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87-17-01: 87-17-01 SCHWEIZER AIRCRAFT CORP: Amendment 39-5973. Final copy of priority letter AD issued August 18, 1987. Applies to models (including kit built) SGU 1-7; SGS 2-8 (TG-2); SGS 2-12 (TG-3); SGU 1-19; SGU 1-20; SGU 1-21; SGU 2-22, 2-22A, 2-22C, 2- 22CK, 2-22E, 2-22EK; SGS 1-23, 1-23B, 1-23C, 1-23D, 1-23E, 1-23F, 1-23G, 1-23H, 1-23H15; SGS 1-24; SGS 1-26, 1-26A, 1-26B, 1-26C, 1-26D, 1-26E; SGS 2-32; SGS 2-33, 2-33A, 2- 33AK; SGS 1-34, 1-34R; SGS 1-35C; SGS 1-36 (SPRITE) gliders, certificated in any category. Compliance is required prior to the next flight after the effective date of this AD, unless already accomplished. To prevent the possibility of the tow release assembly creating a jammed condition during towing and subsequent failure of the tow line to release, which could result in a forced landing, accomplish the following: (a) Inspect the tow release installation to determine if any of the following release arms are installed: P/N 1D217-13, 1D222-15, 1D222-17 or 34017D-15. NOTE: The above arms can be identified by a lug which is welded on the front face of the release arm as shown in Figure 1 of Schweizer Service Bulletin (SB) No. SA-005.1, dated January 31, 1988. (b) Tow release installations which have any of the release arms listed in (a) must have the arms replaced in the following manner: P/N 1D217-13 replace with 1D217-09 P/N 1D222-15 replace with 1D222-11 P/N 1D222-17 replace with 1D222-13 P/N 34017D-15 replace with 34017D-11 (c) Perform the operational check in accordance with Figure 4 in Schweizer SB No. SA-001.3, dated January 31, 1988, following release arm replacement. (d) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, New York Aircraft Certification Office, Federal Aviation Administration (FAA), New England Region, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. Schweizer Aircraft Corporation SB No's. SA-005.1, and SA-001.3, both dated January 31, 1988, identified and described in this document, 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 from Schweizer Aircraft Corporation, P.O. Box 147, Elmira, New York 14902; telephone (607) 739-3821. These documents may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Docket No. 87-ANE-29, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment, 39-5973, becomes effective on August 19, 1988, as to all persons except those persons to whom it was made immediately effective by individual priority letter AD 87-17-01, issued August 18, 1987, which contained this amendment.
88-19-10: 88-19-10 CANADAIR: Amendment 39-6020. Applies to Model CL-600-2B16 series airplanes, Serial Numbers 5002 through 5027, certificated in any category. Compliance required as indicated, unless previously accomplished. To preclude erroneous autopilot/flight director ILS operations, accomplish the following: A. Within 48 hours after the effective date of this AD: 1. Insert the following into the Limitations Section of the FAA-approved Airplane Flight Manual (AFM), under paragraph 8.C., Automatic Flight Control System, and notify all crewmembers: "Flight director approaches and autopilot coupled approaches are not permitted without a valid radio altimeter." NOTE: This may be accomplished by inserting a copy of Canadair, Ltd., Airplane Flight Manual PSP 601A-1, Temporary Revision No. 601/13, dated April 6, 1988, into the AFM. 2. Install a placard in the cockpit, visible to the pilot, stating: "FLIGHT DIRECTOR APPROACHES AND AUTOPILOT COUPLED APPROACHES PROHIBITED WITHOUT A VALID RADIO ALTIMETER." B. Installation of Sperry/Honeywell Flight Guidance Computer, P/N 7003974-715, in accordance with Paragraph 2 of Canadair, Ltd., Service Bulletin 601-0276, dated May 10, 1988, constitutes terminating action for the requirements of paragraph A., above, and the temporary AFM revision and placard should be removed. C. An 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, New York Aircraft Certification Office, FAA, New England Region. NOTE: The request should be forwarded through an FAA Principal Operations Inspector (POI) or Principal Avionics Inspector (PAI), as appropriate, who may add comments and then send it to the Manager, New York Aircraft Certification Office. 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 this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Canadair, Ltd., Commercial Aircraft Technical Services, P.O. Box 6087, Station A, Montreal, Quebec H3C 3G9, Canada. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment, 39-6020, becomes effective October 5, 1988.
2022-25-07: The FAA is superseding Airworthiness Directive (AD) 2019-25- 16, which applied to certain Embraer S.A. Model ERJ 170-100 LR, -100 STD, -100 SE, and -100 SU airplanes; and Model ERJ 170-200 LR, -200 SU, -200 STD, and -200 LL airplanes. AD 2019-25-16 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by the determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2019-25-16 and requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive airworthiness limitations and certain structural modifications, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2015-17-14: We are adopting a new airworthiness directive (AD) for all Airbus Model A319, A320, and A321 series airplanes. This AD was prompted by reports that during a full scale fatigue test, several broken frames in certain areas of the cargo compartment have been found, especially on the cargo floor support fittings and open tack holes on the left-hand side. This AD requires a rototest inspection of the open tack holes and rivet holes at the cargo floor support fittings of the fuselage, including doing all applicable related investigative actions, and repair if necessary. We are issuing this AD to detect and correct cracking in the open tack holes and rivet holes at the cargo floor support fittings of the fuselage, which could affect the structural integrity of the airplane.
