Results
2014-15-09: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 Freighter, A330-200 and -300, and A340-200, -300, -500, and -600 series airplanes. This AD was prompted by reassessment of an unsafe condition related to MZ-type spoiler servo-controls (SSCs) that did not remain locked in the retracted position (hydraulic locking function) after manual depressurization of the corresponding hydraulic circuit. This reassessment resulted in the determination that performing repetitive operational tests of all SSC types is necessary. This AD requires repetitive operational tests of the hydraulic locking function on each SSC installed on the blue or yellow hydraulic circuits, and replacing any affected SSC with a serviceable SSC. We are issuing this AD to detect and correct loss of the hydraulic locking function during take-off, which, in combination with one inoperative engine, could result in reduced controllability of the airplane.
2000-01-05: This amendment supersedes an existing airworthiness directive (AD) applicable to certain Boeing Model 747 series airplanes. That AD currently requires repetitive inspections and tests of the thrust reverser control and indication system on each engine, and corrective actions, if necessary; installation of a terminating modification; and repetitive operational checks of that installation, and repair, if necessary. This amendment is prompted by the results of a safety review, which revealed that in-flight deployment of a thrust reverser could result in significant reduction in airplane controllability. The actions specified in this AD are intended to ensure the integrity of the fail-safe features of the thrust reverser system by preventing possible failure modes, which could result in inadvertent deployment of a thrust reverser during flight, and consequent reduced controllability of the airplane. This action identifies certain repetitive operational checks that were inadvertently omitted from the existing AD, and revises certain procedures for accomplishment of the operational checks and certain follow-on corrective actions.
82-19-02: 82-19-02 GENERAL DYNAMICS: Amendment 39-4458. Applies to Model 340, 440, and military models eligible or to be made eligible for civil use under Type Certificate 6A6, and all such model airplanes converted to turbopropeller power, certificated in all categories. Compliance required as indicated unless previously accomplished. To prevent possible loss of a horizontal stabilizer due to failure of the stabilizer attachment fittings (P/Ns 340-8510150 and 340-8510151) caused by fatigue cracks, accomplish the following: A. Within 250 hours time in service or within 90 days from the effective date of this AD, whichever occurs first, unless previously accomplished within the last 450 hours of time in service, conduct a visual inspection of the upper and lower, forward and aft, horizontal stabilizer attachment fitting lugs in accordance with the applicable provisions of paragraph 2 entitled, "Accomplishment Instructions," General Dynamics Convair Division Service Bulletin 640 (340D)55-3A, Revision 1, dated June 12, 1981. If cracks are found, replace with a new part before further flight. B. Within 250 hours time in service or within 90 days from the effective date of this AD, whichever occurs first, unless previously accomplished within the last 1150 hours of time in service, conduct an ultrasonic inspection of the upper and lower, forward and aft, horizontal stabilizer attachment fitting lugs in accordance with the applicable provisions of paragraph 2 entitled, "Accomplishment Instructions" of SB 640 (340D) 55-3A. If cracks are found, replace with a new part before further flight. C. Repeat the visual inspection required by paragraph A of this AD at intervals not to exceed 700 hours time in service from the last such inspection and repeat the ultrasonic inspection required by paragraph B of this AD at intervals not to exceed 1400 hours time in service from the last such inspection. D. Within 10,000 hours time in service from the effective dateof this AD, unless already accomplished, install bushings in the horizontal stabilizer attachment