Results
73-03-03: 73-03-03 BELLANCA: Amdt. 39-1591. Applies to Model 17-30A (Serial Numbers 30263 through 73-30489) airplanes. Compliance: Required as indicated unless already accomplished. To prevent bolt failures and subsequent washer ingestion into the engine, accomplish the following: a) Within 10 hours time in service after the effective date of this AD, remove the 4 AN4H-17A bolts attaching the air induction box to the throttle body and replace these bolts with new ones. When reassembling the air induction box, assure that the 4 washers between the spacers and the air induction box are properly installed and the bolts are torqued to 35-40 inch- pounds and safety wired. b) Within 50 hours time in service after the effective date of this AD, modify the air induction box in accordance with Bellanca Service Letter Number 75 dated January 3, 1973, or later FAA approved revisions. c) Any alternate equivalent method of compliance with Paragraphs a and b above must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Great Lakes Region. This amendment becomes effective February 7, 1973.
2010-19-05: We are adopting a new airworthiness directive (AD) for the specified ECF model helicopters. This AD results from a mandatory continuing airworthiness information (MCAI) AD issued by the aviation authority of the European Aviation Safety Agency (EASA). The MCAI AD reports the separation and loss of a stainless steel ring (75 millimeter (mm) in diameter) from a tail rotor blade (blade) sleeve resulting in severe, high-frequency vibrations, which can lead to damage to the fenestron blades, loss of yaw control, and subsequent loss of control of the helicopter.
2006-03-05: The FAA is superseding an existing airworthiness directive (AD), which applies to all Short Brothers Model SD3-60 and SD3-SHERPA airplanes. That AD currently requires an inspection of the fork end of the rear pintle pin on each main landing gear (MLG) to verify that sealant is properly applied and is undamaged, and related investigative/corrective actions if necessary. This new AD requires an additional inspection for correctly applied sealant on the MLG rear pintle pin assemblies, and related investigative/corrective actions if necessary. This AD also expands the applicability of the existing AD. This AD results from a new report of a cracked pintle pin fork end. We are issuing this AD to prevent stress-corrosion cracking and subsequent failure of the MLG. DATES: This AD becomes effective March 14, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of March 14, 2006. On March 18, 1993 (58 FR 7983, February 11, 1993), the Director of the Federal Register approved the incorporation by reference of Shorts SD3-60 Service Bulletin SD360-32-33, dated August 7, 1992.
96-13-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 series airplanes, that requires a one-time detailed visual inspection to detect cracking of the elevator gust lock housing and the gust lock support structure, and repair or replacement of cracked parts. This amendment is prompted by a report of failure of an elevator gust lock housing due to fatigue cracking. The actions specified by this AD are intended to prevent fatigue cracking of the elevator gust lock housing and the gust lock support structure, which could result in loss of the elevator and the support structure, and possible consequent loss of primary pitch control.
78-16-03: 78-16-03 LEARJET: Amendment 39-3278. Applies to Learjet Model 23 (Serial Numbers 23-003 and up); Model 24 and 24A (Serial Numbers 24-100 through 24-180); Model 24B and 24B-A (Serial Numbers 24-181 through 24-229); Model 24C, 24D and 24D-A (Serial Numbers 24-218, and 24-230 through 24-328); Model 24E, 24F and 24F-A (Serial Numbers 24- 329 through 24-356); Model 25 and 25A (Serial Numbers 25-002 through 25-066); Model 25B and 25C (Serial Numbers 25-061, 25-067 through 25-201, 25-204 and 25-205); Model 25D and 25F (Serial Numbers 25-206 through 25-253); Model 35 (Serial Numbers 35-001 through 35- 066); Model 35A (Serial Numbers 35-067 through 35-194); Model 36 (Serial Numbers 36-001 through 36-017); and Model 36A (Serial Numbers 36-018 through 36-040) airplanes. COMPLIANCE: Required as indicated unless already accomplished. To preclude a failure of the refrigeration condenser fan: A) Before the next flight, remove or lower the tailcone access door, disconnect the aircraft batteries, and inspect the refrigeration condenser fan part number that is rubber stamped on the blade. If the refrigeration condenser fan installed has a part number other than 6608059-3, no further action is required. (The blades on P/N 6608059-3 fans are not tapered in thickness from the hub to the tip.) B) If Part Number 6608059-3 refrigeration condenser fan is installed, before the next flight fabricate a placard which reads "DO NOT OPERATE REFRIGERATION SYSTEM UNDER ANY CIRCUMSTANCES ON THE GROUND OR IN THE AIR." Install this placard as near as possible to the refrigeration system control switch and operate the airplane in accordance with this restriction. C) When the Part Number 6608059-3 fan is replaced with either a P/N 6608059-1, 6608059-2 or a P/N 6608059-4 fan, the above required placard may be removed and the airplane returned to normal service. (The blades on the -1, -2 and -4 fans are tapered in thickness from the hub to the tip.) D) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. NOTE: Gates Learjet Service Bulletins SB23/24/25-284, dated 7/13/78, and SB35/36- 21-3, dated 7/12/78, or later approved revisions, provide inspection and fan replacement procedures, physical characteristics of the fans, and replacement part credit information. This amendment becomes effective August 17, 1978, to all persons except those to whom it has already been made effective by air mail letter from the FAA dated July 21, 1978.
