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84-24-53 R1: 84-24-53 R1 EMBRAER: Amendment 39-4975. Applies to Models EMB-110P1 and EMB- 110P2 airplanes certificated in any category. Compliance: Required within the next ten (10) hours time-in-service, unless previously accomplished within the last fifty (50) hours time-in-service. To preclude possible structural failure of the empennage assembly, accomplish the following: (a) Unless the structural reinforcements and rivet replacements specified in paragraphs (d) and (e) of AD 83-14-09 (Amendment 39-4692) have already been accomplished, repeat the inspections of the horizontal stabilizer front attachment and fuselage bulkhead 33 area in accordance with paragraph (a) of AD 83-14-09. (b) If loose rivets or cracks of any length are found during the inspections required by paragraph (a), prior to further flight, replace the rivets in accordance with paragraph (b) of AD 83- 14-09 and repair the cracks in accordance with paragraph (c)(2) of AD 83-14-09 notwithstanding the three inch crack criteria of that paragraph. (c) Visually inspect the following components for loose attachments, excessive wear, corrosion, cracks and structural deformation: (1) Forward horizontal stabilizer attachment, including the fuselage and stabilizer attach fittings and attachment hardware. (2) Aft horizontal stabilizer attachment, including the fuselage and stabilizer attach fittings, attach links and all attachment hardware. (3) All elevator to stabilizer hinge fittings, including all bearings/bushings and attachment hardware. (4) Security of elevator mass balance weight assemblies. (5) Left and right elevator Bellcrank assemblies and attachment hardware. (6) Left and right elevator torque tube assemblies and all attachment hardware. (7) Elevator trim tab hinges. (8) Elevator trim tab actuator, bearings, push rod assembly and all attachment hardware. (9) Elevator trim tab free play, measured at the trailing edge, shouldnot exceed airplane maintenance manual limits. (d) Prior to further flight, correct any unsatisfactory conditions found as a result of the inspections required by paragraph (c) in accordance with the airplane maintenance manual. (e) Report any unsatisfactory conditions, within 24 hours, to the FAA, Airframe Branch, Atlanta Aircraft Certification Office; Telephone (404) 763-7407. (Reporting authorized by OMB clearance number 21200056.) (f) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (g) An equivalent means of compliance with this AD may be used if approved by the Manager, FAA, Atlanta Aircraft Certification Office, 1075 Inner Loop Road, College Park, Georgia 30337. This amendment becomes effective on January 17, 1985, to all persons except those to whom it has already been made effective immediately by telegraphic AD T84-24-53 issued December 9, 1984.
75-01-01: 75-01-01 PRATT & WHITNEY AIRCRAFT: Amendment 39-2055 as amended by Amendment 39-2358. Applies to all Pratt & Whitney JT8D-1, -1A, -7, and -7A model turbofan engines. Compliance required as indicated. To prevent failure of the low turbine shaft spline accomplish the following: 1. Remove from service thin wall low turbine shafts not incorporating Pratt & Whitney Aircraft Service Bulletin 2452 (P/Ns 479796, 493412, 511215, 524958, 528365, 528366, 538951, 540354, 540355, 540452, 562503, 562504, 576305, 576312, 576313, 576314, and 587879) prior to the accumulation of 6700 cycles in service since new, or within the next 2000 cycles in service after January 8, 1975, whichever is later. 2. Inspect thin wall low turbine shafts incorporating Pratt & Whitney Aircraft Service Bulletin 2452 (P/Ns 540354-S/B2452, 540355-S/B2452, 540452-S/B2452, 676276, 676277, 676278, 676279, 676280, 676282, 676283, 676284, 676285, 676286, and 676287) for cracked splines in accordance with thePratt & Whitney Service Bulletin 2452, Revision 10, or later FAA approved revision, or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region, prior to the accumulation of 6700 cycles in service since last inspection or within the next 2000 cycles in service after January 8, 1975, whichever is later, unless already accomplished in accordance with Pratt & Whitney Service Bulletin No. 2452, Revision No. 10, or in accordance with the eddy current inspection of Pratt & Whitney Service Bulletin No. 2452, Revision Nos. 5 thru 9. Inspect thereafter at intervals not to exceed 6700 cycles in service from the last inspection. Remove shafts with cracks from service before further flight. 3. Inspect all No. 2 compressor hub splines plated per Pratt & Whitney Service Bulletins 2964 and 4193, in accordance with Pratt & Whitney Alert Service Bulletin 4357, Paragraphs IV.D.2 and IV.D.3, or later FAA approved revision, as applicable, when the low turbine shafts are removed or inspected in accordance with Paragraph 1 or 2 above. Remove hubs with plate peeling from service before further flight. 4. Inspect nonplated titanium No. 2 compressor hub splines, run with low turbine shafts requiring inspection under Paragraphs 1 or 2 of this AD, for taper wear in accordance with Pratt & Whitney JT8D manual, P/N 481672, Revision 76, Section 72-33-6, or later FAA approved revision, prior to the accumulation of 6700 cycles in service or within the next 2000 cycles in service after January 8, 1975, whichever is later, unless already accomplished. Inspect thereafter at intervals not to exceed 6700 cycles in service since last inspection. Remove hubs with taper wear in excess of .010 inch from service before further flight. The manufacturer's service bulletins identified and described in this directive 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 to Pratt & Whitney Aircraft, 400 Main Street, East Hartford, Ct. 06108. 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, MA 01803, and at Federal Aviation Administration Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this AD which includes the incorporated material in full is maintained by the Federal Aviation Administration at its headquarters in Washington D.C., and at the New England Regional Office in Burlington, MA. Upon submission of substantiating data through an FAA maintenance inspector by an owner or operator, the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust the compliance time. NOTE: Pratt & Whitney Alert Service Bulletin 4357 pertains to this subject. Amendment 39-2055 became effective January 8, 1975. This amendment 39-2358 becomes effective September 17, 1975.
