Results
91-05-12: 91-05-12 AIRBUS INDUSTRIE: Amendment 39-6914. Docket No. 90-NM-158-AD. Applicability: All Model A300 series airplanes, equipped with one or more trimmable horizontal stabilizer (THS) attachment lugs made from 2014 material, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect cracks and corrosion in the THS attachment lugs at Frame 91 and to prevent reduced structural integrity of the horizontal stabilizer attachment, accomplish the following: A. Prior to the accumulation of 1,200 landings, or within 90 days after the effective date of this AD, whichever occurs later, unless previously accomplished within the last 1,200 landings, perform a visual and eddy current inspection of all attachment lugs made from 2014 material, in accordance with Airbus Industrie Service Bulletin A300-53-269, dated December 18, 1989. Repeat these inspections thereafter at intervals not to exceed 1,200 landings. NOTE: Attachment lugs made from 7075 material are not affected by this AD. B. If cracks or corrosion are detected, prior to further flight, repair or replace the affected lugs in accordance with Airbus Industrie Service Bulletin A300-53-269, dated December 18, 1989. C. Installation of Modification No. 7715/D7222, in accordance with Airbus Industrie Service Bulletin A300-53-270, Revision 1, dated February 22, 1990, or Revision 2, dated August 27, 1990, constitutes terminating action for the repetitive inspections required by paragraph A. of this AD. D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6914, AD 91-05-12) becomes effective on April 1, 1991.
97-05-05: 97-05-05 DORNIER: Amendment 39-9949. Docket 96-NM-116-AD. Applicability: Model 328-100 series airplanes having serial numbers 3005 through 3014 inclusive; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the diagonal braces that connect the left and right wings to the fuselage, which could result in unstable movement of the wings and adversely affect the aerodynamic characteristics of the wings, accomplish the following: (a) Within 90 days after the effective date of this AD, perform the actions required by paragraphs (a)(1) and (a)(2) of this AD. (1) Check the clearance between the diagonal braces that connect the left and right wings to the fuselage and the Z-profile of the frame to which the top fairing is attached, in accordance with Dornier Service Bulletin SB-328-53-051, dated August 16, 1994. (i) If the clearance meets or exceeds the minimum limits specified in the service bulletin, no further action is required by paragraph (a)(1) of this AD. (ii) If the clearance is less than the minimum limits specified in the service bulletin, prior to further flight, modify the Z-profile of the frame to which the top fairing is attached, in accordance with the service bulletin. (2) Check each diagonal brace for damage or wear, in accordance with the service bulletin. (i) If no damage or wear is detected, no further action is required by paragraph (a)(2) of this AD. (ii) If any damage or wear is detected, prior to further flight, repair the diagonal brace in accordance with a method approved by the Manager Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The actions shall be done in accordance with Dornier Service Bulletin SB-328-53-051, dated August 16, 1994. 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 Dornier Luftfahrt GmbH, P.O. Box 1103, D-82230 Wessling, Germany. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on April 3, 1997.
2016-19-08: We are adopting a new airworthiness directive (AD) for Viking Air Limited Models DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. III airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and [[Page 64054]] correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as corrosion of the elevator control rod and of the elevator actuating lever on the control column. We are issuing this AD to detect and correct corrosion and/or cracking of the elevator control rod assemblies and the elevator actuating lever, which if not detected and corrected, could cause these components to fail. This failure could result in loss of control.
2010-23-22: We are adopting a new airworthiness directive (AD) for the Eurocopter Model AS332L2 helicopters. This AD results from a mandatory continuing airworthiness information (MCAI) AD issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI AD states that a hard landing occurred during in-flight engine failure (one engine inoperative (OEI)) training. An examination revealed the failure of the right-hand main reduction gear module (module) freewheel unit due to excessive wear on some of its components. The MCAI AD prohibits engine failure OEI training with helicopters on which certain main gearbox (MGB) modules with certain freewheel shafts are installed and mandates the replacement of those modules. The actions are intended to prevent failure of certain freewheel units, loss of power to the main rotor system, and subsequent loss of control of the helicopter.