fitting lug holes in accordance with the applicable provisions of paragraph 2 entitled, "Accomplishment Instructions" of SB 640 (340D) 55-3A. Continue to visually inspect at 700 hour intervals per paragraph A and to inspect by ultrasonic procedures at 1400 hour intervals per paragraph B of this AD. E. Within 250 hours time in service or within 90 days from the effective date of this AD, whichever occurs first, unless previously accomplished within the last 450 hours time in service, conduct an internal visual inspection for cracks in the horizontal stabilizer attachment fittings, upper, lower, forward and aft, and associated structure outboard of the lugs and butt rib in the area surrounding the fasteners, in accordance with the applicable provisions of paragraph 2 entitled, "Accomplishment Instructions" of General Dynamics Convair Division Service Bulletin 640 (340D) 55-4, Revision 1, dated March 24, 1982. Inspect for evidence of loose rivets or fasteners in the stabilizer attachment fittings with particular attention given to those just outboard of the butt rib which fasten the upper forward fittings to the spar web and rail. If cracks are found in the stabilizer attachment fittings or associated structure, and/or if loose fasteners are detected in the stabilizer attachment fitting: replace fitting with a new part, repair structure, and/or replace the fasteners, in accordance with the applicable provisions of paragraph 2 entitled, "Accomplishment Instructions" of SB 640 (340D) 55-4 before further flight. F. Within 250 hours time in service or within 90 days from the effective date of this AD, whichever occurs first, unless previously accomplished within the last 1150 hours time in service, conduct an x-ray inspection for cracks in the upper forward and upper aft horizontal stabilizer attachment fittings in the area outboard of the lugs in accordance with the applicable provisions of paragraph 2 entitled, "Accomplishment Instructions" of SB 640 (340D) 55-4. Only the four (4) upper fittings are required to be x-ray inspected as they are the most highly loaded in tension and therefore most susceptible to fatigue cracking. If cracks are found, replace with a new part before further flight. G. Repeat the visual inspection required by paragraph E of this AD at intervals not to exceed 700 hours time in service from the last such inspection and repeat the x-ray inspection required by paragraph F of this AD at intervals not to exceed 1400 hours time in service from the last such inspection. H. Within 10,000 hours time in service from the effective date of this AD, unless already accomplished, replace the first three (3) steel rivets outboard of the butt rib through the two (2) forward upper horizontal stabilizer attachment fittings in accordance with the applicable provisions of paragraph 2 entitled, "Accomplishment Instructions" of SB 640 (340D) 55-4. Continue to visually inspect at 700 hour intervals per paragraph E and x-ray inspect at 1400 hour intervals per paragraph F of this AD. I. Prior to issuance of a Certificate of Airworthiness for military aircraft being converted for civil certification, and prior to further flight for any aircraft that has been out of service for one (1) year or more, the airplane must be inspected in accordance with paragraphs A, B, E, and F of this AD. J. 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 or modifications required by this AD. K. Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Chief, Western Aircraft Certification Field Office, FAA Northwest Mountain Region, Hawthorne, California. 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 General Dynamics, Convair Division, P.O. Box 80877, San Diego, California 92138. These documents also may be examined at FAA Northwest Mountain Region, 17900 Pacific Highway South, C-68966, Seattle, Washington 98168; or Western Aircraft Certification Field Office, 15000 Aviation Boulevard, Hawthorne, California. This supersedes AD 81-16-07, Amendment 39-4180 (46 FR 39431), issued July 24, 1981, and AD 80-11-01, Amendment 39-3775 (45 FR 35309), issued May 13, 1980. This Amendment becomes effective September 16, 1982.
