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64-09-01: 64-09-01\tBOEING: Amdt. 715 Part 507 Federal Register April 18, 1964. Applies to All Models 707 and 720 Series Aircraft, Serial Numbers 17586 through 17612, 17614 through 17652, 17658 through 17690, 17692 through 17724, 17903 through 17905, 17907 through 17930, 18012 through 18037, 18041 through 18050, 18054 through 18087, 18154 through 18167, 18240 through 18246, 18248 through 18251, 18334 through 18339, 18351 through 18357, 18372 through 18397, 18400 through 18404, 18406 through 18408, 18411 and 18412, 18414 through 18425, 18451 through 18457, 18460 and 18461. \n\n\tCompliance required within 1,000 hours' time in service after the effective date of this AD, unless already accomplished. \n\n\tTo prevent slippage of the crank arms on the shafts of the respective stabilizer and spoiler position transmitters, and to prevent rotation of the position transmitter in its brackets, rework the crank arms or replace with modified crank arms, and add a washer under the nut of each clamping boltin accordance with the Modification Data (PRR 15506) of Boeing Service Bulletin No. 1836 or FAA approved equivalent. \n\n\t(Boeing Service Bulletin No. 1836 covers this same subject.) \n\n\tThis directive effective May 19, 1964.
2020-18-05: The FAA is adopting a new airworthiness directive (AD) for all Pratt & Whitney Canada Corp. (P&WC) PT6B-37A model turboshaft engines with engine serial number PCE-PU0289 and earlier. This AD was prompted by a report of contamination from galvanic corrosion between the fuel control unit (FCU) aluminum body and the steel union fitting causing the loss of engine control, resulting in an engine over-speed condition and subsequent in-flight shutdown (IFSD). This AD requires replacing the FCU with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
79-08-06: 79-08-06 MARVEL-SCHEBLER/TILLOTSON: Amendment 39-3450. Applies to HAJ-6 Part Number 10-5243 carburetors with the following serial numbers installed on aircraft certificated in all categories: DF-1-100 118 133 151 174 191 216 250 276 300 101 119 134 154 175 193 218 251 277 301 102 120 135 176 157 194 219 255 278 302 103 121 136 159 177 195 220 256 279 303 104 122 137 161 179 200 222 258 282 304 106 123 138 162 180 202 223 260 287 307 107 124 139 163 182 204 225 261 290 312 110 125 143 164 183 205 227 263 292 313 111 127 144 167 184 208 229 264 293 318 112 128 145 168 185 209 231 266 295 113 129 147 170 186 210 237 269 296 114 130 148 171 187 211 238 271 297 116 131 149 172 189 212 240 274 298 117 132 150 173 190 241 245 275 299 These carburetors are installed on, but are not limited to Cessna TR182 aircraft with Lycoming O-540-L3C5D engines. Compliance required within 30 days after the effective date of this AD, unless previously accomplished. To preclude failure of the engine during idle conditions, remove the carburetor from service and replace with an airworthy carburetor of the same part number with serial number DF-1-500 or subsequent. The aircraft may be flown in accordance with FAR 21.197 to a base where the modification can be performed. This amendment becomes effective April 25, 1979.
65-05-04: 65-05-04 FAIRCHILD: Amdt. 39-40 Part 39 Federal Register February 25, 1965. Applies to Model F-27 Series Aircraft Serial Numbers 1 through 107. Compliance required as indicated. To prevent damage to the rudder and rudder trim tab from rudder vibration, accomplish the following: (a) Within 25 hours' time in service after the effective date of this AD, unless already accomplished within the last 75 hours' time in service, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, inspect the rudder trim tab for cracks in accordance with Fairchild Service Bulletin No. F27-55-8A, Revision 1, dated February 3, 1965 or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) If a crack is found, modify the rudder trim tab in accordance with Fairchild Service Bulletin No. F27-55-8A, Revision 1, dated February 3, 1965, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, before further flight, except that one flight may be made in accordance with the provisions of FAR 21.197 to a base where the repair can be made. During this flight, a maximum operating limit speed (Vmo) of 160 knots CAS or MACH number 0.35 shall be observed. (c) Inspect in accordance with Fairchild Service Bulletin No. F27-55-8A, Revision 1, dated February 3, 1965, aircraft modified in accordance with (b) prior to the accumulation of 600 hours' time in service after modification, and thereafter at intervals not to exceed 150 hours' time in service from the last inspection. (d) Within the next 100 hours' time in service after the effective date of this amendment unless already accomplished, modify the rudder trim tab in accordance with Fairchild Alert Bulletin No. 27-39A, dated March 12, 1965, or later FAA-approved revision, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (e) The repetitive inspections required by (a) and (c) may be discontinued when the modification required by (d) is incorporated. (f) Upon request of the operator, an FAA maintenance inspectors, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. (Fairchild Service Bulletin No. F27-55-8A, Revision 1, dated February 3, 1965, covers this subject.) This directive effective February 25, 1965. Revised May 13, 1965.
