, Part 39, Federal Register October 21, 1967. Applies to Type DHC-6 Aircraft. Compliance required as indicated. To preclude loss of the horizontal stabilizer, accomplish the following: (a) Within the next 15 hours' time in service after the effective date of this AD, unless already accomplished, check that each of the four horizontal tailplane to aft fuselage 5/16 inch diameter bolts, P/N's NAS 625-36 and NAS 625-53, are torqued to a value of 225 to 250 inch-pounds. If correct, no further action is necessary. If loose, comply with (b). (b) Re-torque loose bolts to a value of 225 to 250 inch-pounds and recheck every 7 hours' time in service to assure that this value is maintained. (c) The check required by (b) may be discontinued when a modification, approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region is incorporated. (d) Upon request with substantiating data submitted through an FAA maintenance inspector, the compliance times specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment effective October 21, 1967.
2001-17-21: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model 717 series airplanes, that requires repetitive inspections of the rod ends of the spoiler hold-down actuators for breakage along the intersection of the thread runout and the outer spherical surface of the lug; and replacement of any broken rod end of the spoiler hold-down actuators with a new rod end. This AD also requires replacement of the rod ends of the spoiler hold-down actuators with new rod ends, and reidentification of the spoiler hold-down actuators, which constitutes terminating action for the repetitive inspections. This action is necessary to prevent failure of the rod ends of the spoiler hold-down actuators due to fatigue, which could result in loss of the back-up protection of the spoiler float hold-down and unavailability of monitoring for an uncommanded spoiler movement. This action is intended to address the identified unsafe condition. \n\n\tThe incorporation by reference of Boeing Alert Service Bulletin 717-27A0010, dated August 15, 2000; Boeing Service Bulletin 717-27-0013, dated January 30, 2001; and Boeing Service Bulletin 717-27-0013, Revision 01, dated February 28, 2001; as listed in the regulations, is approved by the Director of the Federal Register as of October 1, 2001.
67-28-01: 67-28-01 AERO COMMANDER: Amdt. 39-492, Part 39, Federal Register October 10, 1967. Applies to Models 560E, 680, 680E, and 720 Airplanes. Compliance required within the next 25 hours' time in service after the effective date of this AD unless already accomplished. To detect cracks in the lower front spar cap between wing station 67 and 86 on each wing, accomplish either (a) or (b) of the following: (a) Perform visual and dye penetrant inspection in accordance with Aero Commander Service Bulletin Number 92 dated September 29, 1967. To facilitate inspection, a top wing access door may be installed in accordance with instructions contained in Aero Commander's letter to all owners and operators dated October 3, 1967. (b) Inspect in accordance with procedures approved by the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region, Fort Worth, Texas. If cracks are detected during above inspections, contact Aero Commander for approved repair or repairin accordance with a method approved by the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region, Fort Worth, Texas. Upon completion of the inspection, positive or negative findings including total time in service shall be forwarded to the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region, Fort Worth, Texas. This amendment effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by air mail letter dated October 5, 1967.
