Results
78-11-05: 78-11-05 CESSNA: Amendment 39-3225. Applies to Model 210M, T210M and P210 (Serial Numbers 21061574 through 21062583, and P2100001 through P2100010); Model 310R and T310R (Serial Numbers 310R0501 through 310R1302, 310R1304 through 310R1315, 310R1317, and 310R1318); Model 340A (Serial Numbers 340A0001 through 340A0458, 340A0460 through 340A0466, 340A0468, and 340A0470 through 340A0483); Model 402B (Serial Numbers 402B1001 through 402B1331 and 402B1333 through 402B1338); Model 404 (Serial Numbers 404-0001 through 404-0218, and 404-0220 through 404-0222); Model 414 and 414A (Serial Numbers 414-0801 through 414-0965, 414A0001 through 414A0032, 414A0034 through 414A0038, and 414A0040 through 414A0047); and Model 421C (Serial Numbers 421C0001 through 421C0479 and 421C0481 through 421C0488) airplanes incorporating ARC Model 400B autopilot installations. To preclude increased flight control forces caused by an autopilot actuator that has failed to disengage when the autopilot is disconnected, unless already accomplished: A) On airplanes not modified in accordance with Cessna Service Letter No. AV78-6, dated March 31, 1978, or later revision, before next flight, disable the Model 400B autopilot: 1. On affected 300 and 400 series airplanes by pulling and banding autopilot computer (COMP.) and actuator (ACT.) circuit breakers; 2. On affected 210 series airplanes by disconnecting the connector at the roll and pitch actuators and securing these connectors to prevent them from interfering with the flight controls; and install a locally fabricated placard in plain view of the pilot indicating "AUTOPILOT INOPERATIVE." NOTE: The autopilot disabling and installation of a locally fabricated placard required by Paragraph A on affected 300 and 400 series airplanes constitutes preventative maintenance and may be performed by persons authorized to perform preventative maintenance under FAR 43. B) Upon accomplishment of the electrical autopilot actuator modification set forth in Cessna Service Letter No. AV78-6, dated March 31, 1978, or later revision, the autopilot may be returned to service and the "AUTOPILOT INOPERATIVE" placard removed. C) Airplanes may be flown to a base where Paragraph A of this AD may be accomplished if the autopilot is not used. D) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective June 5, 1978, to all persons except those to whom it has already been made effective by air mail letter from the FAA dated May 11, 1978.
2025-13-07: The FAA is adopting a new airworthiness directive (AD) for all Safran Helicopter Engines, S.A. (Safran) Model ARRIUS 2B2 engines. This AD was prompted by a manufacturer review of collected data from in- service engines that indicated the preference injector may clog over time caused by fuel coking, which decreases the permeability of the preference injector. This AD requires initial and repetitive non- extinguishing tests for engine flameout and replacement of the preference injector if necessary, a one-time modification (software upgrade) of the electronic engine control unit (EECU) and, for certain engines, repetitive replacements of the preference injector. The FAA is issuing this AD to address the unsafe condition on these products.
2001-14-05: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 737-600, -700, -700C, and -800 series airplanes. This action prohibits installation of repairs of the elevator tab using previously approved repair procedures. This action is necessary to prevent installation of repairs of the elevator tab that are outside allowable limits, which could result in excessive in-flight vibrations of the elevator tab, and consequent loss of controllability of the airplane.
2016-20-13: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and -300 series airplanes; and Model A340-200 and -300 series airplanes. This AD was prompted by a determination that the compliance times for certain post-repair inspections and certain allowable damage limits (ADLs) must be reduced in order to address fatigue. This AD requires identifying any repairs and ADLs used to assess or control any structural damage on certain structural areas, and corrective action if necessary. We are issuing this AD to prevent fatigue damage on primary structure and structural repairs, which could result in reduced structural integrity of the airplane.
2001-13-28: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce Limited, Aero Division-Bristol, S.N.E.C.M.A. (RR) Olympus 593 Mk. 610-14-28 turbofan engines. This action requires replacement of the low-oil pressure (LOP) switch. This amendment is prompted by a report of the failure of the low pressure (LP) and high pressure (HP) rotor thrust bearings due to oil starvation that was caused by the loss of the LOP switch function and resulted in a delayed engine shutdown. The actions specified in this AD are intended to prevent the failure of the LOP switch to indicate an LOP event, which could contribute to uncontained engine failure due to oil starvation in the thrust bearings.
2016-19-14: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318 and A319 series airplanes; Model A320-211, -212, - 214, -231, -232, and -233 airplanes; and Model A321 series airplanes. This AD was prompted by a report of cracks found during maintenance inspections on certain lugs of the 10VU rack side fittings in the cockpit. This AD requires repetitive inspections for cracking of the lugs on the 10VU rack side fittings, and repair of any cracking. We are issuing this AD to prevent reading difficulties of flight-critical information displayed to the flightcrew during a critical phase of flight, such as an approach or takeoff, which could result in loss of airplane control at an altitude insufficient for recovery.
2001-13-25: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-200 and -300 series airplanes, that currently requires repetitive inspections to detect chafing or arcing damage to the cable/wire and fuel tube assemblies on the right-hand side of each engine, and replacement with new components, if necessary. That AD also provides for an optional terminating action for the repetitive inspections required by that AD. This amendment requires accomplishment of the previously optional terminating action. The actions specified by this AD are intended to prevent chafing of the cable/wire bundles against the fuel line, which could result in arcing and a consequent fire or explosion. This action is intended to address the identified unsafe condition.
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.