2001-01-52 R1: This amendment rescinds an existing airworthiness directive (AD) that applies to Bell Helicopter Textron Canada (BHTC) Model 407 helicopters and currently requires, before further flight, imposing never exceed velocity (Vne) restrictions on the helicopter. The requirements of that AD were intended to prevent tail rotor blades from striking the tailboom, separation of the aft section of the tailboom with the tail rotor gearbox and vertical fin, and subsequent loss of control of the helicopter. That AD was prompted by an accident suspected of being the result of a tail rotor strike caused by high airspeed. Since the issuance of that AD, accident investigation findings have not substantiated that a tail rotor strike caused by high airspeed was the cause of the accident. This amendment rescinds that AD. This amendment is prompted by the FAA's determination that the Vne restrictions and accompanying actions imposed by that AD do not correct an unsafe condition.
2016-19-07: We are superseding Airworthiness Directive (AD) 2008-19-08, for all Dassault Aviation Model Falcon 10 airplanes. AD 2008-19-08 required repetitive replacement of the flexible hoses installed in the wing (slat) anti-icing system with new hoses. This new AD requires reducing the life limit of these flexible hoses, which reduces the repetitive replacement intervals. This AD was prompted by additional reports of collapse of the flexible hoses installed in the slat anti- icing systems on airplanes equipped with new, improved hoses. We are issuing this AD to prevent collapse of the flexible hoses in the slat anti-icing system, which could lead to insufficient anti-icing capability and, if icing is encountered in this situation, could result in reduced controllability of the airplane.
2016-18-18: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109A, A109A II, A109C, A109E, A109K2, A109S, and AW109SP helicopters. This AD requires visually inspecting the tail rotor drive shaft assembly (drive shaft) for a crack. This AD was prompted by the discovery of three cracks on the drive shaft of a Model A109S helicopter. The actions of this AD are intended to detect a crack on the drive shaft to prevent failure of the driveshaft, failure of the tail rotor, and subsequent loss of helicopter control.
2005-14-09: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) models RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan engines. This AD requires removal of certain Engine Electronic Controller (EEC) part numbers from service. This AD results from nine reports of loss of engine parameters displayed in the airplane cockpit, with the simultaneous loss of capability to change thrust of the affected engine. We are issuing this AD to prevent loss of airplane control after an aborted takeoff due to asymmetric thrust.
98-09-26: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Dassault Model Falcon 2000 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to provide the flightcrew with procedures for monitoring and properly setting the fuel booster pump pressure; and repetitive visual inspections of the fuel lines to detect fatigue cracking and fuel leakage. This action also requires a one-time inspection of the fuel lines to detect cracking, replacement of any discrepant part with a new part, and installation of new brackets between the pressure switch and the fuel pump of the numbers 1 and 2 engines, which constitutes terminating action for the repetitive inspections and the AFM revision. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent fatigue cracking of the fuel line at the pressure switch pickoff point, which could result in fuel leakage and potential engine fire.
2016-18-14: We are adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R[eacute]gional Model ATR42-500 and Model ATR72-212A airplanes. This AD was prompted by a report indicating that interference occurred between a Type III Emergency Exit door and the surrounding passenger cabin furnishing during a production check. This AD requires measuring the gap between the Type III Emergency Exit doors and certain overhead stowage compartment fittings; removing certain fittings from the overhead stowage compartments and measuring the gap between the Type III Emergency Exit doors and the overhead stowage compartment hooks, if necessary; re-installing or repairing, as applicable, the Type III Emergency Exit doors; and modifying the overhead stowage compartments. We are issuing this AD to prevent interference between a Type III Emergency Exit door and the overhead stowage compartment fitting installed on the rail, which could result in obstructed opening of a Type IIIEmergency Exit door during an emergency evacuation.
2010-23-19: 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: Two cases of main landing gear (MLG) failure to fully extend have been reported. An MLG failing to extend may result in an unsafe asymmetric landing configuration. Preliminary investigation has shown that interference between the MLG door and the MLG fairing seal prevented the MLG door from opening. * * * * * The unsafe condition is possible loss of controllability of the airplane during landing. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
62-05-02: 62-05-02 BRANTLY: Amdt. 402 Part 507 Federal Register February 28, 1962. Applies to All Model B-2 Helicopters With Serial Numbers Prior to 180. Compliance required within the next 25 hours' time in service after the effective date of this directive. To preclude failure of the seals in the engine driven fuel pump due to excessively high temperature conditions in the engine compartment, modify the engine driven fuel pump, Lear- Romec Model RD7790D3, to incorporate high temperature seals in accordance with Brantly Service Bulletin No. 16 and Lear-Romec Service Bulletin No. 3. Reidentify modified units by revising the pump nameplate as follows: (a) Add suffix "-3" to the pump serial number. (b) Change pump model number to "RG7790G". (Brantly Service Bulletin No. 16 and Lear-Romec Service Bulletin No. 3 both cover this same subject.) This directive effective February 28, 1962.
