Results
2018-17-23: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by a report indicating that during a fleet survey on a retired Model 737 airplane, cracking was found common to the number 3 windshield assembly, aft sill web. This AD requires, at certain locations, repetitive high frequency eddy current (HFEC) inspections of the number 3 windshield assembly, aft sill web; and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
2018-16-11: We are adopting a new airworthiness directive (AD) for various Model 234 and Model CH-47D helicopters. This AD requires inspections of the pitch housing and revising the pitch housing retirement life. This AD was prompted by reports of cracking in the pitch housing lugs. The actions of this AD are intended to detect and prevent an unsafe condition on these products.
2017-17-16: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767 airplanes. This AD was prompted by a report of cracking of the vertical stiffener in the nose wheel well. This AD requires repetitive inspections of the nose wheel well bulkhead stiffener for any cracking, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
82-09-02 R1: 82-09-02 R1 ROLLS-ROYCE, LTD.: Amendment 39-4371 as amended by Amendment 39-4642. Applies to Rolls-Royce DART Mk. 506, 510, 511, 514, 525 through 532, 535, and variants series turboprop engines. Compliance is required as indicated, unless already accomplished. 1. Compliance for all affected DART engines except the Mk. 530 is based on an effective date of April 30, 1982. 2. Compliance for the DART Mk. 530 engines is based on an effective date of May 12, 1983. To prevent possible failure of the engine fuel manifold assembly connection flexible hose which could result in release of fuel within the nacelle and consequent loss of engine power and risk of fire, accomplish the following: Remove from service engine fuel manifold assembly No. 7 to No. 6 bulkhead connection hose, P/N RK38451A, Mod 1587, with identification tag bearing a manufacture/3,000 psi test date of "8.9.76." Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Manager, Aircraft Certification Division, FAA, New England Region, may adjust the compliance date specified in the AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the issuance for that operator. NOTE: Rolls-Royce, Ltd., DART Engine Alert Service Bulletin No. Da73-A75, dated February 16, 1982, refers to this subject. Amendment 39-4371 became effective April 30, 1982. This Amendment 39-4642 becomes effective May 12, 1983.
2018-14-05: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by reports of fire incidents of the auxiliary power unit (APU) inlet, which caused tail cone damage after an initial failed APU start followed by two or more in-flight APU start attempts. This AD requires modification of the APU electronic control unit (ECU) wiring harness. We are issuing this AD to address the unsafe condition on these products.
2018-11-06: We are adopting a new airworthiness directive (AD) for all Airbus Model A310-203, -221, -222, -304, -322, -324, and -325 airplanes. This AD was prompted by a design approval holder (DAH) evaluation indicating that the outer wing lower junction is subject to widespread fatigue damage (WFD). This AD requires modifying the fastener holes at certain locations, which includes related investigative actions and applicable corrective actions. We are issuing this AD to address the unsafe condition on these products.
81-07-05: 81-07-05 CANADAIR: Amendment 39-4067. Applies to all Canadair Models CL-44D4 and CL44J aircraft certificated in all categories with nose landing gear crossbeam, P/N 44-85082 or P/N 44-85082-2. Compliance required as indicated. A. To prevent failure of the nose landing gear crossbeam, accomplish the following: 1. Within the next 30 days after the effective date of this AD, unless already accomplished within the last 60 days, conduct the following inspections for cracks and corrosion: (a) Using dye penetrant and a 10-power glass, inspect the forward and aft external faces as detailed in paragraph 3.2 and shown in Figure 1 of Canadair Service Information Circular (SIC) No. 431-CL44, dated June 11, 1980, or an approved equivalent inspection. (b) Using eddy current procedure, inspect the pivot pin taper bore as detailed in paragraph 3.3 and shown in Figure 2 of SIC No. 431-CL44, or an approved equivalent inspection. 2. Within the next 65 hours in service or 30 days, whichever occurs first, after the initial inspection specified in paragraph A1, conduct a visual inspection of the forward and aft external faces as detailed in paragraph 3.1 as shown in Figure 1 of SIC No. 431-CL44, or an approved equivalent inspection. 3. The inspection specified in paragraph A2 shall be repeated at intervals not to exceed 65 hours in service or 30 days, whichever occurs first, from the previous visual inspection. The inspection specified in paragraph A1(a) shall be repeated at intervals not to exceed 650 hours in service or 90 days, whichever occurs first. The inspection specified in paragraph A1(b) shall be repeated at intervals not to exceed 1300 hours in service or 180 days, whichever occurs first. B. A cracked crossbeam must be replaced prior to further flight with a part of the same number or equivalent, or repaired by an approved method. An acceptable replacement part is a Britannia crossbeam, Messier P/N 200192-302, conforming to Aviation Traders (Engineering) Limited (ATL) Modification No. 44/094 and Drawing No. 78-41-039, in accordance with paragraph 5.3 of SIC No. 431-CL44. C. Remove any corrosion found in the inspection areas and reprotect the surface in accordance with instructions in paragraph 6.0 on SIC No. 431-CL44, or equivalent. D. All replacement or repaired crossbeams must be inspected for cracks immediately prior to installation, in accordance with paragraphs A1(a), A1(b), and A2, and at repetitive intervals in accordance with paragraph A3. E. The aircraft may be flown in accordance with FAR 21.197, to a base where the inspection or repair can be performed. F. Equivalent means of accomplishing the repairs, equivalent inspections, and parts must be approved by the Chief, Aircraft Certification Division, FAA Northwest Region. G. Upon submissions of substantiating data by an owner or operator, through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the inspection intervals specified in this AD. The manufacturer's specification and procedures 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 Canadair Limited, P.O. Box 6087, Montreal, Quebec, Canada H3C 3G9, Attention: Mr. W. Remington, Airworthiness Coordinator. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. This AD supersedes AD 74-26-03. This amendment becomes effective March 31, 1981.
