Results
2017-25-04: We are superseding Airworthiness Directive (AD) 2014-22-08, which applied to all Airbus Model A318 and A319 series airplanes; Model A320-111, -211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2014-22-08 required revising the maintenance or inspection program to incorporate new or revised airworthiness limitation requirements. This new AD requires revising the maintenance or inspection program to incorporate new or revised airworthiness limitation requirements, and removes airplanes from the applicability. This AD was prompted by a determination that more restrictive maintenance instructions and airworthiness limitations are necessary. We are issuing this AD to address the unsafe condition on these products.
2007-23-12: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 707 airplanes and Model 720 and 720B series airplanes. This AD requires accomplishing an airplane survey to define the configuration of certain system installations, and repair of any discrepancy found. This AD also requires modifying the fuel system by installing lightning protection for the fuel quantity indication system (FQIS), ground fault relays for the fuel boost pumps, and additional power relays for the center tank fuel pumps and uncommanded on- indication lights at the flight engineer's panel. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent certain failures of the fuel pumps or FQIS, which could result in a potential ignition source inside the fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
93-06-06: 93-06-06 HAMILTON STANDARD: Amendment 39-8531. Docket No. 92-ANE-51. Applicability: Hamilton Standard Models 14RF-9, 14RF-19, and 14RF-21, and Models 14SF-5, 14SF-7, 14SF-11, 14SF-15, 14SF-17, 14SF-19, and 14SF-23 propellers, and Hamilton Standard-British Aerospace Model 6/5500/F-1 propellers installed on but not limited to Embraer EMB-120 and EMB-120RT; SAAB-SCANIA AB SAAB 340B; Aerospatiale ATR42-100, ATR42-300, ATR42-320, ATR72-101, ATR72-210; DeHavilland DHC-8-100, DHC-8-300, DHC-8-314; Construcciones Aeronauticas SA (CASA) CN-235 and CN-235-100; Canadair CL215T; and British Aerospace ATP airplanes. Compliance: Required as indicated, unless accomplished previously. To prevent loss of control of the propeller blade pitch due to propeller control unit (PCU) ballscrew quill wear, accomplish the following: (a) Within 10 hours time in service (TIS) after the effective date of this AD, for propeller assemblies equipped with titanium nitrided transfer tubes (identifiable by gold-colored spline area), remove the titanium nitrided transfer tubes from service, replace the PCU ballscrew quill with a new quill or a quill that has never been mated with a titanium nitrided transfer tube, and install an A-1 nitrided transfer tube (identifiable by a grey-colored spline area) that has been marked in accordance with the applicable SB listed in paragraph (c) of this AD. (b) Within 30 hours TIS after the effective date of this AD, for propeller assemblies equipped with an A-1 nitrided transfer tube and a PCU ballscrew quill that either has been mated to a titanium nitrided transfer tube, or that have no records showing to which transfer tube type the PCU ballscrew quill was mated, replace the PCU ballscrew quill with a new quill or a quill that has never been mated with a titanium nitrided transfer tube. (c) Within 60 days after the effective date of this AD, mark all A-1 nitrided transfer tubes with a new part number in accordance with the following Hamilton Standard Alert Service Bulletins (ASB), all dated October 27, 1992: ASB No. 14RF-21-61-A39, applicable to Hamilton Standard Model 14RF-21 propellers; ASB No. 14RF-9-61-A57, applicable to Hamilton Standard Model 14RF-9 propellers; ASB No. 14RF-19-61-A26, applicable to Hamilton Standard Model 14RF-19 propellers; ASB No. 14SF-61-A61, applicable to Hamilton Standard 14SF series propellers; and ASB No. 6/5500/F-61-A12, applicable to Hamilton Standard-British Aerospace Model 6/5500/F-1 propellers. (d) 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, Boston 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, Boston 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 Boston Aircraft Certification Office. (e) 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. (f) The replacement, and marking of transfer tubes shall be accomplished in accordance with the following service documents: Document No. Page Issue Date Hamilton Standard ASB No. 14RF-21-61-A39 1-7 Original October 27, 1992 Total pages: 7 Hamilton Standard ASB No. 14RF-9-61-A57 1-7 Original October 27, 1992 Total pages: 7 Hamilton Standard ASB No. 14RF-19-61-A26 1-6 Original October 27, 1992 Total pages: 6 Hamilton Standard ASB No. 14SF-61-A61 1-7 Original October 27, 1992 Total pages: 7 Hamilton Standard ASB No. 6/5500/F-61-A12 1-7 Original October 27, 1992 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 Hamilton Standard Division of United Technologies Corporation, One Hamilton Road, Windsor Locks, Connecticut 06096-1010. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, Massachusetts; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment supersedes AD T91-11-51 issued on May 22, 1991. (h) This amendment becomes effective on July 6, 1993.
