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68-01-02: 68-01-02 VICKERS: Amendment 39-540. Applies to Viscount Models 744, 745D, and 810 Series airplane Compliance required as indicated unless already accomplished. (a) For airplanes with 12,500 or more hours' time in service on the effective date of this AD (1) Comply with paragraph (c) and (d) within the next 250 hours' time in service, and thereafter comply with paragraph (c) at intervals not to exceed 500 hours' time in service from the last inspection performed in accordance with either paragraph (c) or (e); and (2) Comply with paragraph (e) within the next 2,750 hours' time in service, and thereafter at intervals not to exceed 3,000 hours' time in service. (b) For airplanes with less than 12,500 hours' time in service on the effective date of this AD (1) Comply with paragraphs (c) and (d) before the accumulation of 12,750 hours' time in service, and thereafter comply with paragraph (c) at intervals not to exceed 500 hours' time in service from the last inspection performed in accordance with either paragraph (c) or (e); and (2) Comply with paragraph (e) before the accumulation of 15,250 hours' time in service and thereafter at intervals not to exceed 3,000 hours' time in service. (c) Visually inspect the full length of the wear pattern made by the three rollers of the guide assembly at wing station 387 on both the left and right aileron control rod tubes, for surface cracks and holes, in accordance with British Aircraft Corporation (BAC) Preliminary Technical Leaflets (PTLs) No. 266 (700 Series) and No. 129 (810 Series), Issue 1, dated May 30, 1967, or later ARB-approved issue, or an FAA-approved equivalent. (d) Check the roller assembly for correct adjustment between the control rod tube and the third roller, to provide a minimum clearance of .005 inches and a maximum clearance of .010 inches at the least worn part of the wear pattern, in accordance with BAC PTLs No. 266 (700 Series) and No. 129 (810 Series), Issue 1, dated May 30, 1967, or later ARB-approved issue, or an FAA-approved equivalent. (e) Remove the aileron control rod tube located at wing station 387, inspect for cracks using dye penetrant, or an FAA-approved equivalent, and measure the outside diameter across all sections of the wear pattern, in accordance with BAC PTLs No. 266 (700 Series) and No. 129 (810 Series), Issue 1, dated May 30, 1967, or later ARB-approved issue, or an FAA- approved equivalent. (f) If cracks or holes are detected or the tube outside diameter across any section of the wear pattern is less than 1.11 inches in diameter during the inspections required by paragraphs (c) and (e), replace the aileron rod control tube before further flight with a new tube of the same part number. When 12,500 hours' time in service have accumulated on the new replacement tube, begin inspecting the tube in accordance with the inspection requirements of paragraph (a). (g) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. This amendment becomes effective February 8, 1968.
2022-10-03: The FAA is adopting a new airworthiness directive (AD) for certain Viking Air Limited (type certificate previously held by Bombardier, Inc. and de Havilland, Inc.) Model DHC-6-1, DHC-6-100, DHC- 6-200, DHC-6-300, and DHC-6-400 airplanes. This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as loose quadrants on the rudder pedal torque tube and signs of loose rivets or rivet joint wear due to inadequate manufacturing tolerances. This AD requires inspecting the rudder pedal torque tube quadrant for looseness and taking corrective action as necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2013-07-12: We are adopting a new airworthiness directive (AD) for certain BRP-Powertrain GmbH & Co KG Rotax 912 F2; 912 F3; 912 F4; 912 S2; 912 S3; 912 S4; 914 F2; 914 F3; and 914 F4 reciprocating engines. This AD requires a one-time visual inspection for excessive oil deposits or carbon deposits on the No. 2 and No. 3 spark plug center and grounding electrodes, and if found, replacement of the cylinder head before further flight. This AD was prompted by a report of certain No. 2 and No. 3 cylinder heads not manufactured to proper specification. We are issuing this AD to prevent excessive oil consumption, which could result in an in-flight engine shutdown, forced landing, and damage to the airplane.
98-21-24: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney JT8D series turbofan engines, that requires removal, visual inspection, eddy current inspection, repair or replacement of affected compressor disks. This amendment is prompted by reports of improper fixturing during the electrolytic cleaning process of certain compressor disks at a certified repair station, Avial or Greenwich Air Services, currently GE Engine Services Dallas LP, certificate number RA1R445K of Dallas, Texas, that can result in damage to the disks in the form of arc burns. The actions specified by this AD are intended to prevent compressor disk cracking from arc burns in tie rod holes, shielding holes, or pressure balance holes, which could lead to a fracture of a compressor disk, resulting in uncontained release of engine fragments, inflight engine shutdown, and airframe damage.
98-21-32: This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A300, A310, and A300-600 series airplanes, that currently requires performing a ram air turbine (RAT) extension test; removing and disassembling the RAT uplock mechanism; performing an inspection to detect corrosion of the RAT uplock mechanism, and replacement with a new assembly, if necessary; and cleaning all the parts of the RAT control shaft and its bearing component parts. This amendment requires modification of the RAT unlocking control unit, which constitutes terminating action for the repetitive tests and inspections. This amendment also limits the applicability of the existing AD. 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 corrosion of the RAT uplock pin/shaft and needle, which could result in failure of the RAT to deployand consequent loss of emergency hydraulic power to the flight controls in the event that power is lost in both engines.
