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89-07-04: 89-07-04 SAAB-SCANIA: Amendment 39-6160. Applicability: Model SF-340A series airplanes, serial numbers 003 through 106, certificated in any category, except those airplanes equipped with mechanical float switches. Compliance: Required as indicated below, unless previously accomplished. To prevent the potential for arcing in the fuel tanks should a lightning strike occur, accomplish the following: A. Within 30 days after the effective date of this AD, conduct an inspection to determine if the jumper assemblies are fitted to the midlevel and tank full optical sensors, in accordance with SAAB Service Bulletin SF340-28- 006, dated March 23, 1988. B. If optical sensor jumper assemblies have not been installed, prior to further flight, install jumper assemblies and check resistance, in accordance with SAAB Service Bulletin SF340- 28-006, dated March 23, 1988. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptablelevel of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments 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 airplanes to a base for the accomplishment of inspections and/or modifications required by 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 SAAB-Scania Aircraft Division, Product Support, S-58188, Linkoping, Sweden. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment, (39-6160, AD 89-07-04) becomes effective April 26, 1989.
2002-22-16: This amendment supersedes an existing airworthiness directive (AD) for the specified Eurocopter France (ECF) helicopters. The existing AD requires visually inspecting the four engine exhaust pipe ejector (ejector) attachment lugs (lugs), the starter-generator (S-G) attachment flange (flange) and attachment half-clamps (half-clamps) for cracks, and the S-G shaft for radial play. This amendment will retain the current requirements except will not require measuring the radial play. This amendment will also require measuring each S-G engine clamp torque and vibration level and recording the S-G vibration level on a component history card or equivalent record. If the S-G vibration level is equal to or higher than 0.5 inches per second (IPS), this superseding AD requires repairing or replacing the S-G, as necessary. This amendment is prompted by additional cases of S-G damage and the need for additional corrective actions. The actions specified by this AD are intended to prevent excessive S-G vibration, which could lead to separation of an ejector, impact with the main or tail rotor, and subsequent loss of control of the helicopter.
72-03-06: 72-03-06 ALLISON: Amdt. 39-1390. Applies to Models 250-B15A, 250-B15E, 250-B15G, 250-B17, 250-C10B, 250-C10D, 250-C18, 250-C18A, 250-C18B, 250-C18C, 250-C19 and 250-C20 engines. Compliance: Required as indicated, unless already accomplished. To ensure adequate life limit margin for Allison P/Ns 6857912 and 6871872 second stage turbine wheels, accomplish the following: A) Within the next 50 hours' time in service after the effective date of this AD, remove from service all P/Ns 6857912 and 6871872 second stage stabilizer trim and to maintain stabilizer control capability, accomplish the following: (a) For airplanes incorporating stabilizer trim modules having over 1500 hours' time in service. B) Prior to their exceeding 1550 hours' time in service, remove from service all P/Ns 6857912 and 6871872 second stage turbine wheels having 1500 hours or less time in service on the effective date of this AD. Allison Commercial Service Letter No. 250CSL-10, dated December 9, 1971, pertains to this subject. This amendment becomes effective February 8, 1972.
2016-01-03: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 Freighter, A330-200, A330-300, A340-200, and A340-300 series airplanes. This AD was prompted by reports that the inner bore of some main landing gear (MLG) unit bogie beams were insufficiently re-protected against corrosion after inspection or maintenance actions were accomplished. This AD requires for certain MLG units, determining which revision of the component maintenance manual (CMM) was used to accomplish the most recent MLG unit overhaul; a detailed inspection for missing or damaged paint, and if necessary, a detailed inspection of the cadmium plating for discrepancies, measurement of the depth of the cadmium plating, a general visual inspection of the base metal for corrosion or damage, a detailed inspection of repaired areas for cracking or corrosion; and corrective actions if necessary. We are issuing this AD to detect and correct corrosion in the bore of each MLG unit bogie beam, which could result in collapse of a MLG unit, and subsequent damage to the airplane and injury to occupants.
