Results
2001-13-20: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that currently requires a detailed visual inspection to detect damage to the terminal lugs on the 12XC and 15XE contactors and the mounting lugs on the 15XE contactor; corrective actions, if necessary; and certain conditional repetitive inspections. This action adds requirements for installation of a new mounting bracket for the 15XE contactor, modification of the cable attachment adjacent to the contactor, and replacement of certain terminal lugs on the 15XE contactor by terminal lugs with a thicker contact area. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent excessive vibrations generated by the mounting configuration of the 15XE contactor, which could cause breakage of the terminal and mounting lugs on the 15XE contactors in the 101VU panel in the avionics compartment, resulting in loss of electrical power from the standby generator.
2025-13-06: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Deutschland GmbH Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, EC135T3, and EC635T2+ helicopters. This AD was prompted by a report of a loss of the tail rotor controls due to a broken control rod of the yaw actuator. This AD requires visual inspection of the ball pivot, fluorescent penetrant inspection of the control rod, visual inspection and measurement of certain parts of the yaw actuator assembly, and depending on the results of these inspections, corrective actions. This AD also prohibits installing an affected part unless it is a serviceable part and certain requirements are met. The FAA is issuing this AD to address the unsafe condition on these products.
78-17-03: 78-17-03 BELL HELICOPTER TEXTRON (BHT): Amendment 39-3282 as amended by Amendment 39-3359 (Airworthiness Docket No. 78-ASW-37). Applies to Model 212 helicopters certificated in all categories equipped with main transmission spiral bevel gear, P/N 204-040-701-3. Compliance is required as indicated. To minimize the possibility of failure of the input spiral bevel gear, P/N 204-040-701-3, used in the main transmission of Bell Helicopter Textron (BHT) Model 212 helicopters, accomplish the following: a. Within the next 25 hours time in service after the effective date of this Airworthiness Directive (AD): 1. For helicopters with rotor brakes, remove the rotor brake quill assembly, P/N 205-040-300-1, as prescribed by paragraph 1 of Part I of BHT Service Bulletin No. 212-78-8, dated July 28, 1978, or later FAA approved revision. 2. For helicopters without rotor brakes, remove the cover plate, P/N 204-040-174-1, from the left side of the transmission. 3. Utilizing the opening provided by step 1 or step 2, above, inspect all 62 teeth of the main spiral bevel gear, P/N 204-040-701-3, as prescribed by paragraph 2 of Part I of BHT Service Bulletin No. 212-78-8, dated July 28, 1978, or later FAA approved revision. 4. Remove and replace any gear that does not meet the inspection requirements set forth in step 3, above. Utilize instructions in the appropriate maintenance and overhaul manual for this procedure. 5. Install cover, P/N 204-040-174-1, over rotor brake quill port, reinstall panels and cowling, and perform the ground run utilizing procedures prescribed by paragraphs 4, 5, and 6 of Part I of BHT Service Bulletin No. 212-78-8, dated July 28, 1978, or later FAA approved revision. 6. Install adjacent to the limitation placard on the rotor brake handle in the crew compartment a decal or placard with the following words: ROTOR BRAKE INOPERATIVE. Letters are to be 1/8-inch minimum height printed or embossed on a contrasting background. b. Within 25 hours time in service after accomplishment of the requirements of paragraph a. of this AD, and thereafter at intervals not to exceed 25 hours time in service, conduct the inspections and replacement, if appropriate, prescribed by Part II of BHT Service Bulletin No. 212-78-8, dated July 28, 1978, or later FAA approved revision. BHT Service Bulletin No. 212-78-8 pertains to and provides for accomplishing the intent of this AD except that in addition, paragraph a, step 6, of this AD must also be accomplished. BHT Service Bulletin No. 212-78-12 also provides instructions and details pertinent to this AD. Except as specifically provided otherwise by this AD, the manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part thereof pursuant to 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 Textron, Post Office Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76106, and at the Federal Aviation Administration Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. Equivalent means of compliance with the requirements prescribed by this AD may be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, Post Office Box 1689, Fort Worth, Texas 76101. Amendment 39-3282 became effective August 21, 1978. This amendment 39-3359 becomes effective November 22, 1978.