91-19-06: 91-19-06 I.A.M. RINALDO PIAGGIO S.P.A.: Amendment 39-8033. Docket No. 91-CE-68-AD. Applicability: Model Avante P180 airplanes (serial numbers 1004, 1006, 1007, and 1009 through 1015), certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent movement or separation of the vertical stabilizer caused by failure of the No. 1 spar attachment, which could result in loss of control of the airplane, accomplish the following: (a) Within the next 25 hours time-in-service (TIS) after the effective date of this AD, and thereafter at intervals not to exceed 50 hours TIS until the modification described in paragraphs (a) (2) and (b) of this AD is accomplished, perform an endoscope inspection of the No. 1 spar of the vertical stabilizer attachment for cracks in accordance with the paragraphs (1) through (3) of Part A of 2. ACCOMPLISHMENT INSTRUCTIONS in Piaggio Avante P180 Service Bulletin 80-0008, Revision No. 1, dated June 26,1991. (1) If no cracks are found, prior to further flight, remove the endoscope, install an inspection plastic plug, return the airplane to service, and accomplish the repetitive inspection requirements. NOTE: The modification described in paragraphs (a) (2) and (b) of this AD may be accomplished as terminating action for the inspection requirements of this AD provided that no cracks are found per the inspections required in paragraph (a) of this AD. (2) If cracks are found, prior to further flight, modify the No. 1 spar of the vertical stabilizer spar attachment and install a reinforcement kit in accordance with paragraphs (1) through (15) of Part B of 2. ACCOMPLISHMENT INSTRUCTIONS in Piaggio Avante P180 Service Bulletin 80-0008, Revision No. 1, dated June 26, 1991. (b) Within the next 500 hours TIS after the effective date of this AD, unless already accomplished in accordance with paragraph (a) (2) of this AD, modify the vertical stabilizer spar attachment andinstall a reinforcement kit in accordance with paragraphs (4) through (15) of Part B of 2. ACCOMPLISHMENT INSTRUCTIONS in Piaggio Avante P180 Service Bulletin 80-0008, Revision No. 1, dated June 26, 1991. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Office, Europe, Africa, Middle East office, FAA, c/o American Embassy, 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 Office. (e) The inspections and modification required by this AD shall be done in accordance with Piaggio Avante P180 Service Bulletin 80-0008, Revision No. 1, dated June 26, 1991. 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 I.A.M. Rinaldo Piaggio S.p.A., Via Cibrario, 4, 16154 Genoa, Italy. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, DC. This amendment (39-8033, AD 91-19-06) becomes effective on October 10, 1991.
98-21-23: This amendment adopts a new airworthiness directive (AD) that is applicable to CFM International, S.A. (CFMI) CFM56-7B series turbofan engines. This action supersedes telegraphic AD T98-18-51 that currently requires an inspection of electronic engine control (EEC) fault messages on both engines for the presence of any of the hydromechanical unit (HMU) fuel metering valve (FMV) signal faults identified in the All Operators Wire every 20 flight cycles or 3 calendar days, whichever occurs first, and, if necessary, removing the HMU and replacing it with a serviceable HMU. This action also requires installation of improved EEC software that constitutes terminating action to the repetitive fault message inspections. This amendment is prompted by development of improved EEC software that obviates the need for the repetitive fault message inspections. The actions specified by this AD are intended to prevent an uncommanded engine acceleration event, or inflight engine shutdown.