67-26-04: 67-26-04 WESTON GARWIN CARRUTH: Amdt. 39-479, Part 39, Federal Register September 16, 1967. Applies to Aircraft Equipped with Model 22-374 Series Altimeters, except those Altimeters which have been Modified and Marked with a White : "M-1" on the Back of the Instrument. The Unmodified Model 22-374 Series Altimeters are known to have been installed in Cessna Model 150G, 172H, 180H, 182J, 182K, 185E, 188, A188, P206A, P206B, TP206A, TP206B, TU206A, U206A, U206B, TU206B, 210F, 210G, T210F, T210G, 337B, T337B, Serial Nos. 310L-0018 through Serial No. 310L-0182, Serial Nos. 320E-0055 through Serial No. 320E-0276, Serial Nos. 320F-0001 through Serial No. 320F-0016, Serial Nos. 401-0014 through Serial No. 401-0022, Serial Nos. 402-0032 through Serial No. 402-0122, Serial Nos. 411-0240, 411-0241, 411-0243, 411-0246, Serial Nos. 411A-0255 through Serial No. 411A-0276 Aircraft, Reference Cessna Service Letter 67-52 dated September 23, 1967. Beech Model H-18 Serial Nos. BA743 through BA750,A23-A Serial Nos. M992 through M1064, A23-19 Serial Nos. MB154 through MB272 except MB266 and MB268, A23-24 Serial Nos. MB125 through MB272, V35 Serial Nos. D8250 through D8567 and D8571 except 35-C33 Serial Nos. CD1045 through CD1114, 35-C33A Serial Nos. CE80 through CE174, 56TC Serial Nos. TG1 through TG5, TG8 through TG10, A65 Serial Nos. LC257 through LC268, 65-B80 Serial Nos. LD332 through LD348, LD351 and LD352, 65-88 Serial Nos. LP43 through LP45, 65-A90 Serial Nos. LJ237 thru LJ304, 65-A90-1 Serial Nos. LM2 through LM37, LM39, LM41 and LM42, 95-C55 Serial Nos. TE186 through TE433, D95A Serial Nos. TD665 through TD687, and TD689 through TD704 Aircraft, Beech Model 95-B55, Serial Nos. TC-1005 through TC-1039 Aircraft, Mooney Model M20C, Serial Nos. 670001 through 670149, M20E, Serial Nos. 1177, 1199, 1217, 1268, 1273, 1277, 1281, 1283, 1286 through 1288, 1290, 1292, 1293, 1295 through 1308, 670001 through 670062, M20F, Serial Nos. 660001 through 660004, 670001 through 670486, Model M22, Serial Nos. 670001 through 670003 Aircraft. Aero Commander Model 500B, 500U, 680FL, 680FLP, 680T Aircraft, Bell Model 47G-2A, 47G-2A1, 47G-3B-1, 47G-4, 47G-4A, 47G-5, 206A Helicopters. The unmodified Model 22-374 Series Altimeter may have also been installed in other Aircraft as a replacement part since June 1, 1966. Compliance required as indicated. To prevent loss of reliable altitude information, accomplish the following: (a) Unless already accomplished, within 12 months after the effective date of this AD: (1) Modify altimeter by replacing balance arm assembly with an assembly identified by an M-1 stamped on the brass portion thereof available from Weston Instruments, Inc., Weston-Garwin Carruth Division in accordance with Weston Instrument, Inc., Weston-Garwin Carruth Division Service Bulletin 600-0002 or equivalent approved by the Chief, Engineering and Manufacturing Branch, Central Region, FAA or (2) Replace the altimeter with an altimeter known to be airworthy. (b) Until the altimeter is modified or replaced in accordance with paragraph (a) of this AD, for those aircraft equipped with only one operative unmodified Weston-Garwin Carruth Model 22-374 Series Altimeter, (1) on and after the effective date of this AD, flight is limited to those conditions in which flight is maintained with visual reference to the ground and when flight visibility is 3 miles or better, and (2) within 10 hours flight time after the effective date of this AD a placard must be installed on the instrument panel in plain view of the pilot which states "This aircraft is limited to operations in those conditions in which flight is maintained with visual reference to the found and when flight visibility is 3 miles or better." (c) On and after the effective date of this AD, for those aircraft equipped with unmodified Weston-Garwin Carruth Model 22-374 Series Altimeter(s) the pilot shall accomplish the following in order to determine if the altimeter(s) is operative: (1) Prior to the commencement of flight, check the altimeter reading(s) against the known field elevation at the appropriate altimeter setting(s). If a deviation of more than 100 feet is observed in the altimeter reading and the aircraft is equipped with only one altimeter, further flight is prohibited until the altimeter is replaced with an altimeter known to be airworthy. If such a deviation is observed in one altimeter on an aircraft equipped with two unmodified Weston-Garwin Carruth Model 22-374 Series Altimeters, flight may only be accomplished in accordance with paragraph (b) of this AD. (2) During flight, check the altimeter(s) for erroneous or erratic reading(s). If such reading(s) are observed and the aircraft is equipped with only one altimeter, flight may be continued in accordance with subdivision (1) of paragraph (b) of this AD to the next point of intended landing. Flight beyond that point may be conducted only in accordance with FAR 21.197 to a base where repairs can be accomplished. If such reading(s) are observed in only one altimeter on an aircraft equipped with two unmodified Weston-Garwin Carruth Model 22-374 Series Altimeters, and the other altimeter is operative, flight may only be accomplished in accordance with paragraph (b) in this AD. This amendment effective September 18, 1967. Revised October 27, 1967.