89-22-16: 89-22-16 GARRETT ENGINE DIVISION: Priority Letter AD issued on October 26, 1989. Applicability: Garrett Turbofan Engine Models TFE731-2, -5, -5AR, and -5R, certificated in any category, installed on, but not limited to, the following aircraft: Lear Jet M31, CASA 101, Falcon 900, Falcon 20-5, and BAe 125-800. Compliance: Required as indicated, unless already accomplished. To prevent an uncommanded engine acceleration or deceleration, accomplish the following: (a) Review the engine log book or maintenance records on the previously listed engine models to determine if DEEC Part Number 2118002-6, 2118002-8, 2118002-9, or 2118002-201 with one of the following serial numbers is installed. Spare DEEC's must also be checked for applicable part number and serial number. DEEC SERIAL NUMBERS PN 2118002-6 PN 2118002-9 PN 2118002-20 68-1094 108-1159 48-1049 78-1128 58-138 68-1095 108-1160 48-1059 78-1129 58-139 69-1096 108-1161 48-1060 78-1130 58-140 68-1097 108-1162 48-1061 78-1131 58-145 68-1106 108-1163 48-1063 78-1133 58-147 68-1108 108-1164 48-1071 78-1134 58-148 68-1109 108-1166 48-1072 78-1135 58-150 68-1110 108-1167 78-1113 78-1136 108-151 68-1111 108-1168 78-1114 78-1137 108-152 68-1112 108-1169 78-1115 78-1138 108-153 108-1152 108-1170 78-1116 78-1139 108-154 108-1154 108-1171 78-1117 78-1140 108-155 108-1155 108-1172 78-1118 78-1141 108-157 108-1156 108-1173 78-1119 78-1142 108-159 108-1157 108-1174 78-1120 78-1145 108-160 108-1158 78-1121 78-1146 108-162 78-1122 78-1147 108-164 PN 2118002-8 78-1123 78-1148 108-165 47-778 78-1124 78-1149 108-166 77-861 78-1125 78-1150 108-167 77-862 78-1126 78-1151 108-168 77-873 78-1127 108-169 108-170 108-172 (b) Remove from service, if necessary, suspect serial numbered DEEC's listed in paragraph (a) with less than 50engine hours time since new within the next 25 engine operating hours after receipt of this priority letter AD, and DEEC's with 50 or more engine hours time since new within the next 100 engine operating hours after receipt of this priority letter AD, and replace with a serviceable DEEC. NOTE: Refer to Garrett Service Bulletin (SB) TFE731-76-3049, dated October 6, 1989, to determine previous accomplishment with this AD, and for removal, installation, repair, and re-identification information for these suspect DEEC's. (c) Repair and re-identify, before further flight, in accordance with the Garrett SB TFE731-76-3049, dated October 6, 1989, suspect serial numbered DEEC's listed in paragraph (a) installed on a spare engine or located as a spare part. (d) Revise the applicable FAA Approved Airplane Flight Manual (AFM) to provide interim emergency procedures to flight crews on airplanes affected by paragraphs (a) and (b), within 10 calendar days after receipt of this priority letter AD, by adding the following: EMERGENCY PROCEDURES In the event that uncommanded engine acceleration or deceleration is experienced: (1) Place power lever for the affected engine in an intermediate position (slightly aft of cruise). (2) Select computer OFF on affected engine (remove electrical power to DEEC). (3) Re-adjust power lever as necessary. (4) Continue with affected computer OFF for the remainder of the flight. NOTE: It is also possible that the DEEC malfunction may affect the reserve power function on engines so equipped; therefore, it is important to conduct the normal reserve power pre-flight check prior to flights during which reserve power may be used. (e) A copy of this AD inserted in the FAA Approved AFM may be considered an acceptable means of compliance with the required AFM revision. (f) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (g) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this priority letter AD or adjustments to the compliance schedule specified in this priority letter AD may be approved by the Manager, Los Angeles Aircraft Certification Office, Transport Airplane Directorate, Aircraft Certification Service, Federal Aviation Administration, 3229 East Spring Street, Long Beach, California 90806-2425. (h) Documents pertinent to this priority letter AD may be obtained, upon request, from Garrett General Aviation Services Division, Distribution Center, 2340 East University, Phoenix, Arizona 85037; telephone (602) 255-2548, or may be examined at the office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Rules Docket No. 89-ANE-42. Priority Letter AD 89-22-16, issued on October 26, 1989,becomes effective immediately upon receipt.
