Results
95-02-09: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model ATP airplanes, that requires inspections to detect damage, overheating, and proper operation of the DC connections and cooling fans in certain transformer rectifier units (TRU), and repair or replacement, if necessary. This amendment is prompted by a report of the loss of all DC electrical power, except for the battery emergency bus, due to failure of the TRU's, which occurred during flight. The actions specified by this AD are intended to prevent such failures that could lead to loss of essential electrical power required to continue safe flight of the airplane.
47-32-14: 47-32-14 BELL: (Was Service Note 1 of AD-1H-1.) Applies Only to Model 47B Serial Numbers 5, 6, and 10. Inspection required at intervals not to exceed 100-hours. In order to prevent misalignment of the tail rotor drive quill and tail rotor drive shaft and powerplant installation, due to the shifting of the engine mount assembly, caused by the insufficient clamping of the engine mount to the rubber mounts, the following action should be taken: (1) Inspect AN 365-524 nuts on AN 5-20A bolts in the "clamp" ends of the 47-612- 111-1 engine mount assembly for bottoming of nuts. If this condition is found, proceed as outlined in steps (2), (3), and (4). (2) Remove bolts from "clamps" and install AN 960-516 washers as required under the head of each bolt. Replace bolts in "clamps" and install nuts loosely. (3) Check installation of engine mount assembly on rubber mounts 47-600-011-1. Front face of left mount "clamp" must be 5/32 inch aft of front face of metal case of rubber mount. (4) Torque nuts to 100-140 inch-pounds. (Bell Service Bulletin No. 47C10 also covers this same subject.)
93-14-02: 93-14-02 FOKKER: Amendment 39-8626. Docket 93-NM-93-AD. Applicability: Model F28 Mark 0100 series airplanes; serial numbers 11244 through 11463, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent erroneous lateral guidance from the automatic flight control and augmentation system (AFCAS) when a go-around is initiated below 100 feet, during a flight director (FD) or non-redundant autopilot approach, accomplish the following: (a) Within 14 days after the effective date of this AD, amend Section 2.08.01, AFCAS LIMITATIONS, subsection Instrument Landing System (ILS) APPROACH, of the FAA-approved Airplane Flight Manual (AFM) to include the following statements. This may be accomplished by inserting a copy of this AD in the AFM. (1) Change Minimum Decision Height: "Weather Limitations: CAT II - FMA: GS/LOC - Minimum Decision Height (DH): 150 feet - Runway Visual Range(RVR): 400 meters/1,200 feet NOTE 1: CAT III (LAND 2 and LAND 3) weather limitations remain unchanged." (2) Change Minimum Use Height with GS/LOC annunciated. "Minimum use height: - If the surface wind exceeds 40 knots: 150 feet - If not: - With GS/LOC annunciated: 150 feet - With LAND 2 or LAND 3 annunciated: 0 feet" (3) Add the following limitation under ILS APPROACH: "USE OF FLIGHT DIRECTOR DURING ILS APPROACH When GS/LOC is annunciated on FMA, both FD's may not be used below 150 feet and must be switched OFF passing 150 feet." (b) Installation of improved AFCAS software, version V13S, in the flight control computers (FCC) in accordance with Fokker Service Bulletin SBF100-22-037, dated May 31, 1993, constitutes terminating action for the requirements of paragraph (a) of this AD. After this installation has been accomplished, the AFM limitations required by paragraph (a) may be removed. (c) 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. (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 installation shall be done in accordance with Fokker Service Bulletin SBF100-22-037, dated May 31, 1993. 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. 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. (f) This amendment becomes effective on August 2, 1993.
2021-03-09: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 727 series airplanes. This AD was prompted by a determination that excessive sealant coating on internal wing Structural Significant Items (SSIs) may not reveal cracks during inspections required by AD 98-11-03 R1. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate inspections that will give no less than the required damage tolerance rating (DTR) for certain SSIs of the wing. This AD also requires repetitive inspections for cracking of the affected SSIs and repair if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2002-14-24: This amendment adopts a new airworthiness directive (AD), applicable to certain Cessna Model 650 airplanes, that requires a one-time inspection of the side brace mechanism assemblies of the left and right main landing gears (MLG) to detect any incorrect part number, and corrective actions if necessary. This action is necessary to prevent inadvertent disengagement of the locking mechanism of the side brace mechanism assembly, which could lead to collapse of the respective MLG, and result in a gear-up landing and possible injury to passengers and crew. This action is intended to address the identified unsafe condition.