2020-17-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319-115 and -153N; A320-214, -216, -232, - 251N, -252N, -271N, and -273N; and A321-211, -231, -251N, -253N, -271N, -272N, -251NX, -252NX, -253NX, and -271NX airplanes. This AD was prompted by reports of fuel leaks at the interface of the low pressure shut off valves on the pylon areas of engines 1 and 2 due to improperly installed parts during production. This AD requires a one-time detailed inspection of each low pressure shut off valve on the pylon areas of engines 1 and 2 for correct installation, and replacing the O-rings and torqueing the mounting bolts within specified values as applicable, as specified in a European Union Aviation Safety Agency (EASA) AD 2020- 0148, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
80-26-01: 80-26-01 ROCKWELL INTERNATIONAL: Amendment 39-3988. Applies to Model NA265-40 Series, Serial numbers 282-1 through 282-137, and -60 Series, Serial Numbers 306-1 through 306-64, 306-68, 306-71 through 306-103 airplanes certificated in all categories, not modified in accordance with Life Extension Modification per North American Rockwell Drawing 306-053010 or Service Kit SK 13808-40. Compliance required as indicated, unless already accomplished. To prevent inadvertent cabin depressurization accomplish the following: (a) On aircraft with 2,000 or more hours' total time in service, within the next 600 hours' additional time in service or within the next 12 months from the effective date of this AD, whichever occurs first. (1) Gain access and conduct a close visual inspection of the fuselage structure below the cabin entrance door and adjacent areas in accordance with "Modification Instructions 1 through 3" of Sabreliner Service Bulletin No. 56 dated September 22, 1980. Access is gained by modification in accordance with Service Kit SK 13808-10. (2) If no cracks are detected, repeat the inspections required in paragraph (a)(1) of this AD at intervals not to exceed 600 hours' time in service since the last such inspection. (3) If cracks are detected which are less than one inch long in the outboard bays only, repair per Sabreliner Service Bulletin Repeat the inspections required by paragraph (a)(1) of this AD at intervals not to exceed 600 hours' time in service since the last such inspection. (4) If cracks are detected which are less than one inch long in the inboard bays or inboard and outboard bays, repair per Sabreliner Service Bulletin No. 56, dated September 22, 1980, and accomplish Service Kit SK 13808-30. Repeat the inspections required by paragraph (a)(1) of this AD at intervals not to exceed 600 hours' time in service since the last such inspection. (5) If cracks are detected which are one inch or longer, repairin a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region, or by the installation of Service Kit SK 13808-40. The installation of Service Kit SK 13808-40 terminates the inspections required by this AD. For other repairs, unless specifically authorized by the Chief, Engineering and Manufacturing Branch, FAA Western Region, repeat the inspections required by paragraph (a)(1) of this AD at intervals not to exceed 600 hours' time in service since the last such inspection. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD. (c) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. This amendment becomes effective January 19, 1981.
