Results
95-19-11: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model Viscount 744, 745D, and 810 airplanes, that requires inspections to detect cracking of certain fittings of the tailplane spar, and replacement of the fittings with serviceable parts, if necessary. This amendment is prompted by reports of fatigue cracking of certain fittings in the tailplane spar. The actions specified by this AD are intended to prevent such cracking, which could result in structural degradation of the attachment of the horizontal stabilizer to the fuselage.
93-11-07: 93-11-07 MCDONNELL DOUGLAS: Amendment 39-8597. Docket 92-NM-132-AD. \n\n\tApplicability: Model DC-6, DC-6A, DC-6B, C-118A, and R6D-1 series airplanes; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo ensure the continuing structural integrity of these airplanes, accomplish the following: \n\n\t(a)\tExcept as provided by paragraph (b) of this AD, inspect each Principal Structural Element (PSE) defined in Chapter 1, Section 6, and Chapter III, of McDonnell Douglas Corporation Report No. L26-014, DC-6 Supplemental Inspection Document (SID), dated January 1992 (hereafter referred to as "the SID"), in accordance with the non-destructive inspection (NDI) methods set forth in Chapter II of the SID, and in accordance with the schedule specified in paragraphs (a)(1) and (a)(2) of this AD: \n\n\t\t(1)\tComplete the initial inspection of each PSE specified in Chapter I, Section 6, and Chapter III of the SID as follows: \n\n\t\t\t(i)\tFor PSE's that have not yet reached their inspection threshold as of one year after the effective date of this AD, the initial inspection must be accomplished no later than the threshold specified. \n\n\t\t\t(ii)\tFor PSE's that have exceeded their inspection threshold as of one year after the effective date of this AD, the initial inspection must be accomplished within on repeat (R) interval for the PSE, measured from a date one year after the effective date of this AD. \n\n\t\t(2)\tSubsequent inspections must be accomplished at intervals not to exceed the intervals specified in Chapter III, Section 1, of the SID for the specific NDI sequence code used at the previous inspection. \n\n\t(b)\tAs an alternative to the requirements of paragraph (a) of this AD: Within one year after the effective date of this AD, incorporate a revision into the FAA-approved maintenance inspection program which provides for inspection of the PSE's defined in Chapter I, Section 6, and Chapter III of the SID. The NDI techniques set forth in the SID provide acceptable methods for accomplishing the inspections required by this AD. \n\n\t(c)\tDiscrepant structure detected during the inspections required by this AD must be replaced or repaired prior to further flight, in accordance with the McDonnell Douglas DC-6 Structural Repair Manual; or in accordance with data approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate. \n\n\t(d)\tAll inspection results (positive or negative) must be reported to the McDonnell Douglas Corporation in accordance with the instructions in the SID. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. \n\n\t(e)\tAn alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safetymay be used if approved by the Manager, Los Angeles Aircraft Certification Office (ACO), 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, Los Angeles ACO. \n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. \n\n\t(f)\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(g)\tThe inspections and reporting requirements shall be done in accordance with McDonnell Douglas Corporation Report No. L26-014, DC-6 Supplemental Inspection Document (SID), dated January 1992. 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 McDonnell Douglas Corporation, P.O. Box 1771, Long Beach, California 90846-1771, Attention: Business Unit Manager, Technical Publications - Technical Administrative Support, C1-L5B. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft Certification Office (ACO), 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. \n\n\t(h)\tThis amendment becomes effective on July 22, 1993.
93-10-02: 93-10-02 TELEDYNE CONTINENTAL MOTORS: Amendment 39-8603. Docket 93-ANE-28. Applicability: Teledyne Continental Motors (TCM) O-200, O-300, IO/TSIO/LTSIO-360, O/IO/TSIO-470, IO/TSIO/LTSIO/GTSIO-520, and IO/TSIO/TSIOL-550 series reciprocating engines listed by serial number in TCM Mandatory Service Bulletin (MSB) No. 93-12, dated May 12, 1993, or that contain cylinder assemblies purchased from TCM between July 29, 1992, and March 30, 1993; installed on but not limited to: Aeronca Models 15AC and S15AC; American Champion (Bellanca) Models 7ACA and 402; Beagle Model 206S; Beech Models Debonaire, Bonanza, and Baron; Bellanca Models 14-19, 14-19-2, 14-19-3, 14-19-3A, 17-30, 17-31, and 17-31TC; Cessna Models 150, 170, 172, 180, 182, 185, 188, 205, 206, 207, 210, 303, 310, 320, 335, 336, 337, 340, 401, 402, 404, 414, 421, and T41; Aero Commander Models 200, 500, and 685; Champion Models Citabria and Lancer; Maule Models Bee Dee M-4, M-4, M-4C, M-4S, M-4T, M-4-210, M-4-210C, M-4-210S,M-4-210T, and M-5-210C; Mooney Models 231 and 252; Navion series; Piper Models Arrow, Seneca, and PA46-310P; and Taylorcraft Model F-19 aircraft. Compliance: Required prior to further flight, unless previously accomplished. To prevent an engine failure due to a missing cylinder valve retainer key, accomplish the following: (a) For engines that have less than 25 hours time in service (TIS), or unknown TIS, on the effective date of the AD since new, rebuild, or factory overhaul, visually inspect each cylinder to determine if both valve retainer keys are in place on each valve, and if the roto coil, if applicable, is properly positioned, in accordance with TCM MSB No. 93-12, dated May 12, 1993. NOTE: Certain TCM engine models do not incorporate roto coils in the valve assembly. (1) If a valve retainer key is missing, or if a roto coil, if applicable, is mispositioned, repair or replace the cylinder, as necessary, in accordance with the applicable TCM Overhaul Manual. (2) If the valve retainer keys are in place, and the roto coil, if applicable, is correctly positioned, return engine to service in accordance with TCM MSB No. 93-12, dated May 12, 1993. (b) For engines with individually installed new service or chrome plated cylinder assemblies purchased from TCM between July 29, 1992, and March 30, 1993, that have less than 25 hours TIS on the effective date of this AD since installation of any cylinder(s), visually inspect each new service or chrome plated cylinder, and repair or replace the cylinder, as necessary, in accordance with paragraph (a) of this AD. (c) Uninstalled cylinder assemblies purchased from TCM between July 29, 1992, and March 30, 1993, must be inspected and repaired, as necessary, in accordance with paragraph (a) of this AD prior to installation on an engine. (d) For engines that have 25 hours or more TIS on the effective date of this AD, since new, rebuild, or factory overhaul, no inspection is required.(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, Atlanta Aircraft Certification Office. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta 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 Atlanta Aircraft Certification Office. (f) The inspections shall be done in accordance with the following service bulletin: Document No. Pages Revision Date TCM MSB No. 93-12 1-7 Original May 12, 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 Teledyne Continental Motors, P.O.Box 90, Mobile, AL 36601; telephone (205) 438-3411 ext. 305, fax (205) 438-3411 ext. 179. 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. (g) This amendment becomes effective August 12, 1993, to all persons except those persons to whom it was made immediately effective by priority letter AD 93-10-02, issued May 17, 1993, which contained the requirements of this amendment.