77-14-03: 77-14-03 SOCIETE NATIONAL INDUSTRIELLE AEROSPATIALE (formerly SUD AVIATION): Amendment 39-295l. Applies to Alouette III Helicopter Model SE 3160 and SA 316B, certificated in all categories. Compliance is required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished in accordance with Alouette Service Bulletin No. 05.38, as revised June 14, 1971. To prevent possible binding of the tail rotor directional control, either replace the Houdaille type AV4S2 hydraulic damper with type AV4S3, or modify the type AV4S2 hydraulic damper by incorporating Houdaille Kit 10.338, in accordance with subparagraph 1C(2)(b) of Alouette Service Bulletin 05.38 as revised June 14, 1971, or equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, c/o American Embassy, A.P.O. New York, N.Y. 09667. This amendment becomes effective August 1, 1977.
87-12-09 R1: 87-12-09 R1 SOCATA GROUPE AEROSPATIALE: Amendment 39-5650 as revised by Amendment 39-6224. Applicability: Models TB 20 and TB 21 (Serial Numbers 275 through 700) airplanes certificated in any category. Compliance: Required within the next 50 hours time-in-service (TIS) after the effective date of this AD, and each 100 hours TIS thereafter, unless already accomplished in accordance with the original issuance of AD 87-12-09. To prevent structural failure of the aileron, possible flutter, and loss of control, accomplish the following: (a) Visually inspect the five aileron balance weight attachment rivets for any detectable looseness, and the aileron skin for cracks using the procedures described in paragraph A, SOCATA TB Service Bulletin (S/B) No. 28, dated December 1986. (1) If one or more loose rivets, or cracks extending less than 9/16 inch (15 mm) from the center of the rivet is found, prior to further flight, repair as described in paragraph B of SOCATA TB AircraftS/B No. 28, dated December 1986. (2) If a crack 9/16 inch or longer from the center of the rivet is found, prior to further flight, replace the P/N TB 20.15.001.000 aileron with P/N TB 20.15.001.001 or P/N TB 20.15.001.002 aileron as applicable. (b) The repetitive inspections specified in this AD are no longer required when the ailerons have been repaired or replaced per the actions specified in either paragraph (a)(1), or (a)(2) above. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Brussels Aircraft Certification Office, FAA, AEU-100, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium; Telephone (322) 513.38.30. All persons affected by this directive may obtain copies of document(s) referred to herein upon request to SOCATA Groupe AEROSPATIALE, B.P. 38, 65001 Tarbes, France; Telephone 62.51.73.00 or 62.93.99.45 (for recorder); or the Product Support Manager, U.S., AEROSPATIALE, 2701 Forum Drive, Grand Prairie, Texas, 75053; Telephone (214) 641-3614; or may examine these documents referred to herein at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This AD revises AD 87-12-09, Amendment 39-5650, which became effective on June 26, 1987. This amendment (39-6224, AD 87-12-09 R1) becomes effective on June 25, 1989.
2010-23-11: 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: The manufacturer has informed Transport Canada that a certain number of the resolver stators, which were installed in the angle of attack (AOA) transducers, were not cleaned correctly. This condition can degrade the AOA transducer performance at low temperatures resulting in freezing of the AOA transducer resolver, which may provide inaccurate AOA data to the Stall Protection System (SPS). If not corrected, this condition can result in early or late activation of the stick shaker and/or stick pusher. These conditions could result in reduced ability of the flight crew to maintain a safe flight and landing of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
93-16-12: 93-16-12 BEECH AIRCRAFT CORPORATION: Amendment 39-8670. Docket 92-NM-248-AD. Applicability: Model 400A airplanes, serial numbers RK-1 through RK-41 inclusive; and Model 400T airplanes, serial numbers TT-3 through TT-20 inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent structural failure of the emergency door frame support, which could lead to decompression of the cabin, accomplish the following: (a) Within 200 hours time-in-service after the effective date of this AD, perform an inspection to verify the installation of all rivets in the area adjacent to the upper edge of the emergency exit door, in accordance with Beechcraft Service Bulletin 2482, dated December 1992. (1) If no rivet is missing, no further action is required by this AD. (2) If any rivet is missing, prior to further flight, install a rivet in accordance with the service bulletin. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Wichita Aircraft Certification Office (ACO), FAA, Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. (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 inspection and installation shall be done in accordance with Beechcraft Service Bulletin 2482, dated December 1992. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on October 13, 1993.