80-23-01: 80-23-01 ROLLS-ROYCE, LTD.: Amendment 39-3966. Applies to Rolls-Royce, Ltd., DART 506, 510, 511, 514, 515, 520, 525, 526, 527, 528, 529, 530, 531, 532, 533, 534, 535, 536, 542, 543, 550, and all variants turboprop engines. Compliance required as indicated, unless already accomplished. To preclude possible frettage fatigue failure of low pressure impellers, inspect for cracks and modify or remove from service all low pressure impellers installed in the following DART model engines: 1. DART 506, 510, 511, 514, 515, and their variants; and DART 520, 525, 526, 527, 528, 529, 530, 531, 532, 533, 534, 535, 536, 550, and all variants of these marks equipped with a low pressure impeller which has run previously in a DART 506, 510, 511, 514, 515, or any variant of these engines. a. After November 30, 1980, no low pressure impeller may exceed 5,000 flight cycles since new without inspection for cracks and incorporation of Modification 1732, in accordance with Rolls-Royce DART Alert Service Bulletin No. Da72-A445, Revision 4, dated October 27, 1980. Remove from service low pressure impellers having crack indications. b. After November 30, 1980, prior to further flight, all low pressure impellers for which the flight cycles since new cannot be positively established, must be inspected and modified to incorporate Modification 1732; in accordance with Rolls-Royce DART Alert Service Bulletin No. Da72-A445, Revision 4, dated October 27, 1980. Remove from service, low pressure impellers having crack indications. c. Remove from service not later than May 31, 1981, all low pressure impellers which have not been inspected for cracks and do not have modification 1732 incorporated. 2. DART 520, 525, 526, 527, 528, 529, 530, 531, 532, 533, 534, 535, 536, 550, and their variants equipped with a low pressure impeller which has not run previously in a DART 506, 510, 511, 514, 515 or any variant of these engines. a. After December 31, 1982, no low pressure impeller may exceed 9,000 flight cycles since new without inspection for cracks and incorporation of Modification 1732, in accordance with Rolls-Royce DART Alert Service Bulletin No. Da72-A445, Revision 4, dated October 27, 1980. Remove from service low pressure impellers having crack indications. b. After December 31, 1982, prior to further flight, all low pressure impellers for which the flight cycles since new cannot be positively established, must be inspected and modified to incorporate Modification 1732, in accordance with Rolls-Royce DART Alert Service Bulletin No. Da72-A445, Revision 4, dated October 27, 1980. Remove from service low pressure impellers having crack indications. c. Remove from service not later than December 31, 1984, all low pressure impellers which have not been inspected for cracks and do not have Modification 1732 incorporated. 3. DART 542 and 543 model engines and their variants. a. After December 31, 1981, no low pressure impeller may exceed 9,000 flight cycles since new without inspection for cracks and incorporation of Modification 1732, in accordance with Rolls-Royce DART Alert Service Bulletin No. Da72-A445, Revision 4, dated October 27, 1980. Remove from service low pressure impellers having crack indications. b. After December 31, 1981, prior to further flight, all low pressure impellers for which the flight cycles since new cannot be positively established, must be inspected and modified to incorporate Modification 1732, in accordance with Rolls-Royce DART Alert Service Bulletin No. Da72-A445, Revision 4, dated October 27, 1980. Remove from service low pressure impellers having crack indications. c. Remove from service not later than December 31, 1983, all low pressure impellers which have not been inspected for cracks and do not have modification 1732 incorporated. NOTE: For the purposes of this AD, a flight cycle is considered to be an engine operating sequence fromtakeoff to landing. Airplanes may be ferried in accordance with the provisions of FAR 21.197 to a base where the AD can be accomplished. Upon request of the operator, equivalent means of compliance with the requirements of this AD may be approved by the Chief, Engineering and Manufacturing Branch, FAA, New England. The Manufacturer's Alert Service Bulletin identified and described in this directive 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 Technical Publications Department, Rolls-Royce, Ltd., East Kilbride G74 4PY, Scotland. The document may also be examined at Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts, 01803, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 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 the New England Region Office. Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust the compliance date(s) specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. This amendment becomes effective October 30, 1980.
2020-16-08: The FAA is correcting an airworthiness directive (AD) that published in the Federal Register. The AD applies to certain Aspen Avionics, Inc., Evolution Flight Display (EFD) EFD1000 Emergency Backup Display, EFD1000 Multi-Function Display, and EFD1000 Primary Flight Display systems installed on various airplanes. As published, the docket number and product identifier in the Comments Invited section of the preamble are incorrect. This document corrects that error. In all other respects, the original document remains the same; however, for clarity, the FAA is publishing the entire rule in the Federal Register.