2010-11-09: We are adopting a new airworthiness directive (AD) for the products listed above. 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: Engine in-flight shutdown incidents have been reported on Diamond Aircraft Industries DA 42 airplanes equipped with TAE 125 engines. The investigations showed that it was mainly the result of failure of the Proportional Pressure Reducing Valve (PPRV) (also known as Propeller Control Valve) due to high vibrations. This condition, if not corrected, could lead to further cases of engine in-flight shutdown, possibly resulting in reduced control of the aircraft. Since the release of European Aviation Safety Agency (EASA) AD 2008-0145, the engine gearbox has been identified as the primary source of vibrations for the PPRV, and it has also been determined that failure of the electrical connection to the PPRV could have contributed to some power loss events or in-flight shutdowns. We are issuing this AD to prevent engine in-flight shutdown, possibly resulting in reduced control of the aircraft.
78-12-05: 78-12-05 SIKORSKY: Amendment 39-3240 as amended by Amendment 39-3562. Applies to Sikorsky Models S-61L, S-61N, S-61NM, and S-61A helicopters with fixed S-61L type landing gears. After the effective date of this AD, compliance is required as indicated below in accordance with the designated paragraphs of Section 2 of Sikorsky Service Bulletin No. 61B25-6C, dated March 8, 1978, or later FAA approved revisions. 1. Within the next 10 landings, remove from service all S6125-50312 series and S6125-50313 series fitting assemblies and replace them in accordance with Paragraph C. 2. Within 15 hours time in service, and thereafter at intervals not to exceed 15 hours time in service, inspect, and replace if cracked, fitting assemblies S6125-50333-1, S6125-50333- 2, S6125-50334-1, and S6125-50334-2 in accordance with Paragraph B. 3. Within 120 landings, and thereafter at intervals not to exceed 120 landings or 15 flight hours from the last inspection, whichever results in longest calendar interval, inspect, and replace if cracked, fitting assemblies S6125-50333-1, S6125-50333-2, S6125-50334-1, and S6125-50334-2 with 7,000 or more landings in accordance with Paragraph D. NOTE: If the number of landings cannot be determined, the fitting assemblies shall be considered to have more than 7,000 landings. 4. Within 15 hours time in service, and thereafter at intervals not to exceed 15 hours time in service from the last inspection, inspect, and replace if cracked, fitting assemblies, P/Ns S6180-63151 series, S6180-63161 series, S6125-50314 series, S6125-50315 series, S6125-50317 series, and the attachment lugs of S6125-50304-1 and S6125-50304-2 cylinder assemblies in accordance with Paragraph E. 5. Within 10 landings, unless already accomplished, and thereafter at intervals not to exceed 400 landings from the last inspection, inspect, and replace if cracked, tube assemblies, P/Ns S6125-50310-3, S6125-50310-4, S6125-50311-6, and S6125-50311-7, with 1,100 or more landings in accordance with Paragraph F. NOTE: If number of landings cannot be determined, fitting assemblies shall be considered to have more than 1,100 landings. 6. Within 10 landings, unless already accomplished, and thereafter at intervals not to exceed 1,200 landings from the last inspection, inspect, and replace if cracked, tube assemblies, P/Ns S6125-50310-3, S6125-50310-4, S6125-50311-6, and S6125-50311-7, with 2,300 or more landings in accordance with Paragraph G. 7. Within 50 landings, unless already accomplished, and thereafter at intervals not to exceed 670 landings from the last inspection, inspect, and replace if cracked, fitting assemblies, P/N S6180-63161 series, with 126,000 or more landings, in accordance with Paragraph H. 8. Daily or at 50 landing intervals, whichever comes first, inspect and replace if cracked, fitting assemblies, P/N S6180-63151 series, with 75,000 or more landings in accordance with Paragraph I. 9. Within50 landings after the effective date of this amendment, unless already accomplished, and thereafter at intervals not to exceed 2,000 landings from the last inspection, inspect and replace, if