91-24-13: 91-24-13 SIKORSKY AIRCRAFT: Amendment 39-8100. Docket No. 91-ASW-07. Applicability: All Sikorsky Aircraft Model S-76A helicopters, certificated in any category, equipped with forward spar cap angles, part numbers (P/N's) 76201-05001-103 and 76201-05001-104, forward spar web, P/N 76201-05001-101, and forward spar web doubler, P/N 76201-05001-107, and not equipped with Modification Kit 76070-20086 installed in accordance with Sikorsky Alert Service Bulletin No. 76-55-12, dated June 6, 1986. Compliance: Required as indicated, unless already accomplished. To prevent failure of the helicopter vertical pylon forward spar cap, web, and web doubler, accomplish the following: (a) For helicopters that have attained 100 or more hours' time in service, comply with paragraph (c) within the next 25 hours' time in service after the effective date of this AD unless already accomplished within the last 25 hours' time in service, and thereafter at intervals not to exceed 50 hours' time in service from the last inspection. (b) For helicopters that have not attained 100 hours' time in service on the effective date of this AD, comply with paragraph (c) before attaining 125 hours' time in service, and thereafter at intervals not to exceed 50 hours' time in service. (c) Inspect for cracks in the forward spar cap angles, spar web, and web doubler and in repairs and reinforcements in the area of the tail rotor shaft cutout in the pylon forward spar and areas adjacent to the fuselage shear deck as follows: (1) Remove the tail rotor drive shaft fairings in the vicinity of the vertical pylon, exposing the shear deck and vertical pylon forward spar. (2) Clean all accessible areas around the tail rotor drive shaft cutout area in the vertical pylon forward spar using a clean cloth dampened with solvent P-D-680, Type II, or FAA-approved equivalent. (3) Using a light, visually inspect the forward side of the spar for cracks in all areas adjacentto the shear deck attachment to the forward spar web and the web doubler. (4) Using a light and mirror, visually inspect the aft side of the spar for cracks. Inspect through the tail rotor drive shaft cutout. (5) If cracks are found in the spar web or spar web doubler or in their repair or reinforcement parts, accomplish the following: (i) For each part, if multiple cracks are found or if a single crack equal to or in excess of 2 1/2 inches in length is found, replace cracked parts prior to further flight with new parts of the same part number; or if not previously repaired or reinforced, incorporate a repair procedure contained in Sikorsky Overhaul and Repair Instructions (O&RI) 76200-014B, or later FAA-approved revisions, or an equivalent procedure approved as noted in paragraph (d) of this AD. (ii) If a single crack is less than 2 1/2 inches in length, visually inspect the part for crack length prior to the first flight of each day, and-- (A) Within 25 hours' time in service after finding a crack, replace or repair the part in accordance with paragraph (c)(5)(i), except (B) Replace or repair the affected part in accordance with paragraph (c)(5)(i) before further flight, whenever the crack length reaches 2 1/2 inches. (6) If a crack is found in the spar cap angles, replace the cracked spar cap angles prior to further flight with a new spar cap angle of the same part number in accordance with Sikorsky Maintenance Manual SA 4047-76-2, or approved equivalent procedures as noted in paragraph (d) of this AD. (7) Reinstall the tail rotor drive shaft fairings after the inspections and rework, as necessary, of paragraphs (c)(1) through (c)(6) are completed. (d) Alternate inspections, repairs, modifications, or other means of compliance which provide an equivalent level of safety, may be used if approved by the Manager, Boston Aircraft Certification Office, FAA, New England Region, 12 New England Executive Park,Burlington, Massachusetts, 01803. (e) On request of an operator, an FAA maintenance inspector, subject to prior approval of the Manager, Boston Aircraft Certification Office, may extend the repetitive inspection interval specified in this AD if the request contains justifying data. (f) This amendment supersedes Amendment 39-4711 (48 FR 39052, August 29, 1983), AD 83-17-07, as amended by Amendment 39-5017 (50 FR 15099, April 17, 1985), AD 83-17-07 R1, and by Amendment 39-5332 (51 FR 24134, July 2, 1986), AD 83-17-07 R2. (g) This amendment (39-8100, AD 91-24-13) becomes effective on December 20, 1991.