2001-12-12: This amendment adopts a new airworthiness directive (AD), applicable to certain CASA Model CN-235 series airplanes, that requires installation of fuselage skin reinforcements in the right and left zones of the fuselage between stations 11232 and 11740 and stringers P7 and P9. The actions specified by this AD are intended to prevent premature fatigue cracking of the fuselage, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
92-11-05: 92-11-05 BRITISH AEROSPACE: Amendment 39-8255. Docket No. 91-NM-281-AD. Applicability: Viscount Model 744 and 745D series airplanes, post-mod D3070 and D3292; and Viscount Model 810 series airplanes, post-mod FG1925 and FG2172, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the engine mount attachment to the wing and wing structure, accomplish the following: (a) Within 100 landings or within 4 months after the effective date of this AD, whichever occurs earlier, visually inspect the upper boom of the wing rib at wing station 257, left and right, for proper fastener edge distance, in accordance with British Aerospace Viscount Alert Preliminary Technical Leaflet (PTL) 192 or PTL 323, both dated January 31, 1990, as applicable. (b) If any discrepancies are detected in the fastener edge distance, prior to further flight, replace the rib boom with a new part, or repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (c) 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. (d) 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. (e) The inspection and replacement shall be done in accordance with British Aerospace Viscount Alert PTL 192, Issue 1, dated January 31, 1990; or British Aerospace Viscount Alert PTL 323, Issue 1, dated January 31, 1990; as applicable. (NOTE: The issue date of PTL 192 and PTL 323 is indicated only on "page 3 of 5" of each document; no other page of these documents is dated.) 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. 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. (f) This amendment becomes effective on July 9, 1992.
99-19-15: This amendment adopts a new airworthiness directive (AD), applicable to certain CASA C-212 and CN-235 series airplanes, that requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This amendment is prompted by reports of inflight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to ensure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
2001-12-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-300 series airplanes, that requires replacement of the hydraulic line between the main hydraulic pump and the pulsation damper in hydraulic system "B" with a new hydraulic flex hose. This action is necessary to prevent cracking in the hydraulic line (due to a production defect), leading to heavy leakage in hydraulic system "B," which could impair the functioning of the airplane's flaps, roll spoilers, inner ground spoilers, and nose wheel steering. This action is intended to address the identified unsafe condition.
2016-18-11: We are adopting a new airworthiness directive (AD) for all Gulfstream Aerospace Corporation Model G-1159, G-1159A, G-1159B, G-IV, and GV airplanes; and certain Model GIV-X and GV-SP airplanes. This AD requires a one-time replacement of the actuator end cap fitting of the main landing gear (MLG) door, and revision of the maintenance or inspection program to establish the life limit of the end cap fitting. This AD was prompted by a report of the failure of the right MLG to extend due to fatigue cracking of the end cap fitting. We are issuing this AD to prevent such cracking, which could result in depletion of the combined (left) and utility hydraulic system fluid and the nitrogen emergency blowdown system, failure of the combined (left) hydraulic system (all phases) to provide adequate hydraulic pressure, and failure of the MLG to extend when commanded.