74-10-10: 74-10-10 AIRESEARCH MANUFACTURING COMPANY OF ARIZONA: Amendment 39-1842 as amended by Amendment 39-1868 is further amended by Amendment 39-2253. Applies to Model TPE331-1-151B, -2-201C, -3U-307G, -5-251C, -5-251K and -6-251M engines. Compliance required as indicated. To detect, correct and prevent loosening of the fuel control assembly mounting and support bracket fasteners, accomplish the following: (a) Within the next 25 hours time in service after the effective date of this AD, unless previously accomplished, replace the fuel control assembly support bracket with a new bracket in accordance with instructions contained in paragraph 2.B. of AiResearch Service Bulletin TPE331-73-0028, dated April 29, 1974, or later FAA-approved revisions. (b) Within 100 hours time in service after accomplishment of paragraph (a), above, or 25 hours additional time in service after the effective date of this AD, whichever occurs later, and intervals not to exceed 100 hours time in service thereafter, inspect and retorque the fuel control assembly and support bracket mounting fasteners in accordance with the procedures contained in paragraph 2.C. of AiResearch Service Bulletin TPE331- 73-0028, dated April 29, 1974, or later FAA-approved revisions. (c) Equivalent procedures may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiation data. Note: AiResearch Operating Information Letter OI-331-3, Revision A, dated April 19, 1974, provides pertinent operational information. Flight crews are urged to obtain a copy of this letter and acquaint themselves with the information presented therein. (d) Unless previously accomplished, within the next 1000 hours time in service, or within one year after the effective date of this AD, whichever occurs earlier, the fuel control assembly support bracket attachment lug and fastener must be modified in accordance with AiResearch Service Bulletin TPE331-73-0029, dated May 27, 1974, or later FAA-approved revisions. This change has been incorporated in production engines by model and serial number as defined in paragraph 1.A. of the above referenced service bulletin. (e) The recurring inspection required in (b), above, may be discontinued when the modification prescribed in (d), above, have been accomplished. (f) If the replacement of the support bracket required by paragraph (a), above, has not already been accomplished on the effective date of this amendment to the AD, this modification, when accomplished, must be done in accordance with the instructions contained in paragraph 2.B. of AiResearch Service Bulletin TPE331-73- 0028, Revision 2, dated June 20, 1975, or later FAA-approved revisions. (g) If the replacement of the support bracket required by paragraph (a), above, has already been accomplished, at the next inspection required by paragraph (b), above, install the three (3) washers, P/N 960C10, and bolts, P/N MS21379-14, as required, per paragraph 2.B. of AiResearch Service Bulletin TPE331-73-0028, Revision 2, dated June 20, 1975, or later FAA-approved revisions. (h) If the modification described in paragraph (d), above, has already been accomplished, before exceeding an additional 100 hours time in service after the effective date of this AD, as amended, unless already accomplished; or, when accomplishing paragraph (d), install the three (3) washers, P/N 960C10 and bolts, P/N MS21279-14, as required, per paragraph 2.B. of AiResearch Service Bulletin TPE331-73-0028, Revision 2, dated June 20, 1975, or later FAA-approved revisions. Amendment 39-1842 became effective May 13, 1974. Amendment 39-1868 became effective June 14, 1974. This amendment 39-2253 becomes effective July 11, 1975.
2014-15-17: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant) airplanes. This AD requires revising the airplane flight manual to incorporate temporary revisions that introduce additional limitations for operation of taxi and landing lights. This AD was prompted by a determination that there is a potential for fuel leakage from auxiliary power unit (APU) boost pump component installations in the right-hand landing lights compartment. We are issuing this AD to advise the flightcrew of the limitations for taxi lights and landing lights to prevent heat generated by the taxi lights and landing lights on the ground reaching the auto-ignition temperature of the fuel, which could potentially ignite any fuel or fumes present in the right-hand landing lights compartment.
2014-15-05: We are adopting a new airworthiness directive (AD) for certain Airbus Model A310-304, -322, -324, and -325 airplanes. This AD was prompted by reports of insufficient clearance between the fuel quantity indicator (FQI) probes and the adjacent structure and metallic components in the wing fuel tanks. This AD requires a one-time detailed visual inspection for sufficient clearance between FQI probes on both the left-hand side and right-hand side of the trim horizontal stabilizer and the adjacent structure and metallic components in the fuel tanks, and modification if necessary. We are issuing this AD to detect and correct insufficient clearance, which could lead to electrical arcing in a fuel tank during a lightning strike, which could result in ignition and consequent fire or explosion in the fuel tank.
99-27-15: This amendment adopts a new airworthiness directive (AD) that is applicable to certain General Electric Company GE90 series turbofan engines. This action requires visually inspecting Ps3 and P3B sense lines and full authority digital engine control (FADEC) Ps3 and P3B sensing ports and fittings, cleaning Ps3 and P3B fittings and sensing ports, purging the Ps3 and P3B systems of moisture, and, if necessary, blending of high metal, nicks, burrs, or scratches on Ps3 and P3B fitting threads. This amendment is prompted by seven reports of loss of thrust control due to corruption of the signals to the FADEC caused by water freezing in the Ps3 sensing system. The actions specified in this AD are intended to prevent loss of thrust control due to corruption of the Ps3 and P3B signals to the FADEC which if it occurs in a critical phase of flight, could result in loss of aircraft control.