80-09-11: 80-09-11\tTELEDYNE CONTINENTAL MOTORS: Amendment 39-3763. Applies to Model GTSIO-520 series engines overhauled by AAR Western Skyways, Inc. \n\tTo prevent the possible separation of the starter torsional damper from the starter gear shaft and subsequent damage to critical components in the engine nacelle, accomplish the following: \n\ta.\tPrior to next flight: \n\t\t1.\tRemove engine cowling to the extent that the rear of the engine, where the starter and/or starter adapter are installed, can be seen. \n\t\t2.\tInspect the locking device at the outboard end of the starter gear shaft, which secures the torsional damper (see Figure I) for proper installation of all required parts. There must be a snap ring (TCM P/N 502171), a nut lock key (TCM P/N 632980), a compression spring (TCM P/N 628311) and a Marsden slotted hex nut (TCM P/N 632979) installed. \n\t\t3.\tIf all of the parts (in 2. above) are installed correctly, no further action is required. \n\tb.\tIf all the parts (in a.2. above) are not installed or are of the incorrect part, accomplish the following: \n\t\t1.\tPrior to the next flight and within every 25 hours engine operating time thereafter until all correct parts are installed, check the torque on the existing hexagon nut on the starter gear shaft to 180-220 foot pounds. For installations incorporating a compressor sheave for air conditioner drive, the hex nut must be checked for a torque of 195-235 foot pounds. \n\t\t2.\tWithin 100 hours engine operating time after the effective date of this AD, install all correct parts in accordance with TCM overhaul manual instructions. \n\tParts may be obtained from Teledyne Continental Motors, P.O. Box 90, Mobile, Alabama 36601, telephone (A/C 205) 438-3411, or AAR Western Skyways, Inc., Troutdale, Oregon, telephone (A/C 503) 665- 1181 or any other Teledyne Continental Motors distributor. \n\n\t\nc.\tAircraft may be flown in accordance with FAR 21.197 to a base where the repairs required by this AD can be accomplished. \n\tAn equivalentmethod of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, P.O. Box 20636, Atlanta, Georgia 30320. \n\tThis amendment is effective upon publication in the Federal Register as to all persons except those persons to whom it was made immediately effective by priority mail, issued April 3, 1980, which contained this amendment.
92-08-01: 92-08-01 BOEING: Amendment 39-8212. Docket No. 91-NM-228-AD.\n\n\tApplicability: Model 757 series airplanes, equipped with Pratt and Whitney PW2000 series engines; as listed in Boeing Alert Service Bulletin 757-28A0028, dated October 3, 1991; certificated in any category.\n\n\tCompliance: Required within 270 days after the effective date of this AD, unless previously accomplished.\n\n\tTo ensure that in-flight engine restart capability is available, accomplish the following:\n\n\t(a)\tRemove and replace the left and right engine fuel shutoff valves in accordance with Boeing Alert Service Bulletin 757-28A0028 dated October 3, 1991.\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. The request shall 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 the airplane to a location where the requirements of this AD can be accomplished.\n\n\t(d)\tThe replacement shall be done in accordance with Boeing Alert Service Bulletin 757-28A0028 dated October 3, 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, 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.\n\n\t(e)\tThis amendment becomes effective on May 19, 1992.
89-22-13: 89-22-13 BOEING: Amendment 39-6362. Docket No. 89-NM-103-AD \n\tApplicability: Model 757 series airplanes equipped with Pratt and Whitney engines, listed in Boeing Service Bulletin 757-76-0006, dated March 16, 1989, certificated in any category. \n\n\tCompliance: Required within the next 12 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent the elevator control cables binding on the engine throttle control cable fairleads, accomplish the following: \n\n\t\tA.\tRemove two engine throttle control cable fairleads in accordance with Boeing Service Bulletin 757-76-0006, dated March 16, 1989. \n\n\t\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, Seattle 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 orcomment, and then send it to the Manager, Seattle Aircraft Office. \n\n\t\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 Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6362, AD 89-22-13) becomes effective on November 20, 1989.
2007-11-18R1: The FAA is revising an existing airworthiness directive (AD) for General Electric Company (GE) CF6-50C series turbofan engines. That AD currently requires reworking certain forward fan stator cases and installing a fan module secondary containment shield. This AD requires the same actions but eliminates a certain service bulletin from the compliance method. This AD results from a review that shows that only one of the service bulletins referenced in the original AD is applicable as a compliance method. We are issuing this AD revision to eliminate a certain service bulletin from the compliance method and to prevent uncontained fan blade failures, which can result in separation of airplane hydraulic lines, damage to critical airplane systems, and possible loss of airplane control.
46-39-05: 46-39-05 DOUGLAS: (Was Mandatory Note 6 of AD-762-7.) Applies Only to C-54B and Other C-54 Series Airplanes Having the C-54B Fuel System. \n\n\tTo be accomplished not later than December 1, 1946. \n\n\tThe main fuel line supporting brackets at wing Stations 357, 378, and 399 are subject to vibration failure and are to be replaced with redesigned brackets. In addition, the United Carr clips at wing Station 378 are to be replaced by Adel clips. \n\n\t(Douglas Service Bulletin No. DC-4-5 covers this same subject.)