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73-14-07: 73-14-07 GRUMMAN AMERICAN AVIATION CORPORATION (GAAC): Amendment 39-1684 as amended by Amendment 39-1970. Applies to all G-159 airplanes, and to G-1159 airplanes, Serial Numbers 1 through 129 and 775, certificated in all categories. Compliance required as indicated. To detect fuselage aft section pressure dome cracks and prevent further cracking, accomplish the following: (a) Within 200 hours time in service after the effective date of this AD or 90 days, whichever is the sooner, unless already accomplished, permanently remove all interior lining attachments other than fabric, carpeting, etc., from the fuselage aft section pressure dome assembly, Part No. 1159B21372 (G-1159), Part No. 159B10252 (G-159) and inspect for cracks in accordance with GAAC Customer Bulletins 167 (G-1159) or 240 (G-159), dated June 18, 1973 or later FAA approved revisions placing emphasis on those areas as defined in paragraph (b). (b) Mark the exact location on the dome and record the geometric configuration of items removed in accordance with paragraph (a), noting the location of any discontinuities, particularly in radially running attachment strips. The FAA would appreciate receiving sketches and descriptive data of both the attachment location and geometric configurations. Sketches and descriptive data may be sent to the Chief, Engineering and Manufacturing Branch, Southern Region, P. O. Box 20636, Atlanta, Georgia 30320. (c) For aircraft found to have no attachments on the dome, no further action is required. (d) For aircraft having attachments, reinspect for cracks at intervals not to exceed 400 landings (G-1159) or 4000 landings (G-159), since the last inspection, in accordance with GAAC Customer Bulletins 167 (G-1159) or 240 (G-159). (e) Repair all cracks detected during the inspections conducted in accordance with (a) or (d). Repair in accordance with GAAC Customer Bulletins 167 (G-1159) or 240 (G-159), before further flight. (f) For the purpose of complying with paragraph (d) of this AD, subject to acceptance by the assigned FAA Maintenance Inspector, the number of landings may be determined by dividing each airplane's hour's time in service by the operator's fleet average time from takeoff to landing for the airplane type. (g) Airplanes having cracked domes may be flown to a base for repairs in accordance with FAR 21.197 either: (1) Unpressurized, or (2) With limited pressurization with the concurrence of the FAA, Chief, Engineering and Manufacturing Branch, Southern Region. Amendment 39-1684 became effective July 16, 1973. This Amendment 39-1970 becomes effective September 30, 1974.
99-23-07: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Eurocopter France Model SA330F, G, J, and AS332C, L, and L1 helicopters. This action requires inserting statements into the Limitations section of the Rotorcraft Flight Manual (RFM) prohibiting flight under certain atmospheric conditions. This amendment is prompted by one incident in which a Multi-Purpose Air Intake (MPAI) inlet seal deflated after the P2 air system line, which feeds the seal, clogged due to the formation of ice. The actions specified in this AD are intended to prevent clogging of the MPAI seal P2 air system line due to ice formation, which could result in deflation of the MPAI seal, loss of engine power, and subsequent loss of control of the helicopter.
2014-06-03: We are adopting a new airworthiness directive (AD) for British Aerospace Regional Aircraft Jetstream Series 3101 and Jetstream Model 3201 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 stress corrosion cracking of the main landing gear yoke pintle housing on a Jetstream series 3100 airplane. We are issuing this AD to require actions to address the unsafe condition on these products.
99-22-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and 340B series airplanes, that requires removal of certain main landing gear downlock and brake hydraulic swivel brackets and replacement with new, redesigned brackets. 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 failure of the downlock or brake swivels. Brake swivel failure could cause the loss of inboard or outboard brakes. Downlock swivel failure could cause the loss of hydraulic fluid in the main hydraulic system, as well as the loss of nose wheel steering operation, extension and retraction capability of landing gear and flaps, and operation of the propeller brake (if installed).