47-10-15: 47-10-15 LOCKHEED: (Was Mandatory Note 17 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2075. Compliance required prior to recertification. Prior to recertification of all aircraft whose certificates were revoked by direction of the Administrator on July 11, 1946, the following Service Documents must be complied with. LOCKHEED SERVICE BULLETINS: *49/SB-50, revised August 24, 1946 - Revision of Cabin Air Recirculating Fan. 49/SB-58, dated July 22, 1946 - Sealing of Main Landing Gear Doors. 49/SB-86, dated July 18, 1946 - Rerouting of Thermocouple Wires. *49/SB-91, revised September 10, 1946 - Replacements of Electrical Power Feed-Through Studs. *49/SB-93, revised August 11, 1946 - Rework of Exhaust System Ball Joints and Collector Segment. 49/SB-95, dated July 22, 1946 - Insulation of Generator Circuit Breakers. (a) 49/SB-97, revised October 28, 1946 - Sealing, Draining, and Ventilation of Nacelles. 49/SB-98, dated July 26, 1946 - Removal of Engine Filtered Air Components and Plumbing. *49/SB-100, revised August 27, 1946 - Replacement of Fuel Pressure Warning Units. 49/SB-101, revised August 6, 1947 - Modification of Hydraulic Pump Case Drain Lines. 49/SB-102, dated July 23, 1946 - Relocation of Engine Fuel Pump Lines. 49/SB-104, revised July 23, 1946 - Replacement of Windshield Wiper Motor Circuit Fuse. 49/SB-106, dated July 22, 1946 - Replacement of Windshield Heater Wire. 49/SB-109, revised August 22, 1946 - Provision for Vacuum Pump Cooling. 49/SB-113, revised August 6, 1946 - Replacement of Aluminum Electrical Wires and Terminals. 49/SB-114, revised July 31, 1946 - Protection of Electrical Receptacle. 49/SB-115, dated July 23, 1946 - Insulation of Galley Circuit Breaker. 49/SB-116, revised August 2, 1946 - Installation of Generator Field Circuit Breaker (Switch Type). *49/SB-117, revised September 5, 1946 - Insulation of Right Angle Electrical Terminals and Electrical Wiring. 49/SB-118, revised August 10, 1946 - Support of Electrical Wiring in Main Gear Wheel Well. 49/SB-119, revised July 27, 1946 - Sealing of Main Landing Gear Door Hinge. 49/SB-119A, revised August 13, 1946 - Sealing of Main Landing Gear Doors. *49/SB-121, revised September 16, 1946 - Installation of Fire Resistant Hoses and Double Hose Clamps in Nacelle Zones 2 and 3. 49/SB-122, dated July 25, 1946 - Installation of Stainless Steel CO2 Lines. *49/SB-123, revised August 27, 1946 - Replacement of Alcohol Tank, Supply Lines and Vent Line (4-pump system). 49/SB-125, dated June 23, 1946 - Removal of Cargo Compartment Insulation. 49/SB-126, dated July 23, 1946 - Protection of Electrical Junctions and Disconnects at Fire Wall. 49/SB-127, revised July 31, 1946 - Sealing of Cabin Heater Panel. 49/SB-131, revised August 10, 1946 - Rerouting of Drain Line for Deicer Distributor Oil Separator. 49/SB-132, revised August 12, 1946 - Attachment of Electrical Wire Bundles in Forward Passenger Compartment. 49/SB-133, revised July 31, 1946 - Installation of Brass Liners and Double Hose Clamps in Line Between Sump Tank and Propeller Feathering Pump. (a) 49/SB-134, revised October 28, 1946 - Installation of Protective Shield for Engine Torquemeter Plumbing. 49/SB-135, revised August 11, 1946 - Addition of Fuselage Drain Provisions. 49/SB-136, dated July 31, 1946 - Protection of Cabin Heater Flexible Fuel Line. 49/SB-137, dated July 27, 1946 - Addition of Double Hose Clamps on Inboard Fuel Tank Interconnection Line. *49/SB-138, revised September 25, 1946 - Provisions for Increase of CO2 Capacity. *49/SB-155, revised August 28, 1946 - Installation of Copper Wires in Lieu of Aluminum Wires. **49/SB-161, dated August 29, 1946 - Replacement of Alcohol Tank, Supply Lines, and Vent Line 2-pump system). LOCKHEED SERVICE INSTRUCTIONS: *49/SI-22, revised October 10, 1946 - Installation of Engine Plumbing and Electrical Wiring Heat Protective System. *49/SI-41, revised August 16, 1946 - Nacelle Fire Extinguishing System Revisions. 49/SI-105, revised August 7, 1946 - Replacement of Hydraulic Secondary Return Line. LOCKHEED SERVICE INFORMATION LETTERS: *No. 42, revised September 10, 1946 (Canceled). No. 56, dated August 10, 1946 - Periodic Inspection of Vacuum Pump Pressure Hose. No. 57, revised August 15, 1946 - Fuselage Fire Control and Smoke Elimination Procedures. No. 58, revised August 15, 1946 - Combating Belly Cargo Compartment and Fuselage Fires. No. 60, dated August 10, 1946 (Canceled). TWA Engineering Order No. 2762 - Rework of Auxiliary Hydraulic Supply Tank and Discharge Line. *Service Documents identified by an asterisk and by (a) have been revised subsequent to issuance of AD-763 (Special) dated Aug. 21, 1946, as indicated by the later revision date effective in each instance. Aircraft previously recertificated in accordance with AD-763 (Special) should be checked for compliance with these later revisions within next 200 hours of operations. **Service Bulletin 49/SB-161 was not called for in AD-763 (Special), but has subsequently been found necessary, inasmuch as Bulletin 49/SB-123 does not adequately describe changes to 2-pump anti-icing systems. Aircraft incorporating 2-pump anti-icing systems should be checked for conformity with Bulletin 49/SB-161 prior to certification.
98-21-20: This amendment supersedes Airworthiness Directive (AD) 97-04-02, which currently requires installing new exterior placards with operating instructions for the airstair door, cargo door, and emergency exits, as applicable, on certain Raytheon Aircraft Company (Raytheon) Models 1900, 1900C, and 1900D airplanes. This AD requires either modifying the existing exterior placards with door operating instructions installed in accordance with AD 97-04-02; or installing new exterior placards with operating instructions for the airstair door, cargo door, and emergency exits, as applicable. This AD results from reports of the placards (required by AD 97-04-02) covering the atmospheric vents for the cabin door differential pressure lock. The actions specified by this AD are intended to continue to assure that clear and complete operating instructions are visible for opening the airstair door, cargo door, or emergency exits, and to prevent improper operation of the cabin door differential pressure lock caused by the placards blocking the atmospheric vents.