73-11-03: 73-11-03 INTERNATIONAL INFLATABLES COMPANY: Amdt. 39-1642. Applies to aircraft incorporating International Inflatables Company regulator, P/N 70003. NOTE: This regulator has been FAA-approved as a replacement for International Inflatables regulator P/N 68240, the subject of AD 71-14-03. Both regulators are used on various International Inflatables passenger evacuation slides, installed in but not limited to, BAC 1-11, B-707, B-727, DC-8, DC-9, and L-188 aircraft. Compliance required as indicated. To determine the presence of corrosion in regulator P/N 70003, accomplish the following: (a) Within the next 60 days after the effective date of this AD, unless already accomplished within the last 60 days, and thereafter at intervals not to exceed 120 days from the last inspection, visually inspect the International Inflatables Company regulator P/N 70003 for any evidence of corrosion both inside and outside of the regulator assembly, or an equivalent inspection approved by the Chief, Aircraft Engineering Division, FAA, Western Region. If there is any evidence of corrosion, replace the regulator prior to further flight with a previously inspected (per this AD) and corrosion-free regulator or an FAA-approved regulator. Do not return to service any regulator exhibiting evidence of corrosion. (b) After the effective date of this AD, and prior to the installation of an International Inflatables Company regulator P/N 70003 in any aircraft, inspect that regulator per (a), above. (c) Submit a written report of the inspection results of each corroded regulator to the Chief, Aircraft Engineering Division, FAA, Western Region, P.O. Box 92007, World Way Postal Center, Los Angeles, California, 90009. The report should include: serial number, date of manufacture, time in service, shelf time, date of last overhaul or inspection, and description of the corrosion. Inspection reports of regulators that are not corroded are not required. (Reportingapproved by the Bureau of the Budget under BOB No. 04-R-174) This amendment becomes effective June 22, 1973.
2005-13-14: The FAA is adopting a new airworthiness directive (AD) for all McDonnell Douglas Model MD-90-30 airplanes. This AD requires replacing existing dual anti-skid control manifolds (DACM) with new, improved or reworked and reidentified DACMs; inspecting the inlet filters and other components of the DACMs for damage; replacing any damaged DACM components with new or serviceable components; and flushing/cleaning the braking system prior to replacing the inlet filters. This AD is prompted by reports of multiple incidents of blown tires on landing while using maximum autobrake. We are issuing this AD to prevent metallic fibers from the first stage filter of the servo valves inside the DACM from becoming lodged in the first stage nozzle of the servo valve, which could lead to tire failure during high speed/high energy braking and possible subsequent runway departure.