91-19-01: 91-19-01 CANADAIR, LTD.: Amendment 39-8026. Docket No. 91-NM-161-AD. Applicability: Model CL-600-1A11 series airplanes, serial numbers 1004 through 1085; Model CL-600-2A12 series airplanes, serial numbers 3001 through 3066; and Model CL-600-2B16 series airplanes, serial numbers 5001 through 5098; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent loss of emergency power to the essential bus when the air driven generator (ADG) is deployed, accomplish the following: (a) Within 25 hours time-in-service after the effective date of this AD, inspect the ADG wiring harness to detect chafing, in accordance with Canadair Service Bulletin A600-0612 (for Model CL-600-1A11 series airplanes), dated April 24, 1991, or Canadair Service Bulletin A601-0370 (for Model CL-600-2A12 and CL-600-2B16 series airplanes), dated April 24, 1991. If chafing is found, prior to further flight, repair in accordance with the applicable service bulletin previously described. (b) Within 60 days after the effective date of this AD, modify the ADG harness installation in accordance with Canadair Service Bulletin A600-0612 (for Model CL-600-1A11 series airplanes), dated April 24, 1991, or Canadair Service Bulletin A601-0370 (for Model CL- 600-2A12 and CL-600-2B16 series airplanes), dated April 24, 1991. (c) An 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, New York Aircraft Certification Office, ANE-170, FAA, Engine and Propeller Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, New York Aircraft Certification Office, ANE-170. (d) Special 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 thisAD. (e) The inspection, repair, and modification requirements shall be done in accordance with Canadair Service Bulletin A600-0612 (for Model CL-600-1A11 series airplanes), dated April 24, 1991, or Canadair Service Bulletin A601-0370 (for Model CL-600-2A12 and CL-600-2B16 series airplanes), dated April 24, 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 Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station A, Montreal, Quebec, Canada H3C 3G9. Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; at the FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. This amendment (39-8026, AD 91-19-01) becomes effective on September 24, 1991.
2014-05-10: We are superseding Airworthiness Directive (AD) 2012-25-04 for Eurocopter France Model AS350B3 helicopters with a certain modification (MOD) installed. AD 2012-25-04 required installing two placards and revising the Rotorcraft Flight Manual (RFM). AD 2012-25-04 also required certain checks and inspecting and replacing, if necessary, all four laminated half-bearings (bearings). This new AD retains the previous AD requirements, requires certain modifications which would be terminating action for the airspeed limitations, and adds certain helicopter models to the bearing inspection with a different inspection interval. These actions are intended to prevent vibration due to a failed bearing, failure of the tail rotor, and subsequent loss of control of the helicopter.
2006-04-07: This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ airplanes, that requires installation of a linear fluid- filled damper between each elevator surface and the airplane structure on both the left and right sides of the airplane, along with related structural and system modifications. The actions specified by this AD are intended to prevent pitch oscillation (vertical bouncing) of the fuselage due to excessive ice buildup on the elevator servo tab, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
96-13-02: This amendment adopts a new airworthiness directive (AD) that applies to certain Jetstream Aircraft Limited (JAL) Jetstream Model 3201 airplanes. This action requires repetitively inspecting the spigot housing plate for cracks and corrosion at the wing/fuselage forward attachment sliding joint, replacing any cracked or corroded part, and eventually replacing the spigots and spigot housing plate with new parts of improved design. A crack in the spigot housing plate assembly found during fatigue testing of the affected airplanes 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.
46-14-01: 46-14-01 FAIRCHILD: (Was Mandatory Note 5 of AD-724-2.) Applies to Model M- 62C Aircraft. Inspect indexing of fixed pitch wood propeller on engine crankshaft. To reduce possibility of crankshaft failure, fixed pitch wood propeller must be installed in the 90 degree position (blades at right angles to the crankthrow.)
98-02-06 R1: This amendment revises an existing airworthiness directive (AD), applicable to certain Boeing 777-200 series airplanes, that currently requires repetitive visual inspections to determine the presence and condition of the nut and cotter pin of the lock link mechanism on the side struts and drag struts on the main landing gear (MLG); and corrective action, if necessary. That AD was prompted by reports of missing or damaged components on the lock link mechanism. The actions specified by that AD are intended to prevent failure of the lock link mechanism to lock the MLG in the down position, and consequent collapse of the MLG during ground operation. This amendment provides an optional terminating action for the repetitive inspections.