88-15-01: 88-15-01 VALENTIN GmbH: Amendment 39-5958. Applies to Model Taifun 17E powered sailplanes (all serial numbers) certificated in any category. Compliance is required as indicated, unless already accomplished. To prevent the possibility of inadequate warning of an impending stall which could result in the loss of control of the powered sailplane, accomplish the following: (a) Within the next 30 hours time-in-service after the effective date of this AD or by September 15, 1988, whichever occurs first, install a stall warning system in accordance with the installation instructions of Valentin Technical Note (TN) No. 8/818, dated December 10, 1985. (b) 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. (c) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Brussels Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 15 Rue de la Loi B-1040 Brussels, Belgium; telephone 513.38.30 Ext. 2710; or the Manager, New York Aircraft Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581; telephone (516) 791- 6680. (d) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, the Manager, Brussels Aircraft Certification Office, or the Manager, New York Aircraft Certification Office, may adjust the compliance time specified in this AD. Valentin-Flugzeugbau GmbH TN No. 8/818, dated December 10, 1985, and associated installation instructions, identified and described in this document, are incorporated herein and made a part hereof pursuant to 5 U.S.C. 551(a)(1). All persons affected by this directive who have not already received these documents may obtain copies upon request from Valentin- Flugzeugbau GmbH, Flugplatzstrasse 18, D-8728 Hassfurt, Federal Republic of Germany; telephone 0 95 21/47 30; or Morris Aviation, Ltd., P.O. Box 718, Statesboro, Georgia, 30458; telephone (912) 489-8161. These documents may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket 88-ANE-26, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment 39-5958 becomes effective on July 14, 1988.
78-11-03: 78-11-03 PRATT & WHITNEY AIRCRAFT: Amendment 39-3224. Applies to all Pratt & Whitney Aircraft JT3D turbofan engine models. Compliance required not later than March 1, 1980, unless already accomplished. To preclude failures of first stage fan blades due to forging laps, which could result in aircraft damage, perform a one-time blue etch anodize inspection of the blades in accordance with the procedures given in Pratt & Whitney Alert Service Bulletin 4733, dated May 5, 1977, or later FAA approved revision, and Special Instruction 2F-77, dated January 28, 1977, or later FAA approved revision. Fan blades that exhibit blue etch linear indications in the inspection areas shown in Figure 1 of ASB 4733 must be reworked or scrapped in accordance with the forging lap repair limits established in Figure 2 of ASB 4733, dated May 5, 1977, or later FAA approved revision. NOTE: The AD does not change the present fan blade blend limits given in the JT3D engine manual. Themanufacturer'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 Pratt & Whitney Aircraft, Division of United Technologies Corporation, 400 Main Street, East Hartford, Connecticut 06108. These documents may also be examined at Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. This amendment becomes effective August 10, 1978.
2013-05-04: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211-Trent 970-84, RB211-Trent 970B-84, RB211- Trent 972-84, RB211-Trent 972B-84, RB211-Trent 977-84, RB211-Trent 977B-84, and RB211-Trent 980-84 turbofan engines. This AD requires inspection of the intermediate pressure compressor rear stub shaft (IPC RSS) piston ring. This AD was prompted by the failure of an oil pump drive shear neck due to a piston ring seal that was not seated properly in the IPC RSS groove. We are issuing this AD to prevent failure of the oil pump drive shear neck, which could result in loss of oil pressure in one or more engines and reduced control of the airplane.
2010-13-05: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Investigation into a landing gear retraction problem on a production test flight revealed that, during aircraft pressurization and depressurization cycles, the pressure floor in the main landing gear bay deflects to a small extent. This causes relative misalignment between the [alternate-extension system] AES bypass valve, the downlock assist valve and the summing lever which, in turn, can result in damage to and potential failure of the respective clevis attached to one or both of the valves. Such a clevis failure could remain dormant and, in the subsequent event that use of the AES was required, full landing gear extension may not be achievable. * ** * * We are issuing this AD to require actions to correct the unsafe condition on these products.
98-21-17: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires repetitive inspections to detect fatigue cracking of the spring beams on the outboard struts; replacement of cracked spring beams with new or serviceable spring beams; and follow-on actions. That action also provides an optional terminating action for the repetitive inspections. This amendment removes that optional terminating action, and requires a new terminating action. This amendment is prompted by the development of an improved process for manufacturing titanium spring beams that will eliminate the embedded porosity flaws in the existing spring beams from which fatigue cracking can originate. The actions specified by this AD are intended to prevent fatigue cracking of the spring beam, which could result in loss of an outboard strut.