60-16-04: 60-16-04 HARTZELL: Amdt. 182 Part 507 Federal Register July 29, 1960. Applies to All Propellers HC-82XF-1D, HC-82XF-1DB, HC-82XG-1D, HC-82XG-6DL, HC-82XL-1D, and HC-92ZK-8L; and to HC-82XK-1D Serial Numbers 100G Through 846G; and to HC-92ZK-8D Serial Numbers 100L Through 491L. These Propellers May Be Used On Such Aircraft As Piper PA-24, Cessna 180 and 182, Meyers 200, Mooney Mark 20, and Lake (Colonial) C-2. Compliance required as indicated. Because of failure or cracking of several cast guide collars, P/N 834-4, -8, -9, the following shall be accomplished: (a) Within the next 25 hours of propeller operation and each 25 hours of operation thereafter, visually inspect for cracks, all guide collars not marked with a letter "P" or "F". This inspection can be accomplished by looking through the spinner blade cutouts without removing the spinner. Cracked collars must be replaced prior to further flight. (b) At the next propeller overhaul or by January 1, 1961,whichever occurs first, replace all unmarked guide collars with marked guide collars. Cast collars which are marked with the letter "P" and forged collars which bear part number as cast collars but are marked with letter "F" have been tested and need not be inspected or replaced. (Hartzell Service Bulletin No. 71 covers this same subject.) This directive shall become effective 30 days after publication in the Federal Register.
80-21-10: 80-21-10 BEECH: Amendment 39-3967. Applies to Model 77 (serial numbers WA-1 through WA-156, WA-158 through WA-161, WA-163 through WA-171, WA-173, WA-174, WA-177 and WA-178) airplanes certificated in all categories. COMPLIANCE: Required as indicated unless already accomplished. To ensure the structural integrity of the engine mount attachment to the airplane, accomplish the following: A) Prior to further flight, accomplish the following: 1. Remove the engine cowling, support the tail of the airplane, and hoist the engine as required to remove weight from the engine mount attachment. 2. Remove and visually inspect for thread damage the four bolts and nuts attaching the engine mount to the firewall. Retain washers and nut retaining clips for reuse. The nut is held in place by a spring clip which may be removed with a magnet or wire hook. NOTE: Remove and inspect the engine mount attachment bolts and nuts one at a time. 3. Align the holes in the engine mount, firewall and fuselage frame. Ream the attachment holes in the firewall and fuselage frame to .375/.379 inch diameter. NOTE: A strap may be used between the engine mount tubes to pull the engine mount holes into alignment. If necessary to facilitate reaming of the firewall and attach fitting holes, support the engine and remove the remaining three bolts. 4. Replace damaged bolts and nuts with a new part of a P/N shown by Table I. Any thread damage on either a bolt or nut requires replacement of both the bolt and nut. Table I Bolt Nut 130909B71 2452-064 (use existing or or AN6-21A/M/(magnaflux inspected) LH8065-064 (use existing retainer) or NAS577-6A (use NAS578-6 retainer) 5. Ensure the bolts, washers, nuts and holes are clean and free of grease and oil. Align parts, install bolts, washers and nuts, and torque to 325 +0 -20 inch-pounds. Do not use a power wrench to install the bolts. 6. Remove the engine hoist and tail support and reinstall the engine cowling. B) Within five days report damaged bolts or other defects found as a result of any inspection required herein to the FAA via an M or D Report (FAA Form 8330-2) or a letter to the Chief, Aircraft Certification Program, Federal Aviation Administration, Room 238, Terminal Building 2299, Mid-Continent Airport, Wichita, Kansas 67209. Describe the defect found, location of bolt on firewall, total time-in-service on the airplane or part at time of discovery, and the aircraft serial number. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.) C) Any equivalent means of compliance with this AD must be approved by the Chief, Aircraft Certification Program, Federal Aviation Administration, Room 238, Terminal Building 2299, Mid-Continent Airport, Wichita, Kansas 67209, telephone (316) 942-4285. Beechcraft Service Instructions No. 1153 and Beech Mailgram Number 80-452-940 pertain to the subject matter of this AD. This amendment becomes effective on November 13, 1980, to all persons except those to whom it has already been made effective by an airmail letter from the FAA dated October 10, 1980, and is identified as AD 80-21-10.
