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70-23-03: 70-23-03\tBOEING: Amendment 39-1105 as amended by Amendment 39-1115. The following airworthiness directive, applicable to all operators of Boeing 747 airplanes is effective immediately upon receipt of telegram dated October 23, 1970. Because of three reported incidents of the pilot's or first officer's instrument panel assemblies sliding aft and producing control column interference, one of the following alternate actions is to be accomplished within 25 flight hours in service after receipt of this telegram: \n\t(1)\tInstall placard on captain and first officer instrument panel stating "Check panel security before take-off." Or \n\t(2)\tIncorporate a check item in flight crew aircraft acceptance check list stating "Check security of captain and first officer instrument panels." Or \n\t(3)\tIn the maintenance program include security of captain and first officer instrument panel as a "required inspection item" whenever the panels are disturbed, subject to the approval of the assigned principal inspector. \n\tEquivalent methods of compliance must be referred to the Chief, Aircraft Engineering Division, FAA Western Region. \n\tAs an alternative action to (1), (2), or (3), secondary safety latches may be installed in accordance with Boeing Service Bulletin 31-2005, dated November 13, 1970, or later FAA approved revision. Accomplishment of this modification will constitute of itself compliance with this AD. \n\tAmendment 39-1105 became effective upon publication in the Federal Register for all person except those to whom it was made effective immediately by telegram dated October 23, 1970. \n\tThis amendment 39-1115 becomes effective December 4, 1970.
47-10-32: 47-10-32 LOCKHEED: (Was Service Note 2 of AD-763-3.) Applies Only to Model 49 Serial Numbers 2021 to 2067, Inclusive. At each periodic inspection, examine the upper wing surface forward of the aileron beam and just outboard of Station 458 joint for the presence of buckles. If serious buckles are found the skin in that area should be replaced and gussets added. After the entire affected area (approximately 5 inches x 36 inches) has been reworked in this manner, no further periodic inspections will be required. (LAC Service Instruction 49/SI-26 covers this same subject.)
47-47-03: 47-47-03 PIPER: (Was Mandatory Note 7 of AD-780-3.) Applies to All PA-12S Seaplanes Equipped With Edo 89-2000 Floats. Compliance required by January 15, 1948. Racking loads imposed by rough water operation can result in damage to the airplane fuselage structure. The following inspection and modification, therefore, is necessary: 1. Inspect fuselage members to which the float braces are attached, particularly in the left side truss. Any parts damaged or bent shall be properly repaired or replaced. 2. Install wire pulls (Edo P/N 89-S-176) inboard at the lower end of the front and rear float struts and add the diagonal brace wires (Edo P/N 92-S-200-9) between the floats. (Edo Service Bulletin No. 4 dated September 5, 1947, contains detailed instructions for this change.)
2016-10-04: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracked antenna support channels, skin cracking underneath the number 2 very high frequency (VHF) antenna, and cracking in the frames attached to the internal support structure. This AD requires repetitive inspections to determine the condition of the skin and the internal support structure, and follow-on actions including corrective action as necessary. We are issuing this AD to detect and correct skin cracking of the fuselage. Such cracking could result in separation of the number 2 VHF antenna from the airplane and rapid depressurization of the cabin.
47-20-08: 47-20-08 ERCO: (Was Mandatory Note 16 of AD-718-6.) Applies to 415-C, -CD and -D Aircraft. Compliance required prior to July 1, 1947. (a) Install a new battery box drain tube to extend at least 1/2 inch below the fuselage belly skin if this has not been already incorporated in the airplane. (b) Examine the fuselage structure and controls carefully for corrosion. If corrosion is found on the structure, the affected areas should be washed with an alkaline solution and followed by a thorough clear water rinse. Corroded controls should be replaced. (c) Examine the baggage compartment for deterioration. If damage is evident, wash the affected area with a diluted alkaline solution and rinse with clear water. Reinforce any damaged areas with 10 1/2-ounce single filled water-resistant canvas, double sewn with 16-4 glace finished thread. (d) Install decalcomania (Erco P/N 415-54062) on the top of the battery box cover. (Ercoupe Service Department Memorandum No. 44 dated February 17, 1947, and Ercoupe Service Department Bulletins No. 8 dated May 24, 1946, and No. 22, dated February 3, 1947, also cover the above subjects.)
2003-14-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that currently requires repetitive detailed inspections to detect cracked, corroded, or stained collar fittings on both inboard trailing edge flaps; and follow-on corrective actions, if necessary. This amendment expands the applicability in the existing AD, and adds repetitive inspections for discrepancies of the collar fittings, torque tube, and splined bushings on both inboard trailing edge flaps; and follow-on and corrective actions, if necessary. The actions specified by this AD are intended to prevent failure of the collar fittings, which could result in separation of the inboard trailing edge flap and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
91-18-21: 91-18-21 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39- 8025. Docket No. 91-NM-43-AD. Applicability: Model DHC-7 series airplanes; Serial Numbers 53 through 57, 59, and 60; certificated in any category. Compliance: Required within one year after the effective date of this AD, unless previously accomplished. To prevent jamming of the flaps and reduction of airplane controllability, accomplish the following: (a) Replace the left- and right-hand wing flap track No. 4 forward support fittings in accordance with the Accomplishment Instructions of de Havilland Service Bulletin No. 7-27-37, dated October 28, 1981. (b) 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 (ACO), ANE-170, FAA, New England Region. 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. (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. (d) The replacement requirements shall be done in accordance with de Havilland Service Bulletin No. 7-27-37, dated October 26, 1981. 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 of Canada, Ltd., de Havilland Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, Renton, Washington; at the FAA, New England Region, New York Aircraft Certification Office, 181 S. 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 (39-8025, AD 91-18-21) becomes effective on October 15, 1991.