cracked, cylinder assemblies, P/Ns S6125-50304-1 and S6125-50304-2, with 45,000 or more landings in accordance with Paragraph J. 10. Within 50 landings after the effective date of this amendment, unless already accomplished, and thereafter at intervals not to exceed 2,000 landings from the last inspection, inspect and replace, if cracked, cylinder assemblies, P/Ns S6125-50304-1 and S6125-50304-2, with 98,000 or more landings in accordance with Paragraph K. 11. Within 50 landings, remove from service all main landing gear upper tube assemblies, P/Ns S6125-50338-1 and S6125-50338-2, and lower tube assemblies, P/Ns S6125- 50337-1 and S6125-50337-2, that have been in service for more than 32,000 landings. NOTE: If the number of landings specified in Paragraphs 7, 8, 9, 10, and 11 above cannot be determined, an estimate of the number of landings based upon the past operation of the part may be made and submitted for approval to the Chief, Engineering and Manufacturing Branch, FAA, New England Region. 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 Sikorsky Aircraft, Stratford, Connecticut 06602. These documents may also be examined at FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its Headquarters in Washington, D.C., and at the FAA, New England Region Headquarters, Burlington, Massachusetts. This amendment supersedes AD 77-16-06, Amendment 39-2997. Amendment 39-3240 became effective upon publication in the FEDERAL REGISTER. This Amendment 39-3562 becomes effective upon publication in the FEDERAL REGISTER.
95-22-09: This amendment supersedes an existing airworthiness directive (AD), applicable to Boeing Defense and Space Group Helicopter Division (Boeing) Model 234 series helicopters, that currently requires inspections of the forward and aft transmission first stage sun and spiral bevel ring gear bolted connection (bolted connection). This amendment requires a revision to the inspection intervals and criteria used during these inspections, as well as adds a visual inspection of the pinion and spiral bevel ring gear. This amendment is prompted by reports that certain of the affected helicopters have been discovered with loose nuts on the bolted connection more frequently than was anticipated in the previous AD. The actions specified by this AD are intended to prevent wear of the spiral bevel ring gear flange surface, failure of the bolted connection, transmission failure, and subsequent loss of control of the helicopter.
94-07-01: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F series airplanes, that requires modification of the cavity vent drain tube assembly at the center wing lower auxiliary fuel tank cavity. This amendment is prompted by a report that the cavity vent tube, if not properly grounded, could act as an electrical path in the event of a lightening strike. The actions specified by this AD are intended to prevent arcing in the tank cavity and possible resulting fire.
92-02-13: 92-02-13 BOEING: Amendment 39-8149. Docket No. 91-NM-168-AD. \n\n\tApplicability: Model 747 series airplanes; as listed in Boeing Alert Service Bulletin 747- 21A2312, and in Boeing Service Bulletin 747-21-2317, both dated May 30, 1991, certificated in any category. \n\n\tCompliance: Required within the next 60 days after the effective date of this AD, unless previously accomplished. \n\n\tTo reduce the potential for an uncontrollable fire in the aft lower lobe compartment, accomplish the following: \n\n\t(a)\tInstall a decompression panel and flapper valve in accordance with Boeing Alert Service Bulletin 747-21A2312 or Boeing Service Bulletin 747-21-2317, both dated May 30, 1991, as applicable. \n\n\t(b)\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\t(c)\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\t(d)\tThe installation required by this AD shall be done in accordance with Boeing Alert Service Bulletin 747-21A2312, dated May 30, 1991; or Boeing Service Bulletin 747-21- 2317, dated May 30, 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington, or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. \n\n\t(e)\tThis amendment (39-8149, AD 92-02-13) becomes effective on March 25, 1992.