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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.