67-23-05: 67-23-05 GRAVINER: Amdt. 39-454, Part 39, Federal Register August 1, 1967. Applies to Automatic Fire Extinguishers Installed on, but not Necessarily Limited to, the Airplanes Listed: P/N's 112A, 147A, and 1137A Installed on BAC 1-11 200 and 400 Series Airplanes; P/N 132A Installed on Short Bros. Skyvan SC-7, Series 2 Variant 200; and P/N 142A Installed on Hawker Siddeley DH-125 Series Airplanes. \n\n\tCompliance required as indicated. \n\n\tTo prevent failure of Graviner fire extinguisher containers, accomplish the following: \n\n\t(a)\tWithin the next 25 hours' time in service after the effective date of this AD, unless already accomplished within the last 500 hours' time in service for fire extinguisher containers with a stamp date October 1965 or before, or unless already accomplished within the last 1,500 hours' time in service for fire extinguisher containers with a stamp date later than October 1965, visually inspect Graviner automatic fire extinguisher containers for cracks orleaks and weight in accordance with Graviner Alert Service Bulletin No. 26-A30, Issue No. 2, dated April 21, 1967, or later ARB-approved issue, or FAA-approved equivalent. \n\n\t(b)\tRepeat the inspection specified in paragraph (a) at intervals not to exceed 500 hours' time in service from the last inspection for fire extinguisher containers with a stamp date October 1965 or before. For fire extinguisher containers with a stamp date later than October 1965, reinspect in accordance with paragraph (a) once between 1,400 and 1,500 hours' time in service after the initial inspection. \n\n\t(c)\tReplace all defective fire extinguisher containers with fire extinguisher containers of the same part number with a stamp date later than October 1965 before further flight. \n\n\tThis AD supersedes AD 67-17-04. \n\n\tThis amendment effective August 1, 1967. \n\n\tRevised August 12, 1967.
70-02-09: 70-02-09 NORTH AMERICAN: Amdt. 39-927. Applicable to operators of North American Sabreliner Models NA-265-40 and -60 with thrust reversers installed. With ten (10) hours time in service or not later than December 29, 1969, whichever occurs first, unless already accomplished since December 19, 1969, perform the "Engine-Thrust Reverser Rigging Inspection" described in North American Alert Wire dated December 19, 1969, or an equivalent inspection approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment is effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated December 24, 1969.
75-16-23: 75-16-23 PATTEN/PAN AVION: Amendment 39-2295. Applies to Pan Avion and Patten/Pan Avion models LSR-174 ( ) and LSR-174 (2) Evacuation Slides, Serial Numbers 473 through 524. Compliance required as indicated. To prevent loss of pressure in the evacuation slide inflation system, within 500 hours' time in service after the effective date of this AD, unless already accomplished, replace the Patten/Pan Avion inflation hoses, part numbers 1500-11A on model LSR-174 ( ) and 1600-19 on model LSR-174 (2), with inflation hoses, part numbers 1500-54 on model LSR-174( ) and 1600-23 on model LSR-174 (2) in accordance with Patten/Pan Avion Service Bulletin 27-75 dated February 20, 1975, or later FAA approved revision. This amendment becomes effective August 11, 1975.
2005-13-05: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-400F series airplanes. This AD requires initial detailed and open-hole high frequency eddy current inspections for cracking of the web, upper chord, and upper chord strap of the upper deck floor beams, and repair of any cracking. This AD also requires a preventive modification of the upper deck floor beams, and repetitive inspections for cracking after \naccomplishing the modification. This AD is prompted by reports of fatigue cracking found on the upper deck floor beam to frame attachment points. We are issuing this AD to prevent fatigue cracks in the upper chord, upper chord strap, and the web of the upper deck floor beams and resultant failure of the floor beams. Failure of a floor beam could result in damage to critical flight control cables and wire bundles that pass through the floor beam, and consequent loss of controllability of the airplane. Failure of the floor beam also could resultin the failure of the adjacent fuselage frames and skin, and consequent rapid decompression of the airplane.
67-23-07: 67-23-07 TOST: Amdt. No. 39-449, Part 39, Federal Register July 20, 1967. Applies to Tost Type Universal 53 Glider Tow Couplings with Serial Numbers 1 through 29999, Installed on Schempp-Hirth Models Standard Austria S, SH, and SH-1; Scheibe Flugzeugbau Models L-Spatz 55, Bergfalke II 55, and SF 26A; and Alexander Schleicher Models Ka 6 CR, Ka 6 E, K 7, and K 8 B gliders. Compliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished. To reduce the release load on the glider coupling when the tow cable imposes asymmetrical loads, replace, in accordance with Tost Modification No. 2/65, dated November 9, 1965, or FAA-approved equivalent, the bracket type automatic releases of the tow coupling with ring type automatic releases that conform to the Luftfahrt-Bundesamt approved type certificate 60.290/11 or later approved issue, or FAA-approved equivalent. This amendment effective August 19, 1967.