2022-25-06: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC-8-402 airplanes. This AD was prompted by an investigation that found that the actual operating temperatures within the integrated flight cabinet (IFC) were significantly higher than anticipated during certification. This AD requires a modification to improve the IFC cooling capacity. The FAA is issuing this AD to address the unsafe condition on these products.
2016-20-03: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200, -300, and -400ER series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the skin lap splice is subject to widespread fatigue damage (WFD). This AD requires repetitive external detailed and surface high frequency eddy current (HFEC) inspections of the outer skin for cracking around fastener heads common to the inboard fastener row of the skin lap splice and corrective action. We are issuing this AD to detect and correct fatigue cracking of the skin lap splice, which could grow and result in possible rapid decompression and reduced structural integrity of the airplane.
2001-13-17: This amendment adopts a new airworthiness directive (AD) that is applicable to all Airbus Model A300 B2 and A300 B4; A300 B4-600, B4-600R, and F4-600R (collectively called A300-600); and A310 series airplanes. This action requires revising the Airplane Flight Manual to advise the flight crew of appropriate procedures to follow in the event of lost or erroneous airspeed indications. This action is necessary to prevent inadvertent excursions outside the normal flight envelope. This action is intended to address the identified unsafe condition.
91-05-07: 91-05-07 PILATUS BRITTEN-NORMAN (PBN): Amendment 39-6891. Docket No. 90-CE-32-AD. Applicability: Model BN-2T Turbine Islander airplanes (all serial numbers), certificated in any category, that do not have PBN Modification Number NB/M/1415 incorporated. Compliance: Required within the next 200 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished. To ensure the ability to restart the engines in flight if an undetected circuit breaker trip does occur, accomplish the following: (a) Modify the airplane electrical system in accordance with the instructions in PBN Service Bulletin BN2/SB 194, dated April 11, 1990. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished. (c) An alternate method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved bythe Manager, Brussels Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Staff. (d) All persons affected by this directive may obtain copies of the document referred to herein upon request to Pilatus Britten-Norman Limited, Bembridge Airport, Isle of Wight, PO36 5PR, England; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-6891, AD 91-05-07) becomes effective on March 25, 1991.
2016-20-08: We are superseding Airworthiness Directive (AD) 95-21-09 for all Airbus Model A300 series airplanes, and Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 95- 21-09 required repetitive inspections for cracking of the No. 2 flap beams, and replacement of the flap beams, if necessary; and provided optional modifications for extending certain inspection thresholds, and an optional terminating modification for certain inspections. This new AD requires reduced compliance times for inspections and also reduces the number of airplanes affected. This AD was prompted by a determination that the compliance times must be reduced. We are issuing this AD to detect and correct cracking of the No. 2 flap beams, which could result in rupture of the flap beams and reduced structural integrity of the airplane.
2016-21-04: We are adopting a new airworthiness directive (AD) for certain Continental Motors, Inc. (CMI) TSIO-550-K, TSIOF-550-K, TSIO-550-C, TSIOF-550-D, and TSIO-550-N reciprocating engines. This AD was [[Page 70930]] prompted by a report of an uncommanded in-flight shutdown (IFSD) resulting in injuries and significant airplane damage. This AD requires replacing the oil cooler cross fitting assembly. We are issuing this AD to prevent failure of the oil cooler cross fitting and engine, IFSD, and loss of the airplane.
2001-13-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes. This AD requires repetitive inspections to detect cracks and corrosion around the lower bearing of the actuator attach fittings of the inboard and outboard flaps. This AD also requires repetitive overhauls for certain actuator attach fittings or repetitive replacement of the fittings with new fittings, as applicable, which terminates the repetitive inspections. This AD also provides for replacement of actuator attach fittings with improved fittings, which terminates all requirements of this AD. This amendment is prompted by reports of cracks on the lower bearing journal of the inboard actuator attach fittings of the outboard trailing edge flaps due to stress corrosion. The actions specified by this AD are intended to detect and correct cracking on the actuator attach fittings of the trailing edge flaps, which could result in abnormal operation or retraction of a trailing edge flap, and consequent reduced controllability of the airplane.