88-25-11: 88-25-11 MOONEY: Amendment 39-6085. Applicability: Models M20J (Serial Numbers 24-0084, 24-0378 through 24-1645, and 24-3000 through 24-3056) and M20K (Serial Numbers 25-0001 through 25-1160) certificated in any category. Compliance: Required within the next 25 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent in-flight opening of the baggage door, accomplish the following: (a) Modify the auxiliary exit mechanism in the baggage door, install a placard, and incorporate the Pilots Operating Handbook/Airplane Flight Manual Supplement as specified in Mooney Aircraft Corporation Service Bulletin No. M20-239, dated September 28, 1988, and operate the airplane in accordance with these instructions. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Airplane Certification Branch, FAA, Fort Worth, Texas 76193-0150. All persons affected by this directive may obtain copies of the document referred to herein upon request to the Mooney Aircraft Corporation, P. O. Box 72, Kerrville, Texas 78029; or may examine this document at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment (39-6085, AD 88-25-11) becomes effective on January 5, 1989.
89-07-02: 89-07-02 McDONNELL DOUGLAS: Amendment 39-6158. \n\n\tApplicability: McDonnell Douglas Model DC-8 series airplanes, equipped with rudder drive torque tube crank assembly, P/N 5647102-1 or -501, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent the loss of directional control of the airplane in critical flight regimes due to fatigue failure of the rudder drive torque tube crank assembly, accomplish the following: \n\n\tA.\tWithin the next 1,000 hours time-in-service after the effective date of this AD, unless already accomplished within the last 2,600 hours time-in-service, conduct an eddy current inspection of the rudder drive torque tube crank assembly, in accordance with the accomplishment instructions in McDonnell Douglas DC-8 Service Bulletin 27-268, dated February 9, 1988, or equivalent inspection technique approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB.\tIf no cracks are found, repeat the inspection in accordance with paragraph A. of this AD at intervals not to exceed 3,600 hours time-in-service. \n\n\tC.\tIf cracks are found, accomplish one of the following: \n\n\t\t1.\tReplace the cracked rudder drive crank assembly (P/N 5647102-1 or -501) with P/N 5647102-501, in accordance with McDonnell Douglas DC-8 Service Bulletin 27-268, dated February 9, 1988, and repeat inspections in accordance with paragraph B. of this AD; or \n\n\t\t2.\tReplace the rudder drive crank assembly with P/N 5647102-503 in accordance with McDonnell Douglas DC-8 Service Bulletin 27-268, dated February 9, 1988. \n\n\tD.\tReplacement of the rudder drive crank assembly with P/N 5647102-503, in accordance with McDonnell Douglas DC-8 Service Bulletin 27-268, dated February 9, 1988, constitutes terminating action for the repetitive inspections required by this AD. \n\n\tE.\tAlternate 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\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tF.\tSpecial 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. \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 McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publications, C1-L00 (54-60). 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\tThis amendment (39-6158, AD 89-07-02) becomes effective April 26, 1989.
73-11-08: 73-11-08 SIAI-MARCHETTI: Amdt. 39-1648. Applies to SIAI Marchetti Model S.205 airplanes, Serial Numbers 001, 002, 003, 101 through 399, and 4-101 through 4-212. Compliance is required within the next 100 hours' time in service after the effective date of this AD unless already accomplished. To provide a means for periodic lubrication of the main and nose landing gear torque link pins and bolts accomplish the following in accordance with SIAI Marchetti Service Bulletin No. SB 205B35 dated March 13, 1972, or an FAA-approved equivalent: (a) Remove the existing main and nose landing gear center torque link hinge bolts and main and nose landing gear upper and lower torque link to landing gear pins. (b) Clean the bushings by removing rust residue; install the following bolts, pins, and grease fittings in the locations indicated, and check the fit between the pins and bushings. (1) Install new pins with grease fittings, P/N 205-9-043-01, in the upper and lower main gear torque link to main gear leg connections with the grease fittings pointing toward the airplane centerline. (2) Install new bolts with grease fittings, P/N 205-9-063-01, in the main landing gear upper to lower torque link connections. (3) Install new pins, P/N 205-9-137-11 and P/N 205-9-138-11, in the upper and lower torque link to nose landing gear leg connections, respectively, and install grease fittings, P/N 205-9-154-01. (4) Install a new bolt with grease fitting, P/N 205-9-153-01, in the nose landing gear upper to lower torque link connection. This amendment becomes effective June 22, 1973.
2016-01-06: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB139 and AW139 helicopters. This AD requires inspecting each full ice protection system tail rotor slip ring (slip ring) for chatter marks, witness marks, or scoring, and determining the depth of each mounting hole. Based on the findings from the inspection, this AD requires either re-identifying the slip ring or replacing the slip ring. This AD is prompted by two incidents of the slip ring body separating from the supporting flange due to improper torque. These actions are intended to prevent separation of the mounting flange from the slip ring body and subsequent loss of control of the helicopter.