74-12-01: 74-12-01 ENSTROM: Amendment 39-1856 as amended by Amendment 39-1940. Applies to Models F-28 and F-28A helicopters: Compliance: Required as indicated, unless already accomplished. To prevent failure of the forged idler yoke (P/N 28-13223) (a) Before further flight and every 10 hours' time in service thereafter inspect by dye penetrant inspection method the webbed area of the forged idler yoke P/N 28-13223 for cracks. A forged idler yoke can be distinctively identified by the Part Number 28-13223 forged in 1/4 inch raised numbers on one side of the barrel portion and the alloy number MMT2014 forged in raised letters on the other side. (b) As part of each pilot preflight inspection (logbook entry not required), the owner/operator is required to visually inspect the webbed area of the forged idler yoke P/N 28- 13223 for cracks. (c) If cracks in the forged idler yoke P/N 28-13223 are detected when inspected in accordance with paragraph (a) or (b) above, replace it before further flight with a cast idler yoke P/N 28-13299, at which time the inspections required by this Airworthiness Directive are no longer applicable. (d) The forged idler yoke P/N 28-13223 can be replaced at any time with a cast idler yoke P/N 28-13299 at which time inspections required by this Airworthiness Directive are no longer applicable. (e) Equivalent methods of compliance with this Airworthiness Directive must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Great Lakes Region. Amendment 39-1856 was effective June 5, 1974, and was effective April 19, 1974, for all recipients of the air mail letter dated April 19, 1974, which contained this amendment. This Amendment 39-1940 becomes effective September 4, 1974.
2005-13-12: The FAA adopts a new airworthiness directive (AD) for certain Air Tractor, Inc. (Air Tractor) Models AT-300, AT-301, AT-302, AT-400, AT-400A, AT-401, AT-402, AT-602, AT-802, and AT-802A airplanes. This AD requires you to repetitively tighten the four eyebolts that attach the front and rear spar of the horizontal stabilizer to the respective stabilizer strut to the specified torque, and repetitively replace at specified intervals any eyebolts that attach the front and rear spar of the horizontal stabilizer to the respective stabilizer strut. An option for replacing the steel brace assembly inside the stabilizer with a new steel brace assembly with larger bushings and stronger eyebolts that increases the interval for replacement of eyebolts for AT-602, AT-802, and AT-802A airplanes is also included in this AD. This AD results from reports of failures of the subject eyebolt. We are issuing this AD to detect, correct, and prevent future fatigue failure in any eyebolt that attachesthe front and rear spar of the horizontal stabilizer to the respective stabilizer strut. Failure of the eyebolt could lead to an abrupt change or complete loss of pitch control and/or the airplane departing from controlled flight.
2016-08-11: We are superseding Airworthiness Directive (AD) 2012-17-13, which applied to certain The Boeing Company Model 707 airplanes, and Model 720 and 720B series airplanes. For certain airplanes, AD 2012-17- 13 required using redefined flight cycle counts; determining the type of material of the horizontal stabilizer, rear spar, and upper and lower chords on the inboard and outboard ends of the rear spar; repetitively inspecting for cracking of the horizontal stabilizer components; and repairing or replacing the chord, or modifying chord segments made of 7079 aluminum, if necessary. For all airplanes, AD 2012-17-13 required inspecting certain structurally significant items, and repairing discrepancies if necessary. This new AD adds a requirement to replace all chord segments made of 7079 aluminum with new, improved chord segments made of 7075 aluminum. This AD was prompted by a determination that all chord segments made of 7079 aluminum must be replaced with new, improved chord segments made of 7075 aluminum. We are issuing this AD to detect and correct stress corrosion and potential early fatigue cracking in the horizontal stabilizer, which could result in reduced structural integrity of the horizontal stabilizer.