86-08-04 R1: 86-08-04 R1 PRATT & WHITNEY: Amendment 39-5287 as amended by Amendment 39-5424. Applies to Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR turbofan engines. Compliance is required as indicated unless already accomplished. To prevent crack propagation and subsequent high pressure compressor (HPC) removable sleeve spacer rupture, perform a one time, eddy current inspection of HPC removable sleeve spacers stages 7-8, 8-9, and 9-10 for cracks, and replace all stages of HPC removable sleeve spacers with the respective HPC integral sleeve spacers, in accordance with the procedures of PW Alert Service Bulletin (ASB) 5649, dated January 15, 1986, or FAA approved equivalent, per the following schedule: (a) For HPC removable sleeve spacers stages 7-8, 8-9, and 9-10: (1) Inspect spacers within the next 1,000 cycles in service from the effective date of this AD, or prior to reaching 1,700 cycles since the last in-shop fluorescent penetrant or ultrasonic inspection, whichever occurs later. (2) Remove cracked spacers from service prior to further flight. (3) Report the following information in writing for each inspection within 30 days of the inspection to the Manager, Engine Certification Office, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, (telex No. 949301 FAANE BURL) (reporting approved by the Office of Management and Budget (OMB) under OMB Number 2120-1156). (i) Engine serial number (ii) Inspection date (iii) Spacer part number and serial number (iv) Spacer total time and cycles (v) Spacer time and cycles since last inspection (vi) Spacer disposition (crack indication, no crack indication) (vii) If a crack indication is present, report confirmation of location and crack size within 30 days after engine disassembly. (b) Replace HPC removable sleeve spacers stages 7-8, 8-9, and 9-10 with the integral sleeve spacers at the next HPC rotor disassembly, but not to exceed 2 calendar years or 4,000 cycles in service, whichever occurs later from the effective date of this AD. (c) Replace HPC removable sleeve spacers stages 10-11, 11-12, and 12-13 with the integral sleeve spacers at the next HPC rotor disassembly. NOTES: (1) For the purposes of this AD, HPC rotor disassembly is defined as removal of any disk, spacer, or hub from the HPC rotor. (2) For the purposes of this AD, the last in-shop fluorescent penetrant or ultrasonic inspection is that conducted in accordance with the procedures identified and described in the PW JT8D restructured Engine Manual Part Number 481672 or FAA approved equivalent. Aircraft may be ferried in accordance with the provisions of FAR Parts 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance time specified in this AD. PW ASB 5649, dated January 15, 1986, 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 a copy upon request to Pratt & Whitney, Publication Department, P.O. Box 611, Middletown, Connecticut 06457. This document also may be examined at the Office of the Regional Counsel, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, Rules Docket Number 85-ANE-46, Room Number 311, between the hours of 8:00 a.m. and4:30 p.m., Monday through Friday except Federal holidays. The provisions of this amendment applicable to the stage 8-9 spacer become effective on the effective date of this amendment. The remaining provisions of this amendment applicable to stages 7-8 and 9-10 spacers are effective on May 27, 1986. This amendment amends Amendment 39-5287 (51 FR 12690), AD 86-08-04. This amendment becomes effective on November 4, 1986.
47-31-01: 47-31-01 NAVION: (Was Mandatory Note 10 of AD-782-3.) Applies to All Serials Up to and Including Number NAV-4-947. To be accomplished not later than October 1, 1947. To reduce the possibility of nose gear hydraulic actuating cylinder line failures due to inflexibility, the cylinders must be removed and reinstalled with the lines therefrom leading aft. Each of the present lines must be replaced with a longer line incorporating a "U" bend. (North American Field Service Bulletin No. 28 covers this same subject.)
2016-19-17: We are superseding Airworthiness Directive (AD) 2010-23-19 for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, and 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, and Model CL-600-2D24 (Regional Jet Series 900) airplanes. AD 2010-23-19 required repetitive inspections for damage of the main landing gear (MLG) inboard doors and fairing, and corrective actions if necessary. This new AD requires repetitive inspections for damage of the MLG inboard doors, MLG fairing, and adjacent structures of the MLG inboard doors, and corrective actions if necessary; replacement of the MLG fairing seal; and a terminating action involving increasing the clearances between the MLG fairing and MLG door. This new AD also adds one airplane and removes others from the applicability. This AD was prompted by reports of the MLG failing to fully extend. We are issuing this AD to prevent loss of controllability of the airplane during landing.