85-06-05: 85-06-05 MCDONNELL DOUGLAS: Amendment 39-5018. Applies to McDonnell Douglas Model DC-9 and C-9 (Military) airplanes, certificated in all categories, equipped with Sundstrand P/N 26340061-04 battery charger. Compliance required as indicated, unless previously accomplished. \n\n\tTo prevent the potential for a localized fire and the potential loss of the Battery Direct and Battery Buses which provide emergency electrical power, accomplish the following: \n\n\tA.\tWithin 90 days after the effective date of this AD, modify Sundstrand P/N 26340061-04 battery chargers whose serial numbers are listed in Section I, paragraph 4.A. of Sundstrand Service Bulletin 26340061-24-2 dated February 24, 1984, in accordance with the Accomplishment Instructions of the Sundstrand service bulletin as referenced by McDonnell Douglas DC-9 Service Bulletin 24-73, dated March 21, 1984, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB.\tWithin 180 days after the effective date of this AD, modify all other Sundstrand P/N 26340061-04 battery chargers not affected by paragraph A. of this AD, in accordance with the Accomplishment Instructions of Sundstrand Service Bulletin 26340061-24-2 dated February 24, 1984, as referenced by McDonnell Douglas DC-9 Service Bulletin 24-73, dated March 21, 1984, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, 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 FAR 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis amendment becomes effective May 20, 1985.
87-03-07: 87-03-07 BOEING: Amendment 39-5523. Applies to Boeing Model 767-200 airplanes equipped with Bendix brakes, Part Numbers 2607092-1 and -2, certificated in any category. To preclude possible runway overshoot during certain runway-limited takeoffs or landings, due to erroneous braking performance information in the Airplane Flight Manual (AFM), accomplish either paragraph A. or B., below, within 30 days after the effective date of this AD, unless already accomplished. \n\n\tA.\tAmend the applicable FAA-approved AFM's, Boeing Documents D6T11320 and D6T11321, to include the information contained in subject FAA-approved revisions below: \n\n\tD6T11320.222, Revision 13; \n\tD6T11320.231, Revision 13; \n\tD6T11321.223, Revision 16; \n\tD6T11321.232, Revision 16; \n\tRevision 2 to Appendix 8F to D6T11321; or \n\n\tB.\tAmend the applicable FAA-approved AFM's, Boeing Documents D6T11320 and D6T11321, by incorporating the following performance adjustments: \n\n\t\t1.\tTAKEOFF SPEEDS - Pre-correction (original) V1 speeds are reduced by two (2) knots for gross weights of 280,000 lbs. and greater, and by one (1) knot for gross weights below 280,000 lbs. \n\n\t\t2.\tTAKEOFF PERFORMANCE-LIMITED WEIGHTS - Pre-correction FIELD LENGTH LIMITS weights are reduced by: \n\n\n\n FIELD LENGTH\nLIMITED WEIGHT 1000 LBS.\nWEIGHT DECREMENT (LBS.) FOR FLAP POSITION SHOWN \t\t\t \n\t\t\t\t\n\t\t\t\t\t\t\t 1\t 5\t 15\t 20\n\t380 & Above\t\t\t\t\t4900\t4900\t4400\t4500\n\t360\t\t\t\t\t\t4600\t4700\t4400\t4300\n\t340\t\t\t\t\t\t4300\t4500\t4300\t4000\n\t320\t\t\t\t\t\t4000\t4100\t4000\t3600 \n\t300\t\t\t\t\t\t3600\t3500\t2600\t2500 \n\t280\t\t\t\t\t\t2800\t2100\t1300\t1300 \n\t260\t\t\t\t\t\t1200\t1100\t1200\t1200 \n\t240 & Below\t\t\t\t\t1000\t1100\t1200\t1200 \n\n\tTo determine corrected runway length (as in obstacle clearance calculations), increase gross weight by the above amounts before entering the FIELD LENGTH LIMITS chart. \n\t\t3.\tLANDING FIELD LENGTH LIMITS - For gross weights above 280,000 lbs., landing field length required is increased by 900 feet over the pre-correction value. For gross weights of 280,000 lbs. and below, the landing field length required is increased by 350 feet over the pre-correction value. \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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tAll persons affected by this directive who have not already received copies of the Airplane Flight Manual performance information may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective February 26, 1987.