2017-25-05: We are superseding Airworthiness Directive (AD) 2012-23-10, which applied to all Airbus Model A318 series airplanes; Model A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2012-23-10 required modifying the affected slide rafts. This AD retains the requirements of AD 2012-23-10. This AD also requires replacing each escape slide pack assembly having a certain part number with a new escape slide pack assembly. This AD was prompted by reports of the escape raft inflation system not deploying when activated due to the rotation of the cable guide in a direction that resulted in jamming of the inflation control cable. We are issuing this AD to address the unsafe condition on these products.
2017-25-06: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318 and A319 series airplanes; Model A320-211, -212, - 214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, - 211, -212, -213, -231, and -232 airplanes. This AD was prompted by reports of a vertical strut penetrating through the cabin floor during an emergency water landing and on airframe ground contact at certain speeds/accelerations. This AD requires modification of the fuselage structure at a certain frame. We are issuing this AD to address the unsafe condition on these products.
2002-04-01: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and C-9 series airplanes; Model MD-88 airplanes; and Model MD-90 airplanes, that currently requires a visual check to determine the part and serial numbers of the upper lock link assembly of the nose landing gear (NLG); repetitive inspections of certain upper lock link assemblies to detect fatigue cracking; and modification of the NLG. The existing AD also provides for terminating action for the repetitive inspections. This amendment requires, among other actions, expanding the applicability of the existing AD, revising compliance times; and adding new inspection requirements. This amendment is prompted by a report indicating that an NLG upper lock link fractured prior to landing and jammed against the NLG shock strut, restricting the NLG from fully extending. The actions specified by this AD are intended to prevent the upper lock link assembly fromfracturing due to fatigue cracking, and the NLG consequently failing to extend fully; this condition could result in injury to passengers and flight crew, and damage to the airplane.
2023-04-07: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a determination that the surface protection is missing between certain aluminum brackets and the struts to which they are attached in the flight deck air distribution system. This AD requires applying surface protection to the affected aluminum brackets and struts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits modifying an airplane using certain service information. The FAA is issuing this AD to address the unsafe condition on these products.
2017-25-03: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. This AD was prompted by a report of sparks and an electrical smell on the flight deck of a Model F28 Mark 0070 airplane. We are issuing this AD to address the unsafe condition on these products.
2002-04-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 F4-605R airplanes, that requires installation of external doublers at frames 29 and 33. The actions specified by this AD are intended to prevent fatigue cracking of certain circumferential joints, which could result in reduced structural integrity of the fuselage in the vicinity of the upper deck cargo door.
2002-03-09: This amendment adopts a new airworthiness directive (AD), that is applicable to Honeywell International Inc. (formerly AlliedSignal Inc. and Textron Lycoming) LTS101 series turboshaft and LTP101 series turboprop engines. This amendment requires a one-time visual inspection for surface finish and a one-time fluorescent penetrant inspection for cracks of certain impellers installed on LTS101 series turboshaft and LTP101 series turboprop engines. This amendment is prompted by a report of a machining discrepancy that may have occurred during manufacture of the affected impellers. The actions specified by this AD are intended to prevent impeller failure from cracks in the impeller back face area, which could result in an uncontained engine failure.
2023-04-04: The FAA is superseding Airworthiness Directive (AD) 2020-15- 20, which applied to certain Airbus SAS Model A350-941 and -1041 airplanes. AD 2020-15-20 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 2020-15- 20 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.