2001-13-03: This amendment adopts a new airworthiness directive (AD) for Kaman Aerospace Corporation (Kaman) Model K-1200 helicopters that requires reducing the life limit of the rotor shaft and teeter pin assembly and establishing a life limit for the flap clevis. This amendment is prompted by the discovery of cracks in parts that were returned to the manufacturer. The actions specified by this AD are intended to prevent failure of the rotor shaft, teeter pin assembly, or flap clevis due to fatigue cracks, and subsequent loss of control of the helicopter.
2016-19-09: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) GE90-76B, GE90-77B, GE90-85B, GE90-90B, and GE90-94B turbofan engines with high-pressure compressor (HPC) stage 8-10 spool, part numbers (P/Ns) 1694M80G04, 1844M90G01, or [[Page 67099]] 1844M90G02, installed. This AD was prompted by reports of cracks found on the seal teeth of the HPC stage 8-10 spool. This AD requires eddy current inspections (ECIs) or fluorescent penetrant inspections (FPIs) of the HPC stage 8-10 spool seal teeth and removing from service those parts that fail inspection. We are issuing this AD to prevent failure of the HPC stage 8-10 spool, uncontained rotor release, damage to the engine, and damage to the airplane.
2001-13-09: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-2C, B4-103, and B4-203 series airplanes, that requires a one-time inspection of the space between the fuel quantity indication (FQI) probes and any adjacent structures for minimum clearance, and corrective action, if necessary. The actions specified by this AD are intended to prevent the possibility of electrical arcing to the fuel tank if the airplane should be struck by lightning. This action is intended to address the identified unsafe condition.
90-26-07: 90-26-07 BRITISH AEROSPACE: Amendment 39-6834. Docket No. 90-NM-172-AD. Applicability: All Model BAC 1-11 200 and 400 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural capability of the glazing frame and possible rapid decompression of the airplane, accomplish the following: A. For airplanes operating at a maximum cabin differential pressure of 7.5 pounds per square inch (psi): Prior to the accumulation of 20,000 landings on the glazing frame since new, or within 1,600 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 1,600 landings, perform an internal and external visual inspection, or non-destructive testing (NDT) inspection, of the pilot's and co-pilot's direct view (DV) window aperture (flight deck side glazing frame at Pillars B and C), in accordance with the Accomplishment Instructions of BritishAerospace Alert Service Bulletin 53-A-PM5985, Issue 1, dated March 21, 1990. B. For airplanes modified for operation above 7.5 psi to a maximum of 8.2 psi cabin differential pressure: Prior to the accumulation of 14,000 landings on the glazing frame since new, or within 1,100 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 1,100 landings, perform an internal and external visual inspection, or non-destructive testing (NDT) inspection, of the pilot's and co-pilot's DV window aperture (flight deck side glazing frame at Pillars B and C), in accordance with the Accomplishment Instructions of British Aerospace Alert Service Bulletin 53-A-PM5985, Issue 1, dated March 21, 1990. C. If cracks are found during the inspections required by paragraph A. and B. of this AD, prior to further flight, perform an eddy current inspection, in accordance with British Aerospace Alert Service Bulletin 53-A-PM5985, Issue 1, dated March21, 1990; and 1. For cracks equal to or less than 0.2 inch, damage may be blended out in accordance with Table 1 or Table 2 of the service bulletin, as appropriate. 2. All other cracks must be repaired in accordance with the Structural Repair Manual, as specified in Table 1 and Table 2 of the service bulletin, as appropriate; or repaired in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate; or the glazing frame must be replaced with a serviceable part. 3. If blending has been previously accomplished, all cracks must be repaired in accordance with the BAC 1-11 Structural Repair Manual, as specified in Table 1 or Table 2 of the service bulletin, as appropriate; or repaired in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. 4. Following repair or replacement, the inspections specified in paragraphs A. and B. of this AD are still required. D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, PLC, Librarian for Service Bulletins, Dulles International Airport, P.O. Box 17414, Washington, D.C. 20041-0414. These documents may be examined at the FAA,Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6834, AD 90-26-07) becomes effective on January 16, 1991.
