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89-18-04: 89-18-04 MCDONNELL DOUGLAS: Amendment 39-6295. (Docket No. 89-NM-16-AD) \n\n\tApplicability: McDonnell Douglas Model DC-9-80 (MD-80) series airplanes and Model MD-88 airplanes, as listed in McDonnell Douglas Service Bulletin 80-8, dated November 3, 1988, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent fire in the number 2 engine nacelle, accomplish the following: \n\n\tA.\tWithin 18 months after the effective date of this AD, relocate the number 2 engine starter shutoff valve pneumatic tube, in accordance with the accomplishment instructions in McDonnell Douglas MD-80 Service Bulletin 80-8, dated November 3, 1988. \n\n\tB.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Los Angeles Aircraft Certification Office. \n\n\tC.\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-LOO (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 (39-6295, AD 89-18-04) becomes effective on September 18, 1989.
2006-17-16: The FAA is adopting a new airworthiness directive (AD) for all Fokker Model F.28 Mark 0070 and 0100 airplanes. This AD requires a one- time detailed inspection to detect corrosion on the wing rear spar lower girder, and related investigative and applicable corrective actions if necessary. This AD results from reports of corrosion of the wing rear spar lower girder between wing station (STA) 8700 and wing STA 9200. We are issuing this AD to detect and correct corrosion of the wing rear spar lower girder, which could result in reduced structural integrity of the wing rear spar.
2006-17-17: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-100, DHC-8-200, DHC-8-300, and DHC-8-400 series airplanes. This AD requires inspecting the left and right control column torque tube assemblies to determine the type of rivets installed and replacing incorrect or indeterminate type rivets with the correct type rivets. This AD results from a report that incorrect rivets having lower than required strength were installed on the control column torque tube during production. We are issuing this AD to prevent shear failure of control column torque tube rivets, which could cause unexpected decoupling of the elevators and large unwanted deflection of the free elevator, and consequent reduced controllability of the airplane.
2018-17-17: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model DHC-8-400 series airplanes. This AD was prompted by reports of arcing and smoke emanating from the windshields. This AD requires a revision to the maintenance or inspection program, as applicable, to include an inspection of the windshield moisture seal for signs of cracks, erosion, wear, and other deterioration; doing that inspection and repair if necessary; and re-torqueing the screws that fasten the windshield heater terminal lugs and applying sealant to the screw heads of the windshield heaters. We are issuing this AD to address the unsafe condition on these products.
2006-17-15: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model DC-10-10 and DC-10-10F airplanes; and Model MD-10-10F airplanes. This AD requires replacing the clamp bases for the fuel vent pipe with improved clamp bases. This AD results from reports that the foil wrapping on existing plastic clamp bases has migrated out of position, which compromises the bonding of the fuel vent pipes to the airplane structure. We are issuing this AD to ensure that the fuel vent pipes are properly bonded to the airplane structure. Improper bonding could prevent electrical energy from a lightning strike from dissipating to the airplane structure, and create an ignition source, which could result in a fuel tank explosion.
87-25-03: 87-25-03 BRITISH AEROSPACE: Amendment 39-5779. Applies to British Aerospace Model 125-800A series airplanes, listed in British Aerospace (BAe) Service Bulletin 57-64-(3067), dated November 29, 1985, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent entrapment of water within the aileron tab accomplish the following: A. Within the next 100 landings or within one year after the effective date of this AD, whichever occurs sooner, modify the aileron tab and the inboard aileron hinge to provide drainage in accordance with BAe Service Bulletin 57-64-(3067), dated November 29, 1985. B. 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, Northwest Mountain Region. C. 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 the modification 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 British Aerospace, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. 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 becomes effective January 13, 1988.
2006-17-08: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney (PW) PW4077D, PW4084D, PW4090, and PW4090-3 turbofan engines that were reassembled with certain previously used high pressure compressor (HPC) exit brush seal assembly parts and certain new or refurbished HPC exit diffuser air seal inner lands. This AD requires replacing the HPC exit inner and outer brush seal packs with new brush seal packs, or replacing the HPC exit brush seal assembly with a new HPC exit brush seal assembly. This AD results from a report of oil leaking into the high pressure turbine (HPT) interstage cavity and igniting, leading to an engine case penetration and engine in- flight shutdown. Although liberated engine parts did not penetrate the engine nacelle, we are issuing this AD to prevent uncontained engine failure, damage to the airplane, and injury to passengers.
2018-14-10: We are superseding Airworthiness Directive (AD) 2017-12-03 for certain Pratt & Whitney Division (PW) PW2037, PW2037M, and PW2040 turbofan engines. AD 2017-12-03 required installing a software standard eligible for installation and precludes the use of electronic engine control (EEC) software standards earlier than SCN 5B/I. This AD requires installing a software standard eligible for installation and preclude the use of EEC software standards earlier than SCN 5B/I or SCN 27A. This AD was prompted by an unrecoverable engine in-flight shutdown (IFSD) after an ice crystal icing event. We are issuing this AD to address the unsafe condition on these products.
2000-08-21: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747 series airplanes, that requires repetitive inspections to detect cracking of the forward and aft inner chords and the splice fitting of the forward inner chord of the station 2598 bulkhead, and repair, if necessary. This amendment is prompted by reports of fatigue cracking found in those areas. The actions specified by this AD are intended to detect and correct such cracking, which could result in reduced structural capability of the bulkhead and the inability of the structure to carry horizontal stabilizer flight loads.
88-20-07: 88-20-07 BOEING: Amendment 39-6024. Applies to all Model 727 series airplanes, certificated in any category.\n \n\tCompliance required as indicated, unless previously accomplished. \n\n\tTo prevent jamming of the main landing gear door actuator caused by fracturing of the pivot trunnion, accomplish the following: \n\n\tA.\tWithin the next 1,600 flight cycles after the effective date of this AD, accomplish the visual inspection of the main landing gear door actuator pivots in accordance with Boeing Service Bulletin 727-32-0358, dated May 31, 1988. Repeat this inspection at intervals not to exceed 800 flight cycles. \n\n\tB.\tIf any of the pivot trunnion shafts are found loose or missing during the inspection performed in accordance with paragraph A., above, prior to further flight, replace the pivot in accordance with Boeing Service Bulletin 727-32-0358, dated May 31, 1988. \n\n\tC.\tAccomplishing the pivot replacement with a part number 3-3141-54 pivot, in accordance with Sargent Controls Service Bulletin 7-3141-32-06, Revision 1, dated November 2, 1987, constitutes terminating action for the initial and repetitive inspections required by paragraph A., above. \n\n\tD.\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\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, Seattle Aircraft Certification Office. \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 Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington, 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington or Seattle Aircraft CertificationOffice, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis Amendment, 39-6024, becomes effective November 1, 1988.