84-03-08: 84-03-08 AIRBUS INDUSTRIE: Amendment 39-4806. Applies to Model A300 airplanes, certificated in all categories and whose serial numbers are listed in paragraph 1, Planning Information, of Airbus Industrie (AI) Service Bulletin A300-32-356, Revision 1, dated December 1, 1982. To prevent failure of main landing gear hinge arms, accomplish the following unless previously accomplished: A. Within 120 days from the effective date of this AD, measure the displacement of the bronze bushing fitted in the stirrup on the actuating cylinder side of all affected hinge arms in accordance with paragraph 2.B of Messier-Hispano-Bugatti (MHB) Service Bulletin 470-32-422, Revision 1, dated December 3, 1982. Depending on the results of the above measurements and within the number of landings specified in the service bulletin, repeat the measurement of the displacement or visually inspect for corrosion, as appropriate, the blending radii of attachment between the trunnions and the hinge arm bodyin accordance with the instructions of the service bulletin. 1. If no trace of corrosion is found, incorporate the modifications AI 4544/S5351 and AI 4544/S5548, described in AI Service Bulletins A300-32-348, Revision 2 and A300-32-355, Revision 2, both dated May 16, 1983, and in accordance with the instructions of MHB Service Bulletins 470-32-421, Revision 2 and 470-32-407, Revision 2, both dated March 31, 1983. 2. If corrosion is detected, replace the affected hinge arms prior to further flight either with new arms or with arms modified in accordance with the instructions of MHB Service Bulletin 470-32-431, dated December 24, 1982, related to AI Service Bulletin A300-32- 362, dated June 15, 1983, after incorporating the modifications required by paragraph A.1. of this AD. 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 March 19, 1984.
2020-13-09: The FAA is adopting a new airworthiness directive (AD) for all DG Flugzeugbau GmbH Models DG-500 Elan Orion, DG-500 Elan Trainer, DG- 500/20 Elan, DG-500/22 Elan, DG-500M, and DG-500MB gliders and certain Models DG-1000S and DG-1000T gliders. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as the rear locking rod of the rear canopy rotating out of the threads of the operating mechanism, which could lead to blocking of the canopy emergency release system, preventing safe escape of occupants from the glider. The FAA is issuing this AD to require actions to address the unsafe condition on these products.
60-02-03: 60-02-03 BOEING: Amdt. 79 Part 507 Federal Register January 15, 1960. Applies to the following 707-100 Series Aircraft Only: Serial Numbers 17586 through 17591, 17609 through 17612, 17628 through 17650, 17658 through 17672, 17696 through 17702, 17925 through 17927.\n \n\tCompliance required by June 1, 1960.\n \n\tBecause of the hazardous condition caused by water injection system failures, the following modifications shall be accomplished as indicated: \n\n\t(a) Relocate the water inlet valve switch from the co-pilot's panel to the flight engineer's panel and add four transient position blue indicating lights (one for each valve). Install a placard for nomenclature.\n \n\t(b) Change water booster pumps start switch on co-pilot's panel to a two-position toggle switch. \n\n\t(c) Install an appropriate placard adjacent to the water booster pump switch to specify that this switch is to be turned off after the water pressure lights go out at the end of water injection. This is necessary to avoid damaging the tank mounted water booster pump after water runout. These modifications are included in Boeing Service Bulletin No. 194 (R-1) dated June 19, 1959. \n\n\tRevised March 29, 1960.
82-25-04: 82-25-04 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-4505. Applies to Model SA330J series helicopters certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent fretting corrosion on the flapping hinge subsequent to loosening of the hinge pin attachment nut, 330A.31.1567.20 or 330A.31.1585.20, accomplish the following: (a) Within the next 25 flight hours after the effective date of this AD, check the torque of the flapping hinge pin nut in accordance with Aerospatiale SA330 Service Bulletin No. 05.65, paragraph 1C(1)(a) or an equivalent approved by the Manager, FAA, Europe, Africa, and Middle East Office, and thereafter at each P2 inspection (300 hours). (b) If the torque value is less than 10 mdaN (74 foot-pounds), adjust the torque in accordance with Aerospatiale SA330 Service Bulletin No. 05.65, paragraph 1C(1)(c) and accomplish the inspection in accordance with paragraph 1C(2)(a) at the nextP2 inspection (300 hours) or an equivalent approved by the Manager, FAA, Europe, Africa, and Middle East Office. This amendment becomes effective December 14, 1982.