73-11-07: 73-11-07 SIAI-MARCHETTI: Amdt. 39-1647. Applies to SIAI Marchetti, Model S.205 airplanes, Serial Nos. 001 through 003, 101 through 399, 4-101 through 4-165, 4-167 through 4- 215, 4-227, 4-232 through 4-252, 4-254, 4-267, 4-268, 4-270, 4-271, 4-273, 4-274, 4-282, 4-285, 5-302, 5-303, 5-406; and Model S.208 airplanes, Serial Nos. 001 through 003, 1-03 through 1-15, 2-16 through 2-22, 2-47 through 2-50, 369, 3-100, 4-51, 4-231, 4-233, and 4-256 through 4-258. Compliance is required as indicated unless already accomplished. To detect frayed or improperly aligned flap and aileron control cables at the passage of the cables from the fuselage to the wings, accomplish the following: (a) Within the next 100 hours' time in service after the effective date of this AD, inspect the flap and aileron control cables in the area of passage from the fuselage to the wings for fraying or contact with the metallic cup, P/N 205-1-156-11, in accordance with SIAI Marchetti Service Bulletin No. 205B31 dated January 14, 1972, or FAA-approved equivalent. (b) If frayed flap or aileron control cables or contact between the control cables and the metallic cup, P/N 205-1-156-11, are found during the inspection required by paragraph (a), before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed, replace any frayed cables and rework the metallic cup, P/N 205-1-156-11, in accordance with SIAI Marchetti Service Bulletin No. 205B31 dated January 14, 1972, or FAA-approved equivalent. This amendment becomes effective June 22, 1973.
2005-13-01: The FAA is superseding an existing airworthiness directive (AD) for Hoffmann Propeller GmbH & Co KG Models HO-V343 and HO-V343K propellers. That AD currently requires initial and repetitive visual inspections of propeller blades for blade shake and blade nut preload. That AD also requires initial and repetitive eddy current inspections of blade hubs for damage and cracks. This AD requires an ultrasonic inspection of the propeller hub and an eddy current inspection of the propeller hub if any cracks are discovered during ultrasonic inspection. Additionally, this AD requires sending a hub inspection report to the manufacturer. This AD also requires replacement of the propeller if any signs of blade shake, cracks, or other damage to the propeller hub outside serviceable limits are detected during the inspections. This AD results from the discovery of a propeller blade separation due to a possible hub failure. We are issuing this AD to prevent propeller hub failure and blade separation due to an unknown root cause, leading to damage and possible loss of control of the airplane.
67-14-07: 67-14-07 PIPER: Amdt. 39-375 Part 39 Federal Register April 20, 1967. Applies to Model PA-25-235 Airplanes, Serial Numbers 25-2000 to 25-4171 Inclusive. Compliance required as indicated. To prevent further failures of engine exhaust system components, accomplish the following: (a) Initial Inspection. Unless already accomplished, conduct the following inspections within the next 50 hours' time in service after the effective date of this AD on aircraft with 150 or more hours total time. On aircraft with less than 150 hours' total time, conduct the following inspection before an accumulation of 200 hours' total time unless already accomplished. (1) Inspect the entire exhaust system for signs of cracks, burn-throughs, weld separations, failed internal baffles, etc. Remove the muffler assembly by disconnecting air ducts, stacks, shrouds, etc., as necessary to permit a thorough visual inspection of exterior and interior surfaces with a probe light and mirror. The cabin air heat shroud must also be removed from the muffler. (2) In addition to the exhaust inspection, accomplish the following: (i) Inspect the lower ignition harness for deteriorated insulation. (ii) Inspect the lower engine mount in the area near the exhaust stack for blistered or burned paint and rust. (iii) Inspect the rubber engine mount bushings for deterioration and loss of resilience. (iv) Inspect all flexible air and heat ducting for deterioration and burning. Parts bound damaged or deteriorated as described above must be replaced or repaired before further flight. Extreme care must be exercised when re-installing the exhaust system components to prevent distortion of preloading any parts. (b) Recurrent Inspections. With 50 hours' time in service from the initial inspection and every 50 hours' time in service thereafter, repeat the initial exhaust system inspection described in (a)(1) except that the muffler neednot be removed from the aircraft provided visual inspection with probe light and mirror are made through the muffler tail pipe outlet and one end of the muffler at the stack connection. (c) Compliance Time Adjustments. (1) The inspection time intervals may be adjusted up to a maximum of 15 hours to coincide with aircraft annual or 100 hour scheduled inspections. (2) Inspections, repairs or alterations must be accomplished by authorized individuals or repair facilities. Aircraft log record entry must be made to reflect AD compliance in accordance with FAR 91.173. (d) The recurrent inspections of the exhaust systems as required in (b) may be discontinued upon installation of the new improved muffler and exhaust stack clamps included in muffler installation kit, Piper Part No. 753-753. (Piper Service Bulletin No. 241 covers this same subject.) This directive effective May 20, 1967.
