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2022-08-04: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 series airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
94-06-05: 94-06-05 HAMILTON STANDARD: Amendment 39-8853. Docket 94-ANE-09. Applicability: Hamilton Standard Model 14RF-9, 14RF-19, and 14RF-21 propellers, installed on but not limited to Embraer EMB-120 series, Construcciones Aeronauticas, SA (CASA) CN-235 series, and SAAB-SCANIA SF340 series aircraft. Compliance: Required as indicated, unless accomplished previously. To prevent propeller hub cracking and loss of engine oil, and possible loss of a propeller blade or hub, accomplish the following: (a) Within 30 days after the effective date of this airworthiness directive (AD), perform an initial torque check of the propeller hub retaining nuts, as follows: (1) For Hamilton Standard Model 14RF-9 propellers, in accordance with Temporary Revision (TR) No. 61-6, dated March 15, 1993, to Hamilton Standard Maintenance Manual (MM) P5186. (2) For Hamilton Standard Model 14RF-19 propellers, in accordance with TR No. 61-6, dated April 8, 1993, to Hamilton Standard MM P5199. (3) For Hamilton Standard Model 14RF-21 propellers, in accordance with TR No. 61-4, dated March 15, 1993, to Hamilton Standard MM P5189. (b) If propeller hub retaining nuts are found not to meet the acceptance criteria in accordance with the applicable TR to the Hamilton Standard MM's during the initial torque check in accordance with paragraph (a), and during the repetitive torque checks performed in accordance with paragraph (e) of this AD, remove the propeller hub from service and inspect for cracks in accordance with the applicable TR's listed in paragraph (a) of this AD. Remove propeller hubs with crack indications and replace with serviceable propeller hubs prior to further flight. (c) If the initial propeller hub retaining nut torque check is acceptable in accordance with the applicable TR listed in paragraph (a) of this AD, support the propeller with an appropriate lifting fixture and loosen all the propeller hub retaining nuts. Tighten the propeller hub retaining nuts as follows: (1) For Hamilton Standard Model 14RF-9 propellers, in accordance with TR No. 61-7, dated July 27, 1993, to Hamilton Standard MM P5186. (2) For Hamilton Standard Model 14RF-19 propellers, in accordance with TR No. 61-7, dated July 27, 1993, to Hamilton Standard MM P5199. (3) For Hamilton Standard Model 14RF-21 propellers, in accordance with TR No. 61-5, dated July 27, 1993, to Hamilton Standard MM P5189. (d) Make a one-time entry into propeller maintenance records to record: (1) that the initial torque check was performed; (2) the propeller hub retaining nuts were loosened and tightened in accordance with paragraph (c) of this AD; and (3) the torque values. (e) Thereafter, perform repetitive torque checks at intervals not to exceed 500 hours time in service since the last inspection, in accordance with the applicable TR to the Hamilton Standard MM's listed in paragraph (a) of this AD. (f) Install all propellersafter the effective date of this AD using the propeller hub retaining nut tightening procedure defined in the applicable TR to the Hamilton Standard MM's listed in paragraph (c) of this AD. Record the torque values in accordance with paragraph (d) of this AD. (g) Visually inspect and investigate all external propeller oil leakage at the next line check, or within 70 hours TIS after the effective date of this AD, whichever occurs first. If the leakage is found to be caused by other than a leak in the blade seal, the pressure relief valve, or actuator assembly, the propeller must be removed from service and replaced with a serviceable propeller prior to further flight. (h) Thereafter, visually inspect and investigate all external propeller oil leakage at intervals not to exceed 70 hours TIS since the last inspection, or at the next line check, whichever occurs first. If the leakage is found to be caused by other than a leak in the blade seal, the pressure relief valve, or actuator assembly, the propeller must be removed from service and replaced with a serviceable propeller prior to further flight. (i) 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, Boston Aircraft Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Boston Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Boston Aircraft Certification Office. (j) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the aircraft to a location where the requirements of this AD can be accomplished. (k) The torque checks, retightening, and installation procedures shall be done in accordance with the following service documents: Document No. Pages Date TR No. 61-6 to Hamilton Standard MM P5186 1-8 March 15, 1993 Total pages: 8. TR No. 61-7 to Hamilton Standard MM P5186 1-9 July 27, 1993 Total pages: 9. TR No. 61-6 to Hamilton Standard MM P5199 1-6 April 8, 1993 Total pages: 6. TR No. 61-7 to Hamilton Standard MM P5199 1-7 July 27, 1993 Total pages: 7. TR No. 61-4 to Hamilton Standard MM P5189 1-8 March 15, 1993 Total pages: 8. TR No. 61-5 to Hamilton Standard MM P5189 1-7 July 27, 1993 Total pages: 7. 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 Hamilton Standard, One Hamilton Road, Windsor Locks, CT 06096-1010. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (l) This amendment becomes effective on March 29, 1994.
98-20-21: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas DC-9-80 series airplanes, that requires an inspection to detect discrepancies of electrical plugs and receptacles of the sidewall lighting system in the passenger cabin, and to verify that the ends of all pins and sockets are even and that they are seated and locked into place. This amendment also requires replacement of any discrepant part with a new part, and modification of the electrical wiring and connectors of the sidewall lighting system in the passenger cabin. This amendment is prompted by reports of failures of the electrical connectors in the sidewall fluorescent lighting, which resulted in smoke or lighting interruption in the passenger cabin. The actions specified by this AD are intended to prevent failures of the electrical connectors, which could result in poor socket/pin contact, excessive heat, electrical arcing, and consequently, connector burnthrough and smoke in the passenger cabin.