85-21-02: 85-21-02 GULFSTREAM AEROSPACE: Amendment 39-5140. Applies to Models AA-1 (S/Ns AA1-0001 to AA1-0459), AA-1A (S/N AA1A-0001 to AA1A-0470), AA-1B (S/N AA1B- 0001 to AA1B-0680) and AA-1C (S/N AA1C-0001 to AA1C-0211) airplanes. Compliance: Required within 25 hours time-in-service after the effective date of this AD unless already accomplished by installing parts in accordance with Gulfstream Aerospace Service Bulletin No. 173 dated March 11, 1985. To prevent failure of the seat belt attachment bracket in a minor crash, accomplish the following: (a) Replace the seat belt attachment bracket, (Part Number (P/N) 60152-2) as follows: (1) Take out the seat belts by removing the AN-3 bolts through the end fittings. Discard the bolts and nuts but retain the bushings and washers. (2) Take out the P/N 60152-2 belt attach brackets by removing the two nuts holding them to the floor. Discard the brackets and nuts, but retain the washers. Visually inspect the retainingplates under the fuselage for corrosion and replace if necessary. (3) Install P/N 5102391-1 brackets, using the washers retained in paragraph (a) (2) above and new nuts. Torque the nuts to 20 to 25 inch pounds. (4) Visually inspect the seat belts for fraying or other signs of deterioration and replace any worn or deteriorated belts. (5) Reinstall the seat belts, using NAS623-3-8 bolts, MS20365-1032 nuts and the bushings and washers retained in paragraph (a) (1) above. (b) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (c) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Atlanta Aircraft Certification Office, 1075 Inner Loop Road, College Park, Georgia 30337; telephone (404) 763-7428. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Gulfstream Aerospace Corporation, Post Office Box 2206, Savannah, Georgia 31402-2206, or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. NOTE: Gulfstream Aerospace Corporation Bulletin No. 173, dated March 11, 1985, covers the subject matter of this AD. This amendment becomes effective on October 28, 1985.
2001-12-01: This amendment adopts a new airworthiness directive (AD) that applies to certain The New Piper Aircraft, Inc. (Piper) Models PA-46-310P, PA-46-350P, and PA-46-500TP airplanes. This AD requires you to inspect the left and right inboard flap drive bellcrank assemblies to ensure that the welding is complete and adequate and replace any assembly that has incomplete or inadequate welding. This AD is the result of reports of several instances where the bellcrank in the flap control system failed. The actions specified by this AD are intended to prevent failure of the flap drive bellcrank assemblies caused by incorrect or inadequate welding. Such failure could cause the inability to control the flaps and lead to reduced or loss of control of the airplane.
91-03-05: 91-03-05 AIRSHIP INDUSTRIES: Amendment No. 39-6871; Docket No. 90-CE-50-AD. Applicability: Skyship Model 600 airships (all serial numbers), certificated in any category. Compliance: Required within the next 250 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent ignition control unit failure and subsequent total loss of engine power, accomplish the following: (a) Remove all ignition control units, Part Number (P/N) ASI/L/80 Issue D, MOD 1 or 2, and replace with P/N ASI/L/80 Issue E, MOD 3 ignition control units, as described in Airship Industries Service Bulletin (SB) REF 600-74-314, Revision 1, dated June 5, 1990. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. (c) An alternate method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Aircraft Certification Staff, Europe, Africa and Middle East Office, FAA, 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 Airship Industries Limited, Manager, Technical Publications, Shortstown, Bedford, MK42 OTF, England; or Airship Industries USA, Inc., Engineering Manager, Route 4, Box 109, Elizabeth City, North Carolina 27909; 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 (39-6871, AD 91-03-05) becomes effective on February 28, 1991.
93-25-13: 93-25-13 AIRBUS INDUSTRIE: Amendment 39-8777. Docket 93-NM-130-AD. Applicability: Model A320 series airplanes, manufacturer's serial numbers (MSN) 002 through 051 inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent fatigue cracking, which could lead to reduced structural integrity of the wing, accomplish the following: (a) Prior to the accumulation of 12,000 total landings, or within 2,000 landings after the effective date of this AD, whichever occurs later, accomplish the requirements of paragraphs (a)(1) and (a)(2) of this AD in accordance with Airbus Industrie Service Bulletin A320-57-1060, dated December 8, 1992. (1) Perform a cold expansion of all the attachment holes for the forward pintle fitting of the MLG, except for the holes that are for taper-lok bolts. (2) Perform a cold expansion of the holes at the actuating cylinder anchorage of the MLG. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, 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 cold expansion shall be done in accordance with Airbus Industrie Service Bulletin A320-57-1060, dated December 8, 1992. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1CFR Part 51. Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac, Cedex 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, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on February 14, 1994.