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93-11-08: 93-11-08 DE HAVILLAND, INC.: Amendment 39-8598. Docket 92-NM-69-AD. Applicability: Model DHC-7 series airplanes; serial numbers 1 through 30, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent structural failure, accomplish the following: (a) Within 6 months after the effective date of this AD, perform a one-time inspection of the lower two securing rivets on the left- and right-hand ground spoiler actuator attachment brackets to ensure the integrity of these rivets and to detect signs of fuel leakage, in accordance with de Havilland Service Bulletin 7-57-12, dated January 15, 1982. (1) If any loose or damaged rivet is found, or if there is evidence of fuel leakage, prior to further flight, modify the ground spoiler actuator attachment brackets (Modification No. 7/1827), in accordance with the service bulletin. (2) If no loose or damaged rivet and no evidence of fuel leakage is found, within 6 months after accomplishing the inspection required by paragraph (a) of this AD, modify the ground spoiler actuator attachment brackets (Modification No. 7/1827), in accordance with the service bulletin. (b) 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, New York Aircraft Certification Office (ACO), ANE-170, FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (c) 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. (d) The inspection and modification shall be done in accordance with de Havilland Service Bulletin 7-57-12, dated January 15, 1982. 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 de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on July 22, 1993.
2013-09-10: We are superseding an existing airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. That AD currently requires repetitive inspections to detect cracking of the lower corners of the door frame and cross beam of the forward cargo door, and corrective actions if necessary. That AD also requires eventual modification of the outboard radius of the lower corners of the door frame and reinforcement of the cross beam of the forward cargo door, which terminates the existing repetitive inspections. This new AD revises the compliance times for the preventive modification; adds certain inspections for cracks in the number 5 cross beam of the forward cargo door; and adds inspections of the number 4 cross beam if cracks are found in the number 5 cross beam, and corrective actions if necessary. For certain airplanes, this \n\n((Page 31390)) \n\nnew AD also adds a one-time inspection for airplanes previously modified or repaired, and a one-time inspection of the reinforcement angle for excessive shimming or fastener pull-up, and corrective actions if necessary. This AD was prompted by additional reports of fatigue cracking in the radius of the lower frames and in the lower number 5 cross beam of the forward cargo door. We are issuing this AD to prevent fatigue cracking of the lower corners of the door frame and number 5 cross beam of the forward cargo door, which could result in rapid depressurization of the airplane.
98-23-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Pratt & Whitney (PW) PW4000 series turbofan engines not incorporating modifications described in certain PW service bulletins listed in the applicability section, that requires high pressure compressor (HPC) blade tip grinding of the rotor assembly, installation of aluminum oxide coated HPC blade tips in stages 9 through 12, modification of HPC 8th through 14th stage stators, incorporation of 1st stage high pressure turbine (HPT) vanes with increased airflow area which also requires additional HPT hardware modifications, and incorporation of HPC 13th-15th stage zirconium oxide blade tips. This amendment is prompted by reports of HPC surge caused by excessive HPC rear stage rotor-to-case clearance. The actions specified by this AD are intended to prevent HPC surge, which can result in engine power loss at a critical phase of flight such as takeoff or climb. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of January 12, 1999.