2020-15-15: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model EC225LP helicopters. This AD was prompted by a mechanical deformation found on the protective cover of the ''SHEAR'' control pushbutton installed on a copilot collective stick. This AD requires modification of the helicopter by replacing the protective cover and re-identifying the part number of the pilot and copilot collective sticks. The FAA is issuing this AD to address the unsafe condition on these products.
2020-16-10: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Inc. (Bell) Model 204B, 205A, 205A-1, 205B, 212, 214B, 214B-1, 412, 412CF, and 412EP helicopters. This AD was prompted by a report of a shoulder harness seat belt comfort clip (comfort clip) interfering with the seat belt inertia reel. This AD requires removing comfort clips from service and inspecting the seat belt shoulder harness (harness) for a rip or an abrasion. The actions of this AD are intended to address an unsafe condition on these products.
79-16-02: 79-16-02 INDIANA MILLS AND MANUFACTURING, INC.: Amendment 39-3519. Applies to Model IMM 111040-1, -2, -3, -4 and -8 safety belt assemblies marked as meeting the standards of FAA TSO-C22f. These safety belts are installed in, but not limited to, Gulfstream American Corp. (formerly Grumman American Aviation Corp.) AA-1B, AA-1C, AA-5, AA-5A, AA-5B model airplanes. These safety belts can no longer be considered to meet the standards prescribed by FAA TSO-C22f and the approved special criteria for push-button release mechanisms which requires the push-button release force to be between 2.5 and 8 pounds when using the loading conditions specified in FAA TSO-C22f (Section 4.3.2.2 of NAS 802). Within 120 days from the effective date of the AD, these safety belts shall not be used in type certificated aircraft. NOTE - Information regarding replacement safety belts for Gulfstream American airplanes can be obtained from: Gulfstream Light Aircraft Customer Service P.O. Box 2206 Savannah, Georgia 31410 Telephone (912) 964-3000 Telex 54-6470 This amendment becomes effective August 2, 1979.
2020-16-03: The FAA is adopting a new airworthiness directive (AD) for PZL Swidnik S.A. (PZL) Model PZL W-3A helicopters. This AD requires establishing a life limit for certain horizontal stabilizers and removing from service any affected horizontal stabilizer in accordance with that life limit. This AD was prompted by the discovery of an error in the Airworthiness Limitations for PZL Model PZL W-3A helicopters. The actions of this AD are intended to address an unsafe condition on these products.
80-08-04: 80-08-04 CHADWICK, INC.: Amendment 39-3736. Applies to all Hughes model 369 helicopters equipped with Chadwick model C-20 Auxiliary Fuel System installed as per STC SH129WE and Bell model 206 helicopters equipped with Chadwick, Inc. model C-22 Auxiliary Fuel System installed per STC SH139WE. Compliance is required as indicated. To prevent a static discharge type of source ignition, accomplish the following: A. Within 120 days after the effective date of this Airworthiness Directive, unless already accomplished, install the Chadwick, Inc. supplied appropriate bonding and grounding harness kit in accordance with Chadwick, Inc., Installation Instructions dated January 2, 1980, (for the C-20 installation) or December 27, 1979, (for the C-22 installation), or an equivalent modification approved by the Chief, B. Conduct a continuity check every 100 hours time in service while equipped with the Chadwick, Inc. auxiliary fuel system, to assure proper grounding between attach points of bonding and grounding kits. Reference: AC 43.13.1A, Chapter 11, Section 3, Paragraph 452, Page 188. 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 Chadwick, Inc., 11969 Southwest Herman Road, Sherwood, Oregon 97140. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment becomes effective April 17, 1980.