93-21-06: 93-21-06 ISRAEL AIRCRAFT INDUSTRIES, LTD.: Amendment 39-8720. Docket 93-NM-96-AD. Supersedes AD 92-12-07, Amendment 39-8268, which superseded AD 90-10-08, Amendment 39-6597. Applicability: Model 1125 Westwind Astra series airplanes on which horizontal stabilizer aft spar splice fitting, part number 453005-509, has not been installed, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the horizontal stabilizer assembly, accomplish the following: (a) Within the next 50 hours time-in-service after July 31, 1992 (the effective date of AD 92- 12-07, amendment 39-8268), unless previously accomplished within the last 150 hours time-in-service prior to July 31, 1992, perform a visual inspection of the horizontal stabilizer hinge fitting to detect cracks in the outer lug root radius and fore and aft surfaces, and around the hinge pin head and nut of the lugs, in accordance with Astra Service Bulletin 1125-55-017, Revision 1, dated April 24, 1991. (1) If no cracks are found during this inspection, repeat the inspection at intervals not to exceed 200 hours time-in-service until the inspection required by paragraph (b) is accomplished. (2) If any crack is found during this inspection, prior to further flight, replace the hinge fitting in accordance with Astra Service Bulletin 1125-55-017, Revision 1, dated April 24, 1991. After replacement, repeat the visual inspection required by this paragraph at intervals not to exceed 200 hours time-in-service until the inspection required by paragraph (b) is accomplished. (b) Within 25 hours time-in-service after the effective date of this AD, unless previously accomplished within the last 75 hours time-in-service, perform a visual inspection of the horizontal stabilizer hinge fitting, including the horizontal stabilizer aft spar splice fitting, part number 453005-503 (aluminum), to detect cracks in the outer lug root radius and fore and aft surfaces, and around the hinge pin head and nut of the lugs, in accordance with the Accomplishment Instructions of IAI Service Bulletin 1125- 55-017, Revision 1, dated April 24, 1991. Accomplishment of this inspection terminates the requirements of paragraph (a) of this AD. (1) If no crack is found during this inspection, repeat the inspection at intervals not to exceed 100 hours time-in-service. (2) If any crack is found during this inspection, prior to further flight, replace the splice fitting, part number 453005-503 (aluminum), with an improved splice fitting, part number 453005- 509 (titanium), in accordance with procedures in the IAI Model 1125 Westwind Astra maintenance manual. Such replacement constitutes terminating action for the inspection requirements of this AD. (c) Within one year after the effective date of this AD, replace the splice fitting, part number 453005-503 (aluminum), with an improved splice fitting, part number 453005-509 (titanium), in accordance with the IAI Model 1125 Westwind Astra maintenance manual. Such replacement constitutes terminating action for the inspection requirements of this AD. (d) 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, Standardization Branch, ANM-113, 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, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (e) 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. (f) The inspections and replacements shall be done in accordance with Astra Service Bulletin 1125-55-017, Revision 1, 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 Astra Jet Corporation, Technical Publications, 77 McCullough Drive, Suite 11, New Castle, Delaware 19720. Copies may be inspected 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. (g) This amendment becomes effective on December 13, 1993.
2017-24-08: We are superseding airworthiness directive (AD) 2014-24-08 for all Rolls-Royce plc (RR) RB211-535E4-37, RB211-535E4-B-37, and RB211- 535E4-C-37 turbofan engines with certain low-pressure (LP) fuel filter- to-high-pressure (HP) fuel pump tube assemblies, or HP fuel pump-to- fuel flow governor (FFG) or FFG-to-HP pump inlet overspill return tube assemblies and flanged adaptor, installed. AD 2014-24-08 required replacing certain LP fuel filter-to-HP fuel pump tube assemblies. This AD retains the requirement in AD 2014-24-08 to remove the LP fuel filter-to-HP fuel pump tube, adds new compliance thresholds, and requires installation of new HP fuel pump-to-FFG and FFG-to-HP pump inlet overspill return tube assemblies and flanged adaptor. This AD was prompted by fuel leaks that have occurred at the flanged joints of the HP fuel pump-to-FFG tube assembly and FFG-to-HP pump inlet overspill return tube assembly. We are issuing this AD to correct the unsafe condition on these products.
2002-04-06: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 727 series airplanes, that requires repetitive inspections for cracking of the upper chord of the rear spar of the wing, and corrective action, if necessary. This action is necessary to find and fix such cracking, which could result in fuel leaking through the cracks, reduced structural integrity of the wing, and separation of the wing from the airplane. This action is intended to address the identified unsafe condition.
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.