91-07-17: 91-07-17 GENERAL ELECTRIC COMPANY: Amendment 39-6954. Docket No. 90-ANE-23. Applicability: General Electric Company (GE) CT58-140-1 turboshaft engines overhauled by H&S Aviation, Division 3 (Formerly Hants and Sussex), Portsmouth, England, between March 14, 1989, and August 21, 1989, installed on, but not limited to, Sikorsky S-61 and Boeing V107 aircraft. The affected parts are identified by part number (P/N) and serial number (S/N) and are installed in engines with S/N, as follows: Engine S/N Part Name P/N Part S/N 295235 Stage 1 forward cooling plate 37C30005P101 BJWTMS 7732 Stage 1 aft cooling plate 3002T25P01 BJWTMS 6649 Stage 2 forward cooling plate 000T88P02 ASVA 3663 Stage 2 aft cooling plate 3002T27P01 ASVA 0125 Power Turbine (PT) wheel & shaft 5002T30P01 GAT 59510 295206 Stage 1 turbine wheel 4002T17P02 GATBK 483 Stage 2 turbine wheel 4002T96P02 GATFE 352 280326 Stage 2 turbine wheel 4002T96P02 GATL 2835 PT wheel and shaft 5002T30P01 GAT 59722 280218 PT wheel and shaft 5002T30P01 GAT 59692 280294 Stage 1 forward cooling plate 37C300055P101 BJWTMS 7663 Stage 1 aft cooling plate 3002T25P01 5778 5778 Stage 2 forward cooling plate 3000T88P02 BJWTMS 5951 Stage 2 aft cooling plate 3002T27P01 BJWTMS 7356 Stage 2 turbine wheel 4002T96P02 GATEL 092 Compliance: Required as indicated, unless already accomplished. To prevent failure of suspect gas generator (GG) turbine rotor parts and power turbine (PT) wheels, which may have a reduced low cycle fatigue life due to inadvertent shotpeening which could result in an uncontained engine failure, remove and inspect all surfaces of GG turbine rotor parts and PT wheels identified above by 20x microscope as follows: (a) Part S/N BJWTMS 7732, BJWTMS 6649, ASVA 3663, ASVA 0125, and GAT 59510, prior to accumulating 5,853 cycles since new (CSN). (b) Part S/N GATBK 483, and GATFE 352, prior to accumulating 5,249 CSN. (c) Part S/N GATL 2835, prior to accumulating 10,792 CSN. (d) Part S/N GAT 59722, prior to accumulating 10,856 CSN. (e) Part S/N GAT 59692, prior to accumulating 9,660 CSN. (f) Part S/N BJWTMS 7663, BJWTMS 5778, BJWTMS 5951, BJWTMS 7356, and GATEL 092, prior to accumulating 5,696 CSN. (g) Remove from service parts found with evidence of shotpeening and replace with a serviceable part. Reidentify parts found with no evidence of shotpeening prior to return to service. NOTE: GE Alert Service Bulletin CT58 A72-173 (CEB-275), contains information in reference to paragraphs (a) through (g) above. (h) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (i) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedule specified in this AD may be approved by the Manager, Engine Certification Office, ANE-140, Engine and Propeller Directorate, Aircraft Certification Service, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803-5299. All persons affected by this directive who have not already received the appropriate alert service bulletin from the manufacturer may obtain copies upon request to GE Aircraft Engines, 1000 Western Avenue, Lynn, Massachusetts 01910. These documents may be examined at the FAA, New England Region, Office of the Assistant Chief Counsel, Room 311, 12 New England Executive Park, Burlington, Massachusetts. This amendment (39-6954, AD 91-07-17) becomes effective on April 26, 1991.
98-23-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model Hawker 800XP series airplanes, that requires replacement of the fuel feed hose assemblies of the auxiliary power unit (APU) with new hose assemblies. This amendment is prompted by a report of the collapse of the inner casing of the fuel feed hose that supplies fuel to the APU. The actions specified by this AD are intended to prevent failure of the fuel feed hose assemblies, which could result in fuel leakage and consequent risk of fire in the aft equipment bay.
98-23-12: This amendment supersedes an existing airworthiness directive (AD), applicable to all de Havilland Model DHC-7 series airplanes, that currently requires certain structural inspections, and repair, if necessary. This amendment requires an additional structural inspection. 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 detect and correct fatigue cracking in certain significant structural areas, which could reduce the structural integrity of these airplanes.