2020-12-15: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by a report that certain safety valves at the left- and right-hand sides of the cabin pressure control system were not installed correctly and that the trunnion nuts used to fasten the V-band clamp were over torqued. This AD requires a measurement of the trunnion nut torque of the V-band clamp, an inspection of the safety valve and airplane bulkhead flange area for any cracking and deformations, and corrective actions, if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
61-04-01: 61-04-01 BRANTLY: Amdt. 252 Part 507 Federal Register February 10, 1961. Applies to All B-2 Helicopters. Compliance required as indicated. Instances have occurred wherein the centrifugal clutch has failed to release at engine shutdown and subsequent restarting has sheared the bolts which transmit torque from the B2-8-14 clutch disc assembly into the fabric coupling and from the fabric coupling into the lugs of the free-wheeling clutch housing. To preclude recurrence of this condition the following must be accomplished: (a) Within the next 10 hours of flight time after the effective date of this directive, inspect all 6 of the AN 4-10A bolts which secure the fabric coupling to the B2-8-14 clutch disc assembly and to the free-wheeling clutch housing for shear failure. This inspection is to be accomplished by inserting an appropriately sized wrench through the lubrication access hole in the B2-7-17 clutch dust cover and checking each bolt for snugness. Any sheared bolts must be replaced prior to further operation. (b) Within the next 10 hours of flight time after the effective date of this directive a placard shall be installed immediately aft or incorporated with the operating limitations placard located between the fuel mixture control and the carburetor heat control levers to read: "PRIOR TO EACH ENGINE START, TURN ROTOR BACKWARD BY HAND THROUGH 30 DEGREES MINIMUM TO CHECK CLUTCH FREEDOM." The purpose of this placard is to insure that these coupling bolts are not subjected to damage resulting from failure of the clutch to release. (Brantly Service Bulletin No. 6 covers this same subject.) This directive effective February 22, 1961.
2020-11-01: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation (Gulfstream) Model GVI airplanes. This AD was prompted by a report that the primary flight control actuation system (PFCAS) linear variable displacement transducer (LVDT) mechanical disconnect monitor may not trigger the disconnect of the affected control surfaces as required in the event of a control surface failure. This AD requires updating the software of each PFCAS remote electronics unit (REU), which includes an improvement to the LVDT. The FAA is issuing this AD to address the unsafe condition on these products.
80-15-08: 80-15-08 SLINGSBY: Amendment 39-3849. Applies to Model T65A Vega gliders, all serial numbers up to and including 1913, certificated in all categories. Compliance required as indicated. To prevent main wing failure due to possible inadequate bonding of the main wing shear web to the wing spar cap, accomplish and operate the glider in accordance with the following: (a) Prior to further flight: (1) Install a placard in full view of and legible to the pilot which reads: Both VNE and rough air airspeed are restricted to 95 kts. maximum. Maximum gross weight is limited to 775 lbs. (2) Install a red radial line on the airspeed indicator dial face at 95 kts., VNE, indicated airspeed. Check the airspeed indicator dial face to determine if it is free to turn. The red radial line may be installed on the airspeed indicator face glass, if the face glass is firmly fixed and not free to turn. If the face glass is free to turn, install the red radial line on the airspeed instrument face. (b) Within the next 100 hours time in service after the effective date of this AD, unless already accomplished, replace the main wing with a Slingsby certified serviceable wing which is identified with "Mod. 27 embodied" adjacent to the wing serial number or with a serviceable wing approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, Brussels, Belgium, at which time the limitations imposed by paragraph (a) of this AD no longer apply. NOTE: Slingsby Technical Instruction No. 38 pertains to this AD and provides guidance to glider owners affected by this AD on obtaining serviceable replacement wings from Slingsby or through Slingsby authorized representatives. This amendment becomes effective July 17, 1980, as to all persons except to those persons to whom it was made immediately effective by telegraphic AD T79EU-12, issued September 12, 1979, which contained this amendment.