2024-20-07: The FAA is adopting a new airworthiness directive (AD) for various helicopters modified by certain supplemental type certificates (STCs) that approve the installation of an emergency float kit or an emergency float with a liferaft kit. This AD was prompted by the results of an accident investigation and subsequent reports of difficulty pulling the emergency float kit activation handle installed on the pilot cyclic. This AD requires repetitively inspecting the pull force on the float activation handle and for certain model helicopters, this AD also requires and replacing certain part-numbered float inflation reservoirs (reservoirs) and pull cable assemblies (cables) with other part-numbered reservoirs and cables. Finally, this AD prohibits installing certain part-numbered reservoirs and cables on specific helicopters. The FAA is issuing this AD to address the unsafe condition on these products.
90-12-04 R1: 90-12-04 R1 BOEING: Amendment 39-8668. Docket 93-NM-43-AD. Revises AD 90-12-04, Amendment 39-6621 which superseded AD 88-01-08, Amendment 39-5827. \n\n\tApplicability: Model 757 series airplanes, listed in Boeing Alert Service Bulletin 757-30A0013, Revision 6, dated March 25, 1993, certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent undetected failure of the anti-ice system which could ultimately result in unacceptable ice build-up on the wings or engine inlets, accomplish the following: \n\n\t(a)\tFor airplanes listed in Boeing Alert Service Bulletin 757-30A0013, Revision 5, dated September 7, 1989: Accomplish the requirements of paragraphs (a)(1) and (a)(2) of this AD. \n\n\t\t(1)\tWithin the next 300 hours time-in-service after February 4, 1988 (the effective date of AD 88-01-08, Amendment 39-5827), perform a functional test of the wing and engine cowl anti-ice control and indication system, in accordance with Section III, Part I of Boeing Alert Service Bulletin 757- 30A0013, Revision 5, dated September 7, 1989. Repeat this functional test thereafter at intervals not to exceed 300 hours time-in-service until the modification required by paragraph (a)(2) of this AD is accomplished. \n\n\tNOTE 1: Paragraph (a)(1) of this AD restates the requirements of AD 88-01-08, Amendment 39-5827, paragraph A. As allowed by the phrase, "unless accomplished previously," if the requirements of AD 88-01-08 have been accomplished previously, paragraph (a)(1) of this AD does not require that the initial inspection be repeated. \n\n\t\t(2)\tWithin the next 3,000 hours time-in-service after July 9, 1990 (the effective date of AD 90-12-04, Amendment 39-6621), modify and test the wing and engine cowl anti-ice control and indication system in accordance with Section III, Parts II, III, IV, V, VI, and VII, as applicable, of Boeing Alert Service Bulletin 757-30A0013, Revision 5, dated September 7, 1989; or Section III, Parts II, III, IV, V, VI, VII, and VIII, as applicable, of Revision 6, dated March 25, 1993. Accomplishment of this modification constitutes terminating action for the repetitive testing requirement of paragraph (a)(1) of this AD. \n\n\tNOTE 2: Paragraph (a)(2) of this AD restates the requirements of AD 90-12-04, Amendment 39-6621, paragraph B. As allowed by the phrase, "unless accomplished previously," if the requirements of AD 90-12-04 have been accomplished previously, paragraph (a)(2) of this AD does not require that the modification be repeated. \n\n\t(b)\tFor airplanes listed in Boeing Alert Service Bulletin 757-30A0013, Revision 6, dated March 25, 1993, that are not subject to paragraph (a) of this AD: Accomplish the requirements of paragraphs (b)(1) and (b)(2) of this AD. \n\n\t\t(1)\tWithin the next 300 hours time-in-service after the effective date of this AD, perform a functional test of the wing and engine cowl anti-ice control and indication system, in accordance with Section III, Part I, of Boeing Alert Service Bulletin 757-30A0013, Revision 6, dated March 25, 1993. Repeat this functional test thereafter at intervals not to exceed 300 hours time-in-service until the modification required by paragraph (b)(2) of this AD is accomplished. \n\n\t\t(2)\tWithin the next 3,000 hours time-in-service after the effective date of this AD, modify and test the wing and engine cowl anti-ice control and indication system in accordance with Section III, Parts II, III, IV, V, VI, VII, and VIII, as applicable, of Boeing Alert Service Bulletin 757-30A0013, Revision 6, dated March 25, 1993. Accomplishment of this modification constitutes terminating action for the repetitive testing requirement of paragraph (b)(1) of this AD. \n\n\t(c)\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operatorsshall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. \n\n\tNOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. \n\n\t(d)\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(e)\tThe tests and modifications shall be done in accordance with Boeing Alert Service Bulletin 757-30A0013, Revision 5, dated September 7, 1989, or Boeing Alert Service Bulletin 757-30A0013, Revision 6, dated March 25, 1993, as applicable. 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 98124-2207. Copies may beinspected 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. \n\n\t(f)\tThis amendment becomes effective on October 13, 1993.
2016-09-11: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and Model A340-200 and -300 series airplanes. This AD was prompted by reports that cracks were found on an adjacent hole of certain frames of the center wing box (CWB). This AD requires removing fasteners, doing a rototest inspection of fastener holes, installing new fasteners, oversizing the holes and doing rototest inspections for cracks if necessary, and repairing any cracking that is found. We are issuing this AD to detect and correct cracking on certain holes of certain frames of the CWB that could affect the structural integrity of the airplane.