85-14-02 R2: 85-14-02 R2 GARRETT AUXILIARY POWER DIVISION (FORMERLY GARRETT TURBINE ENGINE COMPANY AND THE AIRESEARCH MANUFACTURING COMPANY OF ARIZONA): Amendment 39-5571 as amended by Amendment 39-6115. \n\n\tApplicability: All GTEC Models GTCP331-200A, -200AC, -200C, -200ER, -250F, -25OH, and -200P Auxiliary Power Units (APU) with fan assembly, Garrett Part Number 3862160-3, -4, or -5, installed; as installed in, but not limited to, Boeing Model 757, and 767 series airplanes, Airbus Model A310 and A300-600 series airplanes, and certain Boeing Model 747 series airplanes with dual units; certificated in any category. \n\n\tCompliance: Required as indicated, unless already accomplished. \n\n\tTo prevent an uncontained APU cooling fan failure, accomplish the following: \n\n\tA.\tUpon removal of the cooling fan assembly, Garrett Part Number 3862160-3 or -4, from an affected GTCP331 series Auxiliary Power Unit (APU) for any reason; or within 1,000 airplane hours time-in-service after August 15, 1985, or prior to September 15, 1985, whichever comes first, for the Boeing Model 757 and 767 series airplanes; and within 1,000 airplane hours time-in-service after April 2, 1987 (the effective date of Amendment 39-5571), for all other airplanes with a GTCP331 series APU installed; incorporate the new fan assembly with the improved fan containment housing as specified in Section 2.A, "Accomplishment Instructions," of Garrett Service Bulletin GTCP331-49-5546, dated August 9, 1984. \n\n\tB.\tUpon removal of the modified cooling fan assembly, Garrett Part Number 3862160-5, from an affected GTCP331 series APU for any reason, or within six (6) months after the effective date of this AD, whichever occurs first, for all airplanes with GTCP331 series APU installed, incorporate the latest improved fan containment configuration in accordance with the Accomplishment Instructions of Garrett Service Bulletin 3862160-49-5716, dated November 19, 1987. \n\n\tC.\tAn 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, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\t\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a maintenance base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Garrett Airline Service Division, A Division of the Allied-Signal Aerospace Company, Technical Publications, Dept. 65-70, P.O. Box 29003, Phoenix, Arizona 85038. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at 3229 East Spring Street, Long Beach, California. \n\n\tAirworthiness Directive 85-14-02, effective August 15, 1985, was revised by Amendment 39-5571 (AD 85-14-02 R1) which was effective April 2, 1987. \n\n\tThis amendment (39-6115, AD 85-14-02 R2) becomes effective February 22, 1989.
2014-15-06: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100B SUD, 747-200B, 747-300, 747-400, and 747-400D series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the upper deck tension ties are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections for cracking in the upper deck tension ties, and related investigative and corrective actions if necessary; tension tie replacement; and post-replacement repetitive inspections for cracking in the upper deck tension ties, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct fatigue cracking of the upper deck tension ties. Severed or disconnected tension ties at multiple locations could result in rapid decompression and loss of structural integrity of the airplane.
46-24-02: 46-24-02 DOUGLAS: (Was Mandatory Note 3 of AD-762-7.) Applies to C-54 Series Aircraft. \n\n\tTo be accomplished not later than next periodic inspection. \n\n\tRevise the magneto wires forward of the firewall in accordance with Douglas Service Bulletin No. C-54-283 dated March 19, 1946. This is necessary to prevent burning of the magneto ground wire conduit which will cause the magneto to short out.