2015-14-05: We are adopting a new airworthiness directive (AD) for all Pratt & Whitney (PW) JT8D-217C and JT8D-219 turbofan engines. This AD was prompted by reports of cracking in the low-pressure turbine (LPT) shaft. This AD requires removing affected LPT shafts from service using a drawdown plan. We are issuing this AD to prevent failure of the LPT shaft, which could lead to an uncontained engine failure and damage to the airplane.
97-14-03: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737-100, -200, -300, -400, and -500 series airplanes, that requires installation of a newly designed rudder-limiting device and yaw damper system. This amendment is prompted by a report indicating that a full rudder input, either commanded or uncommanded, could result in a rapid roll upset; and by reports of malfunctions of the yaw damper system. The actions specified by this AD are intended to prevent excessive rudder authority and consequent reduced controllability of the airplane; and malfunctions of the yaw damper system, which could result in sudden uncommanded yawing of the airplane and consequent injury to passengers and crewmembers.
2005-13-07: The FAA is adopting a new airworthiness directive (AD) for Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Co.) TFE731-2 and -3 series turbofan engines with certain part numbers (P/Ns) and serial numbers (SNs) of low pressure (LP) 1st and 2nd stage turbine rotor discs initially installed. This AD requires replacement of those LP 1st and 2nd stage turbine rotor discs. This AD results from a report of an uncontained failure of an LP 2nd stage turbine rotor disc that resulted in an in-flight engine shutdown. We are issuing this AD to prevent LP turbine rotor disk separation, which could result in an uncontained engine failure and damage to the airplane.
74-20-05: 74-20-05 BELL: Amendment 39-1965. Applies to Bell Model 212 helicopters, serial numbers 30501 through 30593, certificated in all categories. Compliance required within the next 100 hours' time in service after the effective date of the A.D., unless already accomplished. To prevent possible failure of the synchronized elevator ribs with resulting loss of the elevator, modify the right and left elevators as specified in Part III of Bell Helicopter Company Service Bulletin No. 212-01-74-2 dated March 27, 1974, or later FAA approved revision. 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). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Service Manager, Bell Helicopter Company, P.O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D. C. A historical file on this A.D. which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D. C., and at the Southwest Regional Office in Fort Worth, Texas. This amendment becomes effective October 21, 1974.
74-16-05: 74-16-05 SIKORSKY AIRCRAFT: Amendment 39-1910 is amended by Amendment 39-2033. Applies to S-64A, S-64E, and S-56 helicopters certificated in all categories. Compliance required as indicated. To prevent fatigue failures of the main rotor head spindle lock nut, accomplish the following: (a) Before the accumulation of 750 hours time in service on a main rotor head spindle lock nut, P/N S1510-23031-0, or within the next 25 hours time in service after the effective date of this AD, whichever occurs later, replace the affected lock nut with a serviceable part of the same part number and thereafter repeat replacement at intervals not to exceed 750 hours time in service. (b) Before the accumulation of 10,500 hours time in service on a main rotor head spindle lock nut, P/N S1510-23031-1, or within the next 25 hours time in service after the effective date of this AD, whichever occurs later, replace the affected lock nut with a serviceable part of the same part number and thereafter repeat replacement at intervals not to exceed 10,500 hours time in service. Amendment 39-1910 became effective August 15, 1974. This amendment 39-2033 becomes effective December 12, 1974.