93-23-04: 93-23-04 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE AND EUROCOPTER FRANCE: Amendment 39-8738. Docket Number 93-SW-02-AD. Applicability: Model SE 3160, SA 315B, SA 316B, SA 316C, and SA 319B series helicopters equipped with main rotor blades, part number (P/N) LOM3160-100 installed in accordance with Supplemental Type Certificate (STC) No. SH778GL, certificated in any category. Compliance: Required within 25 hours' time-in-service after the effective date of this airworthiness directive (AD), unless accomplished previously. To prevent excessive main rotor vibrations that could result in failure of rotor system components, and subsequent loss of control of the helicopter, accomplish the following: (a) Install an outside air temperature (OAT) and velocity never exceed (VNE) airspeed limitation flip chart placard, P/N LOM3160-151, on top of the instrument panel immediately to the right of the existing VNE placard, using velcro strips as described in Les "Blades"De L'Helicoptere, Ltd. Service Information Letter No. 1-11-92A, dated December 3, 1992. (b) After compliance with paragraph (a) of this AD, operate the helicopter in accordance with the Helicopter Flight Manual Supplement, approved and dated November 25, 1992, that is applicable to helicopters modified in accordance with STC SH778GL. (c) An alternate method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3229 East Spring Street, Long Beach, California 90806-2425. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Manager, Los Angeles Aircraft Certification Office. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished, provided the indicated airspeed is limited to no more than 50 knots. (e) The installation shall be done in accordance with Les "Blades" de l'Helicoptere, Ltd. Service Information Letter No. 1-11-92A, dated December 3, 1992. 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 Les "Blades" de l'Helicoptere, Ltd., 5132 Greencrest Road, La Canada Flintridge, California 91011. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 4400 Blue Mound Road, bldg. 3B, room 158, Fort Worth, Texas 76106; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective February 17, 1994.
2025-13-05: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model H160-B helicopters. This AD was prompted by occurrences of premature in-service degradation of the main rotor swashplate assembly (swashplate) bearing. This AD requires repetitively inspecting the swashplate bearing for the presence of grease, and depending on the inspection results, performing corrective actions. This AD requires performing certain operational checks, downloading and analyzing certain data, and, depending on the results of the operational checks, further corrective actions. This AD also requires repetitively performing one flight under specific conditions. Additionally, this AD requires inspecting grease on the swashplate bearing and, depending on the inspection results, applying a certain grease or replacing the grease. This AD allows installing certain part- numbered swashplate bearings provided certain requirements are met. The FAA is issuing this AD to address the unsafe condition on these products.
77-15-07: 77-15-07 BRITISH AIRCRAFT CORPORATION: Amendment 39-2980. Applies to Viscount Model 744, 745D, and 810 airplanes with aileron control rods, P/N 60903, sheets 185 and 187 and P/N 70103, sheets 329, 445, 447, 449, 451, 453, 455, 457, and 459, certificated in all categories. Compliance is required as indicated, unless already accomplished. To detect corrosion of the aileron control rods and prevent possible aileron failure, accomplish the following: (a) Within the next 30 days after the effective date of this AD or 18 months from the date of the last overhaul of the specified aileron control rods, whichever occurs later, and thereafter at intervals not to exceed 6 months from the last inspection, inspect the aileron control rods for corrosion in accordance with paragraph 2.2 "Accomplishment Instructions" section of issue 2, dated June 2, 1976, British Aircraft Corporation Alert Preliminary Technical Leaflets No. 305 for 700 series airplanes and NO. 174 for 810 series airplanes, or an FAA-approved equivalent. (b) If, during an inspection required by paragraph (a) of this AD, corrosion is found, before further flight, replace the corroded parts with new parts of the same part number. (c) If, during an inspection required by paragraph (a) of this AD, no corrosion is found, rework the aileron control rods in accordance with paragraph 2.2.1 "Accomplishment Instructions" section of issue 2, dated June 2, 1976, British Aircraft Corporation Alert Preliminary Technical Leaflets No. 305 for 700 series airplanes and No. 174 for 810 series airplanes, or an FAA-approved equivalent. (d) The repetitive inspections required by paragraph (a) of this AD may be discontinued upon compliance with paragraph (e) of this AD. (e) Within the next 2 years after the effective date of this AD or at the next aileron control rod overhaul, whichever occurs sooner, remove the affected aileron control rods, disassemble the external sleeves where fitted, and conducta radiographic inspection of the aileron control rod tubes and a visual inspection of the external sleeves in accordance with paragraph 2.4 "Accomplishment Instructions" and paragraph entitled "Radiographic Technique" of issue 2, dated June 2, 1976, British Aircraft Corporation Alert Preliminary Technical Leaflets No. 305 for 700 series airplanes and NO. 174 for 810 series airplanes, or an FAA-approved equivalent. (f) If, during the inspection required by paragraph (e) of this AD, corrosion is found, before further flight, replace the corroded parts with new parts of the same part number. (g) If, during the inspection required by paragraph (e) of this AD, no corrosion is found, rework the aileron control rods in accordance with paragraph 2.4 "Accomplishment Instructions" section of issue 2, dated June 2, 1976, British Aircraft Corporation Alert Preliminary Technical Leaflets No. 305 for 700 series airplanes and No. 174 for 810 series airplanes, or an FAA-approved equivalent.This amendment becomes effective August 22, 1977.