89-03-01 R1: 89-03-01 R1 GOODYEAR: Amendment 39-6103 as revised by Amendment 39-6334. Applicability: 32x8.8R16, 10PR, P/N 328Q08G2 radial tires, with serial dates 8060Gxxx and above, installed on but not limited to ATR-42 aircraft. Compliance: Required as indicated, unless already accomplished. To prevent tire failure, accomplish the following: (a) Remove from service, all tires with serial dates between 8060Gxxx and 8320Gxxx, as follows: (1) Tires which have accumulated 250 or more landings since new on the effective date of this AD, within the next 50 landings. (2) Tires which have accumulated less than 250 landings since new on the effective date of this AD, at or prior to accumulating 300 landings. (3) Tires for which no landing record has been maintained, within the next 50 landings. (b) Remove from service, all tires with serial dates 8340Gxxx and above, as follows: (1) Tires which have accumulated 250 or more landings since new on the effective date of this AD, within the next 150 landings. (2) Tires which have accumulated less than 250 landings since new on the effective date of this AD, at or prior to accumulating 400 landings. (3) Tires for which no landing record has been maintained, within the next 150 landings. NOTES: (1) Tires with serial dates 8060Gxxx and above may be used as replacements subject to the restrictions of paragraphs (a) and (b) above. Tires with serial dates prior to 8060Gxxx are approved without restrictions. (2) Goodyear Alert Service Bulletins 32-001, dated December 5, 1988, and 32-002, Revision 1, dated July 14, 1989, apply to this AD. (c) 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. (d) 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 times specified in this AD may be approved by the Manager, Boston Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. This AD revises AD 89-03-01, Amendment 39-6103 (54 FR 1342; January 13, 1989) which became effective on February 12, 1989. This amendment (39-6334, AD 89-03-01 R1) becomes effective on November 13, 1989.
2002-05-03: This amendment supersedes an existing airworthiness directive (AD), that is applicable to General Electric Company (GE) CF6-6, CF6- 45, and CF6-50 series turbofan engines, that currently requires revisions to the Time Limits Section of the manufacturer's Instructions for Continued Airworthiness (ICA) to include required inspection of selected critical life-limited parts at each piece-part exposure. This amendment modifies the airworthiness limitations section of the manufacturer's manual and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements. A Federal Aviation Administration (FAA) study of in- service events involving uncontained failures of critical rotating engine parts has indicated the need for mandatory inspections. The mandatory inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained failures. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
2022-22-10: The FAA is superseding Airworthiness Directive (AD) 2020-21- 11, which applied to certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, -133, -151N, and - 153N airplanes; and Model A320 and A321 series airplanes. AD 2020-21-11 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2020-21-11 and requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
90-13-04: 90-13-04 SAAB-SCANIA: Amendment 39-6631. Docket No. 90-NM-16-AD. Applicability: Model SF-340A series airplanes, Serial Numbers 004 through 108, inclusive, certificated in any category. Compliance: Required prior to the accumulation of 16,000 landings or within 30 days after the effective date of this AD, whichever occurs later, unless previously accomplished. To prevent fatigue damage and reduced structural integrity of the wings, accomplish the following: A. Remove the four fasteners in the lower part of the wing/fuselage attachment fitting at Wing Station 42.3 (left and right wings), enlarge the holes, and inspect for cracks using a non-destructive testing method (eddy current), in accordance with SAAB-Scania Service Bulletin 340-57-017, dated December 1, 1989. 1. If no cracks are found, prior to further flight, install oversize fasteners in accordance with the service bulletin. 2. If cracks are found, prior to further flight, further enlarge theholes and install oversize fasteners, in accordance with the service bulletin. The holes may be enlarged up to 0.264/0.262 inch (6,706/6,655 mm). 3. If cracks are still found following the maximum reaming allowed, repair prior to further flight, in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. B. An 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, Standardization Branch, ANM- 113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. C. 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 this AD. All persons affected by this directivewho have not already received the appropriate service documents from the manufacturer may obtain copies upon request to SAAB-Scania, Product Support, S- 581.88, Linkoping, Sweden. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6631, AD 90-13-04) becomes effective on July 23, 1990.
2002-04-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-600, -700, -700C, and -800 series airplanes, that requires a one-time inspection of certain fasteners in rudder pedal housings to determine if pan-head fasteners are installed, and replacement of existing fasteners with improved fasteners, if necessary. The actions specified by this AD are intended to prevent loss of free movement of the rudder pedals, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
89-07-17: 89-07-17 MCDONNELL DOUGLAS: Amendment 39-6169. \n\n\tApplicability: Model DC-9 series, Model DC-9-80 series, Model MD-88, and C-9 (military) series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo detect center tank fuel pump failures, accomplish the following: \n\n\tA.\tWithin 10 calendar days after the effective date of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to add the following, and provide to flight crews. This may be accomplished by inserting a copy of this AD in the AFM: \n\n\t\tSECTION I - LIMITATIONS \n\n\t\tFUEL MANAGEMENT \n\n\t\tAdd the following wording at the beginning of this section: "Prior to engine start on any flight where center tank fuel is present and will be needed for that route segment, the center tank fuel pumps must be individually checked to verify pump operation. This must be accomplished by observing that both inlet fuel pressure low lights extinguish when each individual center tank pump is activated. \n\n\t\tNOTE: Center tank pumps on aircraft with a center tank fuel pump low pressure warning system installed are not required to be checked in accordance with these procedures." \n\n\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, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\t\tNOTE: The request should be forwarded through an FAA Principal Operations Inspector (POI), who may add any comments and then send it to the Manager, Los Angeles Aircraft Certification Office. \n\n\tThis amendment (39-6169, AD 89-07-17) becomes effective on May 4, 1989.