99-27-11: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11 200 and 400 series airplanes, that requires replacing the thrust reverser control unit selector valve with a new or modified valve and inspecting for proper rigging of the thrust reverser cable drums and thrust reverser control unit selector valve detent, and corrective actions, if necessary. This amendment also requires revising the Airplane Flight Manual to provide the flight crew with procedures to address uncontrolled operation of the thrust reverser system. 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 provide the flight crew with procedures in the event of uncommanded deployment of the thrust reverser, and to prevent uncommanded deployment of the thrust reverser in flight or on the ground, which could result in reduced controllability of the airplane.
99-27-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Rolls-Royce Limited Dart series turboprop engines. This amendment requires a one-time visual inspection of the interior of the switch to determine the type of low torque switch, and removal from service of unapproved Klixon low torque switches and replacement with serviceable parts. This amendment is prompted by the discovery of unapproved low torque switches in fleet operation. The actions specified by this AD are intended to prevent possible low torque switch failure, which could result in failure of a propeller to auto-feather following an engine power loss, resulting in possible loss of control of the airplane due to high asymmetric drag.
76-06-01: 76-06-01 SIKORSKY AIRCRAFT: Amendment 39-2541. Applies to S-61L, S-61N, S- 61NM, S-61R, S-62A, S-64A, S-64E, S-64F helicopters certified in all categories, including Military CH-3C, HH-3C, CH-3E, HH-3E, CH-54B helicopters certificated in all categories and equipped with: 1. Model 66WAP200 hydraulic pumps, Serial Numbers 1080 through 1086, 2013, 2015, 2228, 2298, 2670, 2889, and all Serial Numbers with "DO-" prefix, except FAA approved New York Air Brake Company Serial Numbers DO-1 through DO-83. 2. Model 66WAN200 hydraulic pumps, Serial Numbers DO-2110, DO-2117, DO- 2163, DO-2165, DO-2222, DO-2227. Compliance required as indicated. To detect flaking chrome plating from the pistons of Model 66WAP200 hydraulic pump, Serial Numbers 1080 through 1086, 2013, 2015, 2228, 2298, 2670, 2889, and all Serial Numbers with "DO-" prefix, except FAA approved New York Air Brake Company Serial Numbers DO-1 through DO-83; and Model 66WAN200 hydraulic pump, Serial Numbers DO-2110, DO-2117, DO-2163, DO-2165, DO-2222, DO-2227, accomplish the following: a. Before the first flight each day, inspect the filter and filter bowl on the primary, auxiliary, and utility hydraulic manifold for the presence of chrome plating flakes, in accordance with the applicable Maintenance Manual instructions. If flakes are found, remove all pumps, with serial numbers noted above, and replace with FAA approved pumps before further flight. Immediately after replacement of the pump, flush and inspect the hydraulic system in accordance with the applicable Maintenance Manual instructions. NOTE: For the requirements regarding the listing of compliance with this AD in the helicopter's permanent maintenance record, see FAR 91.173. b. Within the next 180 calendar days after the effective date of this AD, replace all pumps, with serial numbers noted above, with FAA approved New York Air Brake Company pumps. c. Advise the FAA, Chief, Engineering and Manufacturing Branch, New EnglandRegion, 12 New England Executive Park, Burlington, Massachusetts 01803, of the serial numbers of unapproved pumps found, the registration and serial number of the helicopter on which they are installed, and the serial nubmers of the replacement pumps. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.) d. After complying with Paragraph (b) of this AD, the inspection required by Paragraph (a) may be discontinued. This amendment becomes effective March 24, 1976.
2014-14-05: We are adopting a new airworthiness directive (AD) for certain Airbus Model A320-111, -211, -212, and -231 airplanes. This AD was prompted by reports of broken struts of the center wing box (CWB). This AD requires a detailed inspection of the CWB struts for cracking, and repair if necessary. We are issuing this AD to detect and correct cracked or broken struts, which could result in strut failure and consequent reduced structural integrity of the airplane.