81-04-11: 81-04-11 SHORT BROTHERS LIMITED: Amendment 39-4046. Applies to Model SD3-30 airplanes, certificated in all categories, which have Meansco nose landing gear assembly, P/N 18001, serial numbers MMC-005, MMC-006, MMC-008, MMC-009, MMC-010, MMC- 011, MMC-012, MMC-015, MMC-022, MMC-023, MMC-024, MMC-029, MMC-031 through MMC-051; Menasco nose landing gear down lock mechanism assembly, P/N 18003, serial numbers MMC-003 through MMC-059; or Menasco main landing gear shock strut and link assembly, P/N 17525, serial numbers MMC-011 through MMC-130, installed. Compliance is required as indicated, unless already accomplished. To prevent malfunction or collapse of the landing gear, accomplish the following: (a) Within 100 hours time in service, or prior to the accumulation of 150 landings after the effective date of this AD, whichever occurs later: (1) Visually inspect the nose landing gear assembly, Menasco P/N 18001, for evidence of leaking hydraulic fluid. NOTE: Payspecial attention to the area around the edges of the nameplate. (2) If no leaks are found, make the appropriate log book entry and return to service. (3) If leakage is detected, remove the nameplate and inspect the cylinder, Menasco P/N 18103, for cracks using either the dye penetrant or the eddy current method in accordance with Item 11, "ACCOMPLISHMENT INSTRUCTIONS," of Menasco Mfg. of Canada Ltd. Service Bulletin No. 32-53, Revision 2, dated March 5, 1980, or an FAA-approved equivalent. (b) If as a result of the inspection required in paragraph (a)(3) of this AD: (1) No cracks are found, reinstall nameplate, make the appropriate log book entry, and return the cylinder to service. (2) Cracks are found, before further flight, except as provided in paragraph (g) of this AD, remove the cylinder from service and replace with a new or serviceable cylinder of the same Menasco part number, or an FAA-approved equivalent. NOTE: Short Brothers Limited Service Bulletin No. SD3-32-68, Revision 2, dated April 25, 1980, pertains to the same subject. (c) Within 500 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 600 hours time in service until paragraphs (d) and (e) of this AD are accomplished: (1) For Menasco nose landing gear down lock mechanism, P/N 18003, serial numbers MMC-003 through MMC-059, disassemble, clean, grease the spring and sliding faces, reinstall, and test in accordance with Part A of Item 11, "ACCOMPLISHMENT INSTRUCTION," of Menasco Mfg. of Canada Ltd. Service Bulletin No. 32-45, dated August 27, 1979, or an FAA-approved equivalent. NOTE: Short Brothers Limited Service Bulletin No. SD3-32-66, dated September 25, 1979, refers to this same subject. (2) For Menasco main landing gear shock strut and link assembly P/N 17525, serial numbers MMC-011 through MMC-130, disassemble components P/N 17781, P/N 17782, and P/N 17787; clean, grease spring, sliding spring, and sliding faces, reassemble, and test in accordance with Part A of Item 11, "ACCOMPLISHMENT INSTRUCTIONS," of Menasco Mfg. of Canada Ltd. Service Bulletin No. 32-44, Revision 1, dated January 16, 1980, or an FAA- approved equivalent. NOTE: Short Brothers Limited Service Bulletin No. SD3-32-65, Revision 1, dated March 13, 1980, refers to this same subject. (d) Following rework of the nose landing gear down lock mechanism components to accommodate grease fittings accomplished in accordance with Part B and C of Item 11, "ACCOMPLISHMENT INSTRUCTIONS," of Menasco Mfg. of Canada Ltd. Service Bulletin No. 32-45, dated August 27, 1979, or an FAA-approved equivalent, compliance with paragraph (c)(1) of this AD is no longer required. (e) Following rework of the main landing gear shock strut and link assemblies to accommodate grease fittings accomplished in accordance with Part B and C of Item 11, "ACCOMPLISHMENT INSTRUCTIONS," of Menasco Mfg. of Canada Ltd. ServiceBulletin No. 32-44, Revision 1, dated January 16, 1980, or an FAA-approved equivalent, compliance with paragraph (c)(2) of this AD is no longer required. (f) Grease nose landing gear down lock mechanism and main landing gear shock strut and link assemblies reworked in accordance with paragraphs (d) and (e) of this AD every 600 hours time in service thereafter. (g) The airplane may be flown in accordance with FAR Sections 21.197 and 21.199 to a base where the maintenance can be performed. (h) Upon submission of substantiating data, through an FAA Aviation Safety Inspector, the Chief, Aircraft Certification Staff, Europe, Africa and Middle East Office, may adjust the inspection intervals. (i) If an equivalent means of compliance is used in complying with paragraphs (a), (c), (d) or (e) of this AD, that equivalent means must be approved by the Chief, Aircraft Certification Staff, AEU-100, FAA, Europe, Africa and Middle East Office, c/o American Embassy, Brussels, Belgium. This amendment becomes effective March 3, 1981.