93-11-06: 93-11-06 DE HAVILLAND, INC.: Amendment 39-8596. Docket 92-NM-204-AD. Applicability: Model DHC-7 series airplanes; serial numbers 3 through 37, 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, modify the wing inboard leading edge and support structure (Modification No. 7/1632), in accordance with de Havilland Service Bulletin 7-57-14, dated June 25, 1982. (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 modification shall be done in accordance with de Havilland Service Bulletin 7-57-14, dated June 25, 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.
95-17-10: This amendment adopts a new airworthiness directive (AD) that applies to certain Jetstream Aircraft Limited (JAL) Jetstream Models 3101 and 3201 airplanes. This action requires modifying the central annunciator panel test button circuit. A report of diode failure in this circuit and subsequent inadvertent engine shutdown on one of the affected airplanes prompted this action. The actions specified by this AD are intended to prevent failure of a diode in the central annunciator panel test button circuit, which could result in inadvertent engine shutdown while in flight if the central annunciator panel test button is pressed.
96-11-02: This amendment adopts a new airworthiness directive (AD) that applies to Jetstream Aircraft Limited (JAL) HP137 Mk1, Jetstream series 200, and Jetstream Model 3101 airplanes. This action requires repetitively inspecting the spigot housing plate for cracks at the wing/fuselage forward attachment sliding joint, replacing any cracked housing plate, repetitively inspecting the spigots and spigot posts for corrosion and installing improved spigots if corrosion is found that exceeds certain limits, and eventually installing improved spigots if corrosion that does not exceed certain limits is found. For certain affected airplanes, this action requires repetitively inspecting the spigot bushes for migration gaps, replacing the bushes with modified bushes if gaps are found that exceed 0.5 inch, and eventually replacing the bushes with modified bushes if migration gaps are not found. Reports of bush migration gaps found on three of the affected airplanes and another report of corrosion and several cracks found on the spigot housing plate on a Jetstream Model 3101 airplane prompted this action. The actions specified by this AD are intended to prevent structural failure of the wing/fuselage area caused by a cracked or corroded spigot housing assembly.
99-04-20: This amendment adopts a new airworthiness directive (AD) that is applicable to Agusta S.p.A. Model A109K2 helicopters. This action requires replacing a certain Breeze-Eastern rescue hoist (rescue hoist) with a different part-numbered airworthy rescue hoist. This amendment is prompted by an incident in which a rescue hoist cable broke due to cable damage, resulting in one fatality. The actions specified in this AD are intended to prevent the breaking of the rescue hoist cable, personal injury, or entanglement of the rescue hoist cable in the helicopter s main or tail rotor blades, and subsequent loss of control of the helicopter.
97-07-11: This amendment supersedes Airworthiness Directive (AD) 81-20-01, which currently requires repetitively inspecting the nose landing gear (NLG) actuator support structure and the front pressure bulkhead for cracks on Jetstream Aircraft Limited (JAL) HP137 Mk1 and Jetstream series 200 airplanes, and replacing any cracked part. This AD retains the repetitive inspections required by AD 81-20-01; requires repetitively inspecting the NLG retraction jack upper mounting fitting and attachment hardware for security bolt failure and for bolts with improper torque levels on the HP137 Mk1, Jetstream series 200, and Jetstream Model 3101 airplanes, and requires replacing any failed security bolts and adjusting any bolt with an improper torque level; and requires modifying the NLG retraction jack on all affected airplanes, as terminating action for the repetitive inspections. This AD results from reports of NLG jack mounting fitting failures on several of the affected airplanes, and the Federal Aviation Administration's policy on aging commuter-class aircraft. The actions specified by this AD are intended to prevent failure of the NLG caused by a cracked NLG actuator support structure or cracked front pressure bulkhead, which, if not detected and corrected, could lead to nose gear collapse and damage to the airplane.
97-11-08: This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model CL-415 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to modify the limitation that prohibits positioning the power levers below the flight idle stop during flight, and to provide a statement of the consequences of positioning the power levers below the flight idle stop during flight. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the propeller ground beta range was used improperly during flight. The actions specified in this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
97-23-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 and 0070 series airplanes, that requires replacement of the fusible pin in the upper torque link of the main landing gear with an improved pin. 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 reduced structural integrity and potential collapse of the main landing gear.