2010-16-11: We are adopting a new airworthiness directive (AD) for certain Model MD-90-30 airplanes. This AD requires inspecting for corrosion of the retract cylinder support fitting for the main landing gear (MLG) and the mating bore for the support fitting in the MLG trunnion fitting, performing corrective actions if necessary, and replacing cadmium-plated retract cylinder support bushings and bearings. This AD results from reports of the retract cylinder support fitting for the MLG failing during gear extension and subsequently damaging the hydraulic system. We are issuing this AD to prevent corrosion and damage that could compromise the integrity of the retract cylinder support fitting for the MLG, which could adversely affect the airplane's safe landing.
2008-17-06: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Bombardier Model DHC-8-400 series airplanes. The existing AD currently requires revising the Limitations section of the airplane flight manual (AFM) to include procedures for pulling the "HYD PWR XFER'' circuit breaker in the event of the loss of all hydraulic fluid in the No. 1 or No. 2 hydraulic system. This AD requires a revision to the AFM to include additional procedures for ensuring that the "PTU CNTRL'' switch is Normal, the "PTU CNTRL ON'' advisory light is out, and the "HYD PWR XFER'' circuit breaker is pulled in the event of the illumination of the "2 HYD ISO VALVE'' caution light. This AD resulted from low No. 2 hydraulic pressure in-flight, which caused the power transfer unit to overspeed, and the fluid flow within the No. 1 hydraulic system to increase. We are issuing this AD to prevent possible loss of both the No. 1 and No. 2 hydraulic systems, resulting in the potential loss of several functions essential for safe flight and landing of the airplane. DATES: This AD becomes effective September 2, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of September 2, 2008. On July 10, 2007 (72 FR 30968, June 5, 2007), the Director of the Federal Register approved the incorporation by reference of certain other publications. We must receive any comments on this AD by September 15, 2008.
99-26-18: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace (Jetstream) Model 4101 airplanes, that requires repetitive inspections to detect loose or migrated levers of the elevator cable tension regulators, and replacement of the regulator assembly with a new assembly, if necessary. 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 detect and correct loose or migrated regulator levers of the elevator cable tension regulators, which could result in reduced controllability of the airplane.
2014-15-03: We are adopting a new airworthiness directive (AD) for certain serial number Pratt & Whitney Canada Corporation (P&WC) model PW150A turboprop engines. This AD requires rerouting of the igniter cables and installation of new support brackets. This AD was prompted by reports of damage to a high-pressure fuel line, which could result in a high- pressure fuel leak into the engine nacelle. We are issuing this AD to prevent high-pressure fuel leaks, which could cause engine fire and damage to the engine and the airplane.
90-15-07: 90-15-07 SHORT BROTHERS, PLC: Amendment 39-6661. Docket No. 90-NM-137-AD. Applicability: Model SD3-60 series airplanes, equipped with AAR Oklahoma, Inc., freon air conditioning system, installed in accordance with Supplemental Type Certificate (STC) SA3749SW, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent an electrical fire and subsequent loss of essential equipment and/or flight instruments, accomplish the following: A. Within 10 days after the effective date of this AD, inspect electrical panels 1C, 2C, 2D, and 6D to verify that all wiring and terminals are installed in accordance with Advisory Circular (AC) 43.13-1A. If there is evidence of arcing or burnt wires, prior to further flight, replace any defective wires and terminals. B. Within 10 days after the effective date of this AD, accomplish either sub-paragraph 1. or 2., below: 1. Modify the air conditioning system wiring installation and install a new placard on the co-pilot's audio panel, in accordance with AAR Oklahoma, Inc., Service Information Letter 5-90-1, dated June 7, 1990; and revise the Airplane Flight Manual (Document No. 18R008, Freon Air Conditioner Flight Manual Supplement) by incorporating Revision A, dated June 7, 1990; or 2. Deactivate the air conditioning system as follows: a. In Panel 1C, remove wire HH1A-2P (2 gauge wire) connected to the left- hand general service bus; cap and stow this wire. b. In Panel 2C, remove wire HH101A-2P (2 gauge wire) connected to the right-hand general service bus; cap and stow this wire. c. Locate the ground service circuit breakers located in panel 2D or 6D; pull the two 20 amp and the two 2 amp circuit breakers; and install a suitable collar around each circuit breaker shaft to prevent them from being reset. C. 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, Airplane Certification Office, ASW-150, FAA, Southwest Region. NOTE: The request should be submitted directly to the Manager, Airplane Certification Office, ASW-150, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Airplane Certification Office, ASW-150. D. Special flight permits may be issued in accordance with FAR Sections 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 information from the manufacturer may obtain copies upon request to AAR Oklahoma, Inc., 6611 S. Meridian Avenue, P.O. Box 59100, Oklahoma City, Oklahoma 73159. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the FAA, Southwest Region, Airplane Certification Office, 4400 Blue Mound Road, Fort Worth, Texas. This amendment (39-6661, AD 90-15-07) becomes effective on July 31, 1990.