87-05-02: 87-05-02 BEECH: Amendment 39-5553. Applies to Models 1900 and 1900C (all serial numbers) airplanes equipped with optional "chip detect" annunciators, certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To preclude the reduction of the attention-getting qualities and enhance pilot awareness of the cockpit caution and warning annunciators, accomplish the following: (a) Revise Beech Models 1900/1900C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual (POH/AFM), Part Number (P/N) 114-590021-3, by incorporating Revision A3, dated February 1986. (b) An alternate means of compliance with paragraph (a) of the AD is as follows: (1) Using pen-and-ink or other permanent means, delete the words "at the next point where maintenance can be performed" from the procedure entitled ILLUMINATION OF "CHIP DETECT" ANNUNCIATOR on page 3A-6. (2) In place of the words deleted in step (1), insert the words "prior to the next takeoff". (c) The requirements of paragraph (a) or (b) of this AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations (FAR) on any airplane owned or operated by him. The person accomplishing these actions must make the appropriate aircraft maintenance record entry as prescribed by FAR 91.173. (d) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209; Telephone (316) 946-4400. All persons affected by this directive may obtain copies of the documents applicable to this AD upon request to Beech Aircraft Corporation, 9709 East Central, P.O. Box 85, Wichita, Kansas 67201; or the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective March 23, 1987.
2013-07-01: We are adopting a new airworthiness directive (AD) for Diamond Aircraft Industries GmbH Models DA 42, DA 42 M-NG, and DA 42NG airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as overextension of the main landing gear (MLG) shock absorber that could lead to the MLG jamming in the gear bay and result in damage to the aircraft or occupant injury. We are issuing this AD to require actions to address the unsafe condition on these products.
98-14-02: This document makes a correction to Airworthiness Directive (AD) 98-14-02 applicable to Pratt & Whitney Canada (PWC) PW100 series turboprop engines that was published in the Federal Register on July 1, 1998 (63 FR 35794). PWC Service Bulletin (SB) No. 21077, Revision 8, is dated incorrectly. This document corrects the dating of that SB. In all other respects, the original document remains the same.
80-21-51: 80-21-51 BRITISH AEROSPACE (FORMERLY VICKERS-ARMSTRONG AIRCRAFT LIMITED): Amendment 39-4205. Applies to all Viscount Model 744, 745D and 810 airplanes, certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent failure of the elevator control system, accomplish the following: (a) Before further flight, determine the time in service on spigot fitting P/N 70120-367. Replace each spigot fitting with a serviceable part in accordance with the following schedule, and thereafter continue to replace the spigot fittings at intervals not to exceed 3,000 hours time in service: (1) If spigot fitting has 12,000 hours or more time in service since new, or the total time in service is unknown, replace before further flight. (2) If spigot fitting has less than 12,000 but more than 3,000 hours time in service on the effective date of this AD: (i) Before further flight, unless already accomplished, inspect forcracks using the magnetic flaw detection saturation method and 5X magnification in accordance with item 4 of the British Aerospace Weybridge Bristol Division Campaign Wire REF SS/749/V, dated September 5, 1980, or an FAA-approved equivalent. If any crack or cracks are found, replace spigot fitting before further flight. (ii) If no cracks are found, replace spigot fitting within 300 hours time in service after the effective date of this AD, or prior to the accumulation of 12,000 hours time in service, whichever occurs first, except as provided in paragraph (a)(4) of this AD. (3) If spigot fitting has 3,000 hours time in service or less on the effective date of this AD, replace prior to the accumulation of 3,000 hours time in service, or within 300 hours time in service, whichever occurs later. (4) Spigot fittings with more than 3,000 hours time in service on the effective date of this AD must be replaced prior to September 15, 1981. (b) Before further flight, unless already accomplished, inspect the spring servo tab operating mechanism for security by examining the inboard tab on the LH elevator and its attachment to the elevator together with connecting linkage through to "bellcrank" lever, P/N 70133-567, and its associated spigot fitting, P/N 70120-367, on the inner end of the LH elevator torque tube. In addition, the control circuit must be checked from this point through to the adjustment spring located on the inner end of the subject torque tube. If defects are found, repair as necessary and return to service. (c) When replacing spigot fitting, P/N 70120-367, insure that the twin center bearing assembly in the control lever, P/N 70133-567, is free to move. If defects are found, repair as necessary and return to service. (d) For Viscount Type 810, prior to the accumulation of 10,000 flights or within 50 hours time in service after the effective date of this AD, whichever occurs later, inspect the right and left handtailplane top root end fittings, P/N's 81018-227 and 81018-228, in accordance with British Aerospace Technique AL/MAT/3713, dated September 26, 1980, or an FAA-approved equivalent. Cracked fittings must be replaced prior to further flight. (e) If an FAA-approved equivalent is used in complying with this AD, that equivalent must be approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office. Report defects found to the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Office, c/o American Embassy, Brussels, Belgium. Reporting approved by the Office of Management and Budget OMB No. 04/R0174. 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 British Aerospace, Aircraft Group, Weybridge-Bristol Division, Brooklands Road, Weybridge, Surrey, England KT13 OSF. These documents may be examined at FAA Headquarters, Room 916, 800 Independence Avenue, SW., Washington, D.C. 20591. This amendment becomes effective August 27, 1981, as to all persons except those persons to whom it was made immediately effective by telegraphic AD T80-21-51, issued October 2, 1980, which contained this amendment.