98-20-08: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and C-9 (military) series airplanes, that requires visual and eddy current inspections to detect cracking of the frame-to-longeron attachment area, the frame-to-skin shear clips at certain fuselage stations, and the fuselage bulkhead at the front spar of the engine pylon in the aft fuselage; and repair, if necessary. This AD also requires certain modifications which, when accomplished, will terminate the requirement for inspections. This amendment is prompted by reports indicating that fatigue cracking has occurred at those areas. The actions specified by this AD are intended to prevent such fatigue cracking, which could cause damage to adjacent structure and result in reduced structural integrity of the airplane.
2013-04-11: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -800, and -900ER series airplanes. This AD was prompted by incorrect wire support clamps installed within the left environmental control systems (ECS) bay, which could allow wiring to come in contact with the exposed metal of the improper clamp. This AD requires inspections to identify the part number of the wire support clamp, related investigative actions, and corrective actions if necessary. We are issuing this AD to prevent electrical arcing and a potential ignition source within the ECS bay, which in combination with flammable fuel vapors, could result in a center wing fuel tank explosion, and consequent loss of the airplane.
56-04-01: 56-04-01 CHAMPION: Applies to Model 7EC Aircraft, Serial Numbers 300 to 370 Inclusive. To be accomplished as soon as practicable but not later than April 1, 1956. Inspect front and rear control stick socket castings, P/N 2-705, for cracks at the ears to which the push-pull tube attaches. If found cracked, the castings should be replaced. If a standard AN bolt, nut and washer are installed, replace with a clevis bolt, AN 24-16, (11/16 grip), and an AN 320-4 shear nut so that excessive loads cannot be placed on the socket ears.
98-20-23: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100, -200, and -300 series airplanes, that requires a one-time inspection to detect discrepancies in the electrical wiring and wiring harness behind the lavatory, and corrective actions. 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 chafing of electrical wiring, which could result in severe overheating of the wiring, consequent smoke in the flight deck and cabin, and possible injury to flightcrew or passengers.
92-15-09: 92-15-09 BRITISH AEROSPACE: Amendment 39-8303. Docket No. 91-NM-265-AD. Applicability: Model ATP series airplanes; serial numbers 2001 through 2041, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent poor windshield visibility, which could adversely affect the pilot's and co-pilot's ability to navigate the airplane visually, accomplish the following: (a) For airplanes having serial numbers 2001 through 2041: Within 14 days after the effective date of this AD, and thereafter at intervals not to exceed 50 hours time-in-service, apply Repcon wipe-on rain repellent, or other equivalent rain repellent, onto the windshields and adjacent sliding side windows, in accordance with British Aerospace Service Bulletin ATP-30-3, Revision 3, dated October 19, 1990. (b) For airplanes having serial numbers 2001 through 2019: Within 9 months after the effective date of this AD, relocate the windshield washer nozzles by incorporating Modification 35073A, in accordance with British Aerospace Service Bulletin ATP-30-10, dated September 30, 1991; or Revision 1, dated February 24, 1992. (c) For airplanes having serial numbers 2001 through 2041: Within 9 months after the effective date of this AD, reroute the windshield washer fluid supply lines by incorporating Modification 35198A, in accordance with British Aerospace Service Bulletin ATP-30-10, dated September 30, 1991; or Revision 1, dated February 24, 1992. (d) Accomplishment of the modification required by paragraph (b) of this AD constitutes terminating action for the requirements of paragraph (a) of this AD. (e) 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. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (f) 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. (g) The rain repellent fluid applications shall be done in accordance with British Aerospace Service Bulletin ATP-30-3, Revision 3, dated October 19, 1990, which includes the following list of effective pages: Page Number Revision Level Date 1 3 October 19, 1990 2-4 Original November 1988 The modifications shall be done in accordance with British Aerospace Service Bulletin ATP-30-10, dated September 30, 1991; or British Aerospace Service Bulletin ATP-30-10, Revision 1, dated February 24, 1992. These service bulletins contain the following list of effective pages: Service Bulletin Number Page Number Revision Level Date ATP-30-10 1-9, 11, 13, Original September 30, 1991 Original Issue 15, 17, 19 10, 12, 14, (These pages are not used) 16, 18 ATP-30-10 1-9, 9A, 17, 1 February 24, 1992 Revision 1 19 11, 13, 15 Original September 30, 1991 10, 12, 14, (These pages are not used) 16, 18 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, DC 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. (h) This amendment becomes effective on September 8, 1992.
2013-04-08: We are adopting a new airworthiness directive (AD) for Diamond Aircraft Industries GmbH [[Page 14161]] Model H-36, HK 36 R, HK 36 TS, and HK 36 TTS 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 installation of an unsuitable self-locking nut on the bell crank of the elevator push rod that can cause failure of the elevator, resulting in loss of control. We are issuing this AD to require actions to address the unsafe condition on these products.
2010-13-01: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the European Aviation Safety Agency (EASA) to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: The turbine wheel, part number (P/N) 095-01-015-03, of the SAPHIR 20 Model 095 APU is a life-limited part. Microturbo had determined through "fleet leader" testing and inspection that the published life limit of this turbine wheel should be reduced to 9,000 cycles. Use of the turbine wheel beyond 9,000 cycles could lead to the release of high energy debris that could jeopardize aircraft safety. For the reasons described above, EASA AD 2008-0084 required the implementation of the new life limit on the affected parts and the replacement parts that had exceeded the new life limit. Microturbo has now determined that the life limit of the turbine wheel should be further reduced to 4,225 cycles. Use of the turbine wheel beyond 4,225 cycles could lead to the release of high energy debris that could jeopardize aircraft safety. We are issuing this AD to prevent an uncontained burst of the APU turbine that could liberate high-energy fragments resulting in injury and damage to the aircraft.