2016-20-01: We are adopting a new airworthiness directive (AD) for Bell Model 427 and Model 429 helicopters. This AD requires replacing certain engine and transmission oil check valves. This AD also prohibits installing the affected check valves on any helicopter. This AD is prompted by a report of several cracked or leaking check valves. These actions are intended to detect and prevent a cracked or leaking check valve which could result in loss of lubrication to the engine or transmission, failure of the engine or transmission, and subsequent loss of control of the helicopter.
2001-12-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2001-12-51 that was sent previously to all known U.S. owners and operators of all Boeing Model 737-800 series airplanes by individual notices. This AD requires revising the Airplane Flight Manual (AFM) to prohibit operating the airplane at speeds in excess of 300 knots indicated airspeed (KIAS) with speedbrakes extended. This AD also provides for optional terminating action for the AFM revision. This action is prompted by a report indicating that severe vibration of the horizontal stabilizer occurred on a Boeing Model 737-800 series airplane. The actions specified by this AD are intended to prevent severe vibration of the elevator and elevator tab assembly following deployment of the speedbrakes, which, if not corrected, could result in severe damage to the horizontal stabilizer, followed by loss of controllability of the airplane.
90-13-01 R1: 90-13-01 R1 BELL HELICOPTER TEXTRON, INC. (BHTI): Amendment 39-8034. Docket No. 90-ASW-35. Final rule of priority letter AD. Applicability: Model 206B, 206L, 206L-1, and 206L-3 helicopters, all serial numbers, certificated in any category. Compliance: Required before further flight, unless already accomplished. To prevent failure of a tail rotor blade assembly, which could result in loss of control of the tail rotor, accomplish the following: (a) Determine the part number and serial number of the tail rotor blade assembly installed on the helicopter. (b) If the tail rotor blade assembly installed is P/N 206-016-201-113 or P/N 206- 016-201-127 and is identified with any serial number listed below, remove and replace the blade assembly with an airworthy part before further flight: T-41361 T-41627 T-41725 T-41737 T-42088 T-42127 T-42157 T-42307 T-42311 T-42316 T-42494 T-42496 T-42497 T-42502 T-42523 T-42534 T-43276 T-44089 T-44120 T-44157 T-44174 Serial Numbers: T-44222 T-44300 T-44638 (c) If one of the tail rotor blade assemblies listed in paragraph (b) is found, report the helicopter registration, serial number, and tail rotor blade assembly serial number to the Manager, Rotorcraft Certification Office, ASW-170, Federal Aviation Administration, Fort Worth, Texas, 76193-0170, telephone (817) 624-5170, within 10 days of the inspection. (Reporting approved by the Office of Management and Budget under OMB No. 2120-0056.) (d) In accordance with FAR Sections 21.197 and 21.199, the helicopter may be flown to a base where the tail rotor blade assembly replacement may be accomplished. NOTE: Any unairworthy blade assemblies found as a result of (b) of this AD should be permanently marked as unairworthy. (e) Record compliance with paragraph (b) of this AD in the AD compliance record and in the maintenance record of the helicopter log book. This record must include the serial numbers of any deficient blade assembly found during compliance with this AD. (f) An alternate method of compliance which provides an equivalent level of safety, may be used if approved by the Manager, Rotorcraft Certification Office, Southwest Region, Federal Aviation Administration, Fort Worth, Texas 76193-0170, telephone (817) 624-5170. This amendment (39-8034, AD 90-13-01 R1) becomes effective on October 17, 1991, as to all persons except those persons to whom it was made immediately effective by Priority Letter AD's 90-13-01 and 90-13-01 R1, issued June 14 and June 22, 1990, which contained this amendment.