81-24-03: 81-24-03 GULFSTREAM AMERICAN CORPORATION: Amendment 39-4257. Applies to Model AA5, Serial Numbers AA5-0641 through AA5-0834; Model AA5A, Serial Numbers AA5A-0001 through AA5A-0900; Model AA5B, Serial Numbers AA5B-0001 through AA5B- 1323, airplanes certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent an engine power loss, accomplish the following: PART I For Model AA5 Serial Numbers AA5-0641 through AA5-0834; Model AA5A Serial Numbers AA5A-0001 through AA5A-0900, accomplish the following: For airplanes with 400 or more hours time in service on the effective date of this AD, comply with paragraphs (a) and (c) within 25 hours time in service from the effective date of this AD. Thereafter comply with paragraph (a) at intervals not to exceed 25 hours time in service from the last inspection until paragraph (b) has been accomplished and with paragraph (d) within the next 50 hours time in service from the effectivedate of this AD. For airplanes with less than 400 hours time in service on the effective date of this AD, comply with paragraph (d) within the next 50 hours time in service from the effective date of this AD and with paragraphs (a) and (c) prior to the accumulation of 425 hours total time in service. Thereafter comply with paragraph (a) at intervals not to exceed 25 hours time in service from the last inspection until paragraph (b) has been accomplished. (a) Inspect both forward and aft carburetor airbox screens (Gulfstream American P/N 5503006-9) to determine if any of the wires are broken. (1) If there are less than five broken wires per screen, inspect the induction system and the carburetor throat for filter material and correct, if necessary. Comply with paragraph (b) within 50 hours time in service from the first inspection under this paragraph. (2) If there are five or more broken wires per screen, inspect the induction system and the carburetor throat forfilter material and correct, if necessary. Comply with paragraph (b) before further flight. (b) Install the improved filter retention screens (Gulfstream American P/N 5503006- 20). (c) Inspect the carburetor airbox for damage and the carburetor air filter for deterioration. (1) If the airbox is found to have cracks, or loose or missing fasteners, replace or repair, as necessary, before further flight. (2) If the air filter is found to be separated and/or deteriorated, replace with an appropriate serviceable filter before further flight. (d) Within the next 50 hours time in service from the effective date of the AD, install a permanent warning placard, Gulfstream P/N 5503014, on exterior of the airbox which reads: "WARNING Air Filter deterioration can cause engine power loss. Consult Aircraft Maintenance Manual for air filter servicing and replacement requirements." Part II For Model AA5B, Serial Numbers AA5B-0001 through AA5B-1323, accomplishthe following: For airplanes with 400 or more hours time in service on the effective date of this AD, comply with paragraph (a) within 25 hours time in service from the effective date of this AD. For airplanes with less time than 400 hours time in service on the effective date of this AD, comply with paragraph (a) prior to the accumulation of 425 hours time in service. (a) Inspect the carburetor airbox for damage and the carburetor air filter for deterioration. (1) If the airbox is found to have cracks, or loose or missing fasteners, replace or repair, as necessary, before further flight. (2) If the air filter is found to be separated and/or deteriorated, replace with an appropriate serviceable filter before further flight. (b) Within the next 50 hours time in service from the effective date of the AD, install a permanent warning placard, Gulfstream P/N 5503014, on exterior of the airbox which reads: "WARNING Air Filter deterioration can cause enginepower loss. Consult Aircraft Maintenance Manual for air filter servicing and replacement requirements." An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. The airplane may be flown in accordance with FAR 21.197 and FAR 21.199 to a base where these repairs and/or replacements can be performed. Make the appropriate maintenance record entry for Parts I and II. Gulfstream American Service Bulletin No. 170 dated July 23, 1981, pertains to Part I of this AD. Gulfstream American Service Letter No. 81-1 dated October 9, 1981, pertains to Part II of this AD. This amendment becomes effective November 16, 1981.
98-21-12: This amendment adopts a new airworthiness directive (AD) that is applicable to McDonnell Douglas Helicopter Systems (MDHS) Model 369D, 369E, 369FF, 500N, AH-6 and MH-6 helicopters. This action requires visual inspections of the overrunning clutch retainer, carrier, housing, and pin for wear from spinning of the bearing outer race. This amendment is prompted by a report of inflight vibrations and subsequent investigations of three other overrunning clutches, which indicated wear of the bearing carrier due to spinning of the bearing outer race. The actions specified in this AD are intended to detect wear of other clutch components, excessive vibration which could lead to failure of the overrunning clutch, wear on the bearing carrier, and subsequent loss of power to the helicopter rotor drive system.
98-21-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-200 and -300 series airplanes, that requires repetitive inspections for cracking of the lower skin panels of the outer wings; and repair, if necessary. This amendment also requires modification of the panels and a follow-on inspection to detect cracking of the modified areas, which constitute terminating action for the repetitive inspections. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fatigue cracking of the lower skin panels of the outer wings, and consequent reduced structural integrity of the airplane.
2013-06-06: We are adopting a new airworthiness directive (AD) for General Electric Company (GE) CF34-8C and CF34-8E turbofan engines with certain part numbers (P/N) of operability bleed valves (OBV) installed. This AD was prompted by three failure events of ring lock fuel fittings on the OBV. Two of those events led to an engine fire. This AD requires the affected OBVs be removed from service and replaced with OBVs eligible for installation. We are issuing this AD to prevent failure of OBV ring lock fuel fittings, engine fuel leakage, uncontrolled fire, and damage to the airplane.