77-13-14: 77-13-14 HAWKER SIDDELEY AVIATION, LIMITED: Amendment 39-2939. Applies to Model DH-114 airplanes, certificated in all categories, except those modified in accordance with either Hawker Siddeley Modification 1102 or 1103. Compliance is required as indicated, unless already accomplished. To detect corrosion and cracking of the drag brace fittings at the center section spar lower cap, and prevent possible structural failure of the wing, accomplish the following: (a) Within the next 50 hours time-in-service after the effective date of this AD, inspect the drag brace fittings, P/N 4 FS.1797(L.H.) and 4 FS.1798(R.H.), for corrosion and cracks in accordance with paragraph 4, entitled "Inspection of Fittings," of Hawker Siddeley Aviation, Ltd., Technical News Sheet, Series 114, No. F.18, dated April 9, 1973, or an FAA- approved equivalent. (b) If a crack or evidence of severe corrosion is found in either drag brace fitting during the inspection specified in paragraph (a)of this AD, before further flight, replace the drag brace fitting with an improved fitting, P/N 14FS.6069 (L.H.) or P/N 14FS. 6070 (R.H.), in accordance with the instructions set forth in paragraph 5.2 of Hawker Siddeley Aviation, Ltd., Technical News Sheet, Series 114, No. F.18, dated April 9, 1973, or an FAA-approved equivalent. (c) "Severe corrosion" as used in this AD is internal corrosion that has progressed to a point where there is evidence of corrosion breaking through the exterior surface of the fitting. "Surface corrosion" as used in this AD means corrosion limited to surface pitting. NOTE: The Hawker Siddeley Aviation, Ltd., Model DH-114 Maintenance and Repair Manual further defines the terms "severe corrosion" and "surface corrosion." (d) If, during an inspection specified in paragraph (a) of this AD, no crack is found and evidence of corrosion is found but it is limited to surface corrosion and does not constitute the severe corrosion specified in paragraph (b) of this AD, before further flight, remove the corrosion and protect the surface from further corrosion in accordance with FAR 43.13, and thereafter reinspect the drag brace fittings in accordance with the inspection requirements of paragraph (a) of this AD at intervals not to exceed 100 hours time-in-service from the last inspection. NOTE: Advisory Circular AC 43.13-1A, "Acceptable Methods, Techniques and Practices - Aircraft Inspection and Repair," contains information relating to corrosion protection and removal. (e) If, during an inspection specified in paragraph (a) of this AD, no crack is found in the fittings, and the fittings are free of evidence of any corrosion, reinspect the fittings in accordance with the inspection requirements of paragraph (a) of this AD at intervals not to exceed 100 hours time-in-service from the last inspection. (f) The repetitive inspections required by paragraphs (d) and (e) of this AD may be terminated upon the installation of the improved fittings, P/Ns 14FS. 6069 (L.H.) and 14FS. 6070 (R.H.), in accordance with the instructions set forth in paragraph 5.2 of Hawker Siddeley Aviation, Ltd., Technical News Sheet, Series 114, No. F.18, dated April 9, 1973, or an FAA- approved equivalent. This amendment becomes effective July 7, 1977.
2013-09-09: We are superseding an existing airworthiness directive (AD) for all Slingsby Sailplanes Ltd. Models Dart T.51, Dart T.51/17, and Dart T.51/17R sailplanes equipped with aluminum alloy spar booms. 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 an incident of glue joint failure on a starboard wing caused by water entering the area of the airbrake box that resulted in delamination and corrosion in the area of the aluminum alloy spar booms and the wing attach fittings. We are issuing this AD to require actions to address the unsafe condition on these products.
98-23-13: This amendment supersedes an existing airworthiness directive (AD), applicable to all British Aerospace Model Viscount 700, 800, and 810 series airplanes, that currently requires repetitive inspections to detect cracks and corrosion in the inboard and outboard engine nacelle structures on the wings; replacement of any cracked fittings and mating struts; and treatment or replacement of any corroded fittings or struts. This amendment requires repetitive inspections to detect cracking or corrosion of the eye end fittings of the outboard engine lower support or of the bore of the taper pin holes, and repair, if necessary. This amendment also limits the applicability of the existing AD. This amendment is prompted by reports of cracked and separated lower eye end fittings. The actions specified by this AD are intended to detect and correct cracking of the eye end fittings of the outboard engine lower support, which could result in reduced structural integrity of the engine nacelle support structures.
98-22-16: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-22-16 which was sent previously to all known U.S. owners and operators of RHC Model R44 helicopters by individual letters. This amendment supersedes AD 98-12-19, issued August 5, 1998, applicable to RHC Model R44 helicopters, that currently requires main rotor blade inspections and replacement if a crack is found. This amendment requires the same inspections as AD 98-12-19, but mandates replacement of all the affected main rotor blades prior to further flight after November 15, 1998. This amendment is prompted by an incident in which a crack was discovered in a main rotor blade. The actions specified by this AD are intended to prevent failure of a main rotor blade and subsequent loss of control of the helicopter.