81-10-06: 81-10-06 McDONNELL DOUGLAS: Amendment 39-4109. Applies to McDonnell Douglas Model DC-10-10, -10F, -30, -30F, and -40 series airplanes certificated in all categories utilizing the following slide or slide/raft assemblies at the No. 3 door: \n\n\nManufacturer\nPart No. \nLeft-Hand Door \nSargent Industries, Pico Division\n5LD230500-112 \n\n5LD230500-114 \n\n5WD230500-101 \n\n5WD230500-101 (DAW95) \n\n5WD230500-201\n\n5WD230500-201 (DAW95) \n\n5WD230500-401 \n\n5WD230500-401 (DAW95)\nAir Cruisers Company\n24D29220-3 \n\n24D30051-11 \n\n24D30051-11 (DAW98) \n\n24D30051-13 (DAW98) \n\n24D30051-51 \n\n24D30051-53 (DAW98) \n\n24D30051-91 \n\nRight-Hand Door \nSargent Industries, Pico Division\t\n5LD230600-112 \n\n5LD230600-114 \n\n5WD230600-101 \n\n5WD230600-101 (DAW95) \n\n5WD230600-201 \n\n5WD230600-201 (DAW95) \n\n5WD230600-401 \n\n5WD230600-401 (DAW95) \nAir Cruisers Company\n24D29220-4 \n\n24D30051-21 \n\n24D30051-21 (DAW98) \n\n24D30051-23 (DAW98)\n\n24D30051-61 \n\n24D30051-63 (DAW98) \n\n24D30051-101\n\t\t\t\n\tCompliance is required as indicated unless already accomplished. \n\n\tTo prevent improper deployment of No. 3 door slide or slide/raft, accomplish the following: \n\n\tAt the next slide or slide/raft assembly overhaul after the effective date of this AD, but in no case exceeding three years from the effective date of this AD, unless already accomplished, modify the affected evacuation system assemblies and container assembly, Douglas P/N AWD7446-503, in accordance with Part 2 of Douglas Service Bulletin No. 25-278 dated March 7, 1980. \n\n\tAlternate methods of compliance may be used when approved by the Chief, Los Angeles Area Aircraft Certification Office, Northwest Region. \n\n\tThe 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). \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). \n\n\tThese documents also may be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108, or 15000 Aviation Boulevard, Hawthorne, California 90261, Room 6W14. \n\n\tThis amendment becomes effective June 12, 1981.
63-25-02: 63-25-02 LOCKHEED: Amdt. 651 Part 507 Federal Register November 30, 1963. Applies to All Models 49, 149, 649, 649A, 749, 749A, 1049-54, 1049C, 1049D, 1049E, 1049G, and 1049H Series Aircraft. Compliance required as indicated. As a result of several fatigue failures of the nose landing gear actuating cylinder attach bolts, accomplish the following: (a) For operators maintaining records of landings, within the next 1,000 landings after the effective date of this AD, unless already accomplished within the last 5,000 landings, and thereafter within each 6,000 landings from the last replacement, comply with (c). Where past records of landings are unavailable the number of landings prior to the effective date of this AD may be obtained by substituting one landing for each hour of time in service prior to the effective date of this AD. (b) For operators not maintaining records of landings, within the next 1,000 hours' time in service after the effective date of this AD, unless already accomplished within the last 5,000 hours' time in service, and thereafter within each 6,000 hours' time in service from the last replacement, comply with (c). (c) Replace the nose landing gear actuating cylinder bolts as follows: (1) Replace the two forward bolts, P/N 307403 and P/N 307404, which attach the forward end of the actuating cylinder to the fuselage structure via a universal joint, with new bolts of the same part numbers. (2) Replace the aft bolt, P/N 307402, which attaches the actuating cylinder rod to the drag strut pivot, with a new bolt of the same part number. (3) For those aircraft which use P/N 272216-3 and P/N 272238 in lieu of P/N 307402 and P/N 307403, replace these bolts with new bolts of the same part numbers or replace P/N 272216-3 with P/N 307402 and replace P/N 272238 with P/N 307403 in accordance with items 1, 2, 3, 5, 6, and 7 of the section entitled "Description of Change B" of Lockheed Service Bulletin 49/SB-616. (4) Forthose aircraft which use P/N 272216-2 in lieu of P/N 307404 replace this bolt with P/N 307404 and accomplish the rework of the section entitled "Description of Change A", Lockheed Service Bulletin 49/SB-616. This supersedes AD 63-01-02. This directive effective December 30, 1963.