91-11-05: 91-11-05 GENERAL ELECTRIC COMPANY: Amendment 39-7001. Docket No. 90-ANE- 35. Applicability: General Electric Company (GE) CF6-80A and CF6-80C2 series engines installed on, but not limited to, Airbus A300 and A310; and Boeing 747 and 767 aircraft. Compliance: Required as indicated, unless already accomplished. To prevent aborted takeoff and uncontained engine failure, accomplish the following: (a) Ultrasonic inspect the inertia weld of affected high pressure compressor rotor (HPCR) stages 11-14 spool-shafts at the next engine shop visit after the effective date of this AD but no later than 5,000 cycles in service (CIS) after the effective date of this AD, according to the following: (1) Inspect CF6-80A HPCR stages 11-14 spool-shafts, Part Numbers (P/N) 9225M37G11, 9225M37G14, 9225M37G16, 9225M37G18, 9225M37G19, 9225M37G20, 9225M37G21, and 1509M71G01, in accordance with the Accomplishment Instructions in GE CF6-80A Service Bulletin (SB) 72-531, Revision 2, dated May 18, 1990. (2) Inspect CF6-80C2 HPCR stages 11-14 spool-shafts, P/N 9380M30G07, 9380M30G08, 9380M30G09, 9380M30G10, 1531M21G01, 1509M71G02, 1509M71G03, 1509M71G04, 1509M71G05, and 1509M71G06, in accordance with the Accomplishment Instructions in GE CF6-80C2 SB 72-314, Revision 2, dated June 20, 1990. (3) Remove from service prior to further flight and replace with serviceable parts, HPCR stages 11-14 spool-shafts with ultrasonic indications greater than or equal to 50 percent full-screen height. (4) For the purpose of this AD, an engine shop visit is defined as the induction of the engine into a shop where the subsequent maintenance entails removal of the high pressure turbine module. (5) For the purpose of this AD, definition of ultrasonic indication is provided in GE CF6-80A SB 72-531, Revision 2, dated May 18, 1990, and GE CF6-80C2 SB 72-314, Revision 2, dated June 20, 1990, for the CF6-80A and CF6-80C2 engine models, respectively. (b) Aircraft may be ferried inaccordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (c) Upon submission of substantiating data by an owner or operator through an FAA Inspector (maintenance, avionics, or operations, as appropriate) an alternate method of compliance with the requirements of this AD or adjustments to the compliance times specified in this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803-5299. The ultrasonic inspections shall be done in accordance with the following GE documents: DOCUMENT PAGE NO. ISSUE/REVISION DATE GE CF6-80A 2-12, 15, 17-27, Rev. 1 4/3/89 SB 72-531 30, 31 1, 13, 14, 16, 28, 29 Rev. 2 5/18/90 GE CF6-80C2 2-12, 15, 17-27, Rev. 1 4/19/89 SB 72-314 30, 31 1, 13, 14, 16, 28, 29 Rev. 2 6/20/90 This incorporation by reference was approved bythe Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from General Electric Aircraft Engines, CF6 Distribution Clerk, Room 132, 111 Merchant Street, Cincinnati, Ohio 45246. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, Room 311, 12 New England Executive Park, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, D.C. This amendment (39-7001, AD 91-11-05) becomes effective on July 5, 1991.
92-12-06: 92-12-06 AIRBUS INDUSTRIE: Amendment 39-8267. Docket No. 91-NM-13-AD. Applicability: Model A310, A320, and A300-600 series airplanes; as listed in Airbus Industrie Service Bulletins A310-35-2002, Revision 2, dated April 30, 1991; A320-35-1002, Revision 1, dated December 3, 1990; and A300-35-6001, Revision 2, dated April 30, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent passengers from being unable to receive oxygen during an emergency situation, accomplish the following: (a) Within 90 days after the effective date of this AD, replace Puritan Bennett passenger emergency oxygen container door latch seals with modified seals, and test all units for correct operation, in accordance with Airbus Industrie Service Bulletins A310-35-2002, Revision 2, dated April 30, 1991 (for the Model A310); A320 35-1002, Revision 1, dated December 3, 1990 (for the Model A320); and A300-35-6001, Revision 2, dated April 30, 1991 (for the Model A300-600). (b) An alternative method 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. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The replacement and testing shall be done in accordance with Airbus Industrie Service Bulletins A310-35-2002, Revision 2, dated April 30, 1991 (for the Model A310); A320- 35-1002, Revision 1, dated December 3, 1990 (for the Model A320); and A300-35-6001, Revision 2, dated April 30, 1991 (for the Model A300-600); as applicable. Airbus Industrie Service Bulletin A320-35-1002, Revision 1, dated December 3, 1990 contains the following list of effective pages: Page Number Revision Level Date 1, 3-9 1 December 3, 1990 2 (removed) 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (e) This amendment becomes effective on July 31, 1992.