99-24-04 C1: This document corrects information in an existing airworthiness directive (AD) that applies to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes. That AD currently requires a one-time visual inspection to determine whether self-aligning nuts are installed at certain locations of the aft pressure bulkhead tee; and corrective actions, if necessary. This document corrects a typographical error in a service bulletin reference. This correction is necessary to ensure that the appropriate service information is used to accomplish the AD. \n\n\tThe incorporation by reference of certain publications listed in the regulations was approved previously by the Director of the Federal Register as of December 27, 1999. (64 FR 63187, November 19, 1999).
47-49-01: 47-49-01 LOCKHEED: (Was Mandatory Note 34 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2088. Compliance required prior to December 31, 1947. Relocate the rudder trim tab cockpit control unit to comply with provisions of CAR 4b.322 regarding plane and sense of motion of control. (LAC Service Instruction 49/SI-18 covers this same subject.)
47-10-04: 47-10-04 LOCKHEED: (Was Mandatory Note 4 of AD-763-3.) Applies Only to Model 49 Serial Numbers 2021, 2022, 2026, 2027, 2028, 2034, and 2035. Compliance required prior to March 15, 1947. Add 12 grounding jumpers between the engine autosyn transmitters and their support brackets. (LAC Service Bulletin 049/SB-20 covers this same subject.)
2014-13-17: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; 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); and Model A310 series airplanes. This AD was prompted by reports of failures of the right inner tank fuel pump. This AD requires repetitive functional tests of the circuit breakers for the fuel pump power supply, and replacement of certain circuit breakers. We are issuing this AD to detect and correct failure of the circuit breakers for the fuel pump power supply, which could result in a fuel pump overheating, leading to a fuel tank explosion.
99-25-13 C1: This document corrects two typographical errors that appeared in airworthiness directive (AD) 99-25-13 that applies to all Boeing Model 777-200 and -300 series airplanes. That AD currently requires revising the Limitations Section of the Airplane Flight Manual to prohibit the dispatch of certain airplanes under certain conditions. That AD also requires repetitive inspections to ensure correct operation of the backup generators; and, for certain airplanes, a one-time inspection to detect damage of the engine external gearbox; and corrective actions, if necessary. This document corrects incorrect paragraph references. This correction is necessary to ensure that operators accomplish the appropriate requirements of the AD.
99-26-06: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney JT8D-200 series turbofan engines, that requires initial and repetitive fluorescent magnetic particle inspections or fluorescent penetrant inspections of the combustion chamber outer case (CCOC) for cracks, and, if necessary, replacement with serviceable parts. Also, this AD requires a one-time boss material verification, and, if necessary, replacement with serviceable parts. Finally, this AD requires replacement of CCOCs with welded-on bosses with improved, one-piece CCOCs. Installation of the one-piece CCOC constitutes terminating action to the inspection requirements of this AD. This amendment is prompted by a report of an uncontained engine failure caused by fatigue cracks originating at the weld joining the drain boss to the CCOC. The actions specified by this AD are intended to prevent CCOC cracks, which could result in an uncontained engine failure and damage to the airplane.