80-16-01 R1: 80-16-01 R1 MESSERSCHMITT-BOLKOW-BLOHM GmbH: Amendment 39-3859 as amended by Amendment 39-3929. Applies to Model BO-105 series helicopters, serial numbers up to and including 450, which have engine cowling assemblies P/N's 105-62502, 105-62503, 105-62651, 105-62656, 105-62657 or 105-62658 installed, certificated in all categories. Compliance required prior to accumulation of 100 hours time in service after the effective date of this AD, or before November 15, 1980, whichever occurs later. To assure the proper application of the fire protection paint and compliance with airworthiness requirements accomplish the following, unless already accomplished: (a) (1) Remove the engine cowling; and (2) Inspect for the presence of fire protection paint between the cowling and the asbestos fabric in accordance with paragraph A of Part 2, "ACCOMPLISHMENT INSTRUCTIONS," of Messerschmitt-Bolkow-Blohm Service Bulletin No. 60-46, dated August 20, 1979 (hereinafter referred to as the Service Bulletin), or an FAA-approved equivalent. (b) If as a result of the inspection required in paragraph (a)(2) of this AD, no evidence of the presence of fire protection paint between the engine cowling and the asbestos fabric is found. (1) Replace asbestos fabric if heat damage or brittleness are present in accordance with paragraph 2.B of "ACCOMPLISHMENT INSTRUCTIONS," of the Service Bulletin, or an FAA-approved equivalent; and (2) Return the engine cowling assembly to service. (c) If as a result of the inspection required in paragraph (a)(2) of this AD, evidence of the presence of fire protection paint between the engine cowling and the asbestos fabric is found, comply with the following in accordance with paragraph B of Part 2, "ACCOMPLISHMENT INSTRUCTIONS", of the Service Bulletin, or an FAA-approved equivalent - (1) Remove the asbestos lining and install new asbestos lining; (2) Apply fire protection paint and top lacquer to the asbestos lining; and (3) Apply two coats Wiedokoll fire protection paint N6582. (d) In accordance with FAR 21.197 and 21.199, the helicopter may be flown to a base where the repairs required by this AD may be accomplished. (e) Before release to service of any engine cowling assemblies held as spares to which this AD is applicable, accomplish the inspection required in paragraph (a)(2) of this AD, and comply with paragraph (b) or (c) of this AD, as appropriate. (f) For purposes of this AD, an FAA-approved equivalent must be approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. Amendment 39-3859 became effective August 11, 1980. This Amendment 39-3929 becomes effective September 19, 1980.
2018-07-13: We are adopting a new airworthiness directive (AD) for certain Textron Aviation Inc. Models 510, 680, and 680A airplanes equipped with certain part number brake assemblies. This AD was prompted by a report that brake pad wear indicator pins were set incorrectly, which could lead to brake pad wear beyond the acceptable limits without indication. This AD requires inspection of the brake pad wear indicator pins and replacement of the brake assembly if any pin is set incorrectly. We are issuing this AD to address the unsafe condition on these products.
63-24-04: 63-24-04 VERTOL: Amdt. 648 Part 507 Federal Register November 27, 1963. Applies to All Model 107-II Helicopters, Serial Numbers 2 and Up. Compliance required before further flight and every 120 hours' time in service thereafter, except that compliance for spare mix and aft transmission assemblies shall be prior to installation on certificated aircraft. As a result of a fatigue failure of the aft rotor transmission quill shaft, P/N 107D2067-1, accomplish the following: (a) Remove aft transmission assembly P/N 107D2010, separate mix box P/N 107D2003 and inspect the mix box and aft transmission in accordance with Vertol Service Bulletin No. 107-113 dated October 28, 1963. Mix box or aft transmission assemblies which exceed the envelope of tolerances established in Figure 2 of Vertol Service Bulletin No. 107-113 dated October 28, 1963, shall be replaced before further flight. (b) Remove the quill shaft in accordance with the 107-5 Overhaul Manual, Chapter 62-10-2. (1) Retire from service all quill shafts P/N 107D2067-1 with a total time in service of 120 hours or more. (2) Quill shafts with less than 120 hours' total time in service may be continued in service until the accumulation of 120 hours provided the shafts satisfactorily pass the inspection specified in Vertol Service Bulletin No. 107-113 dated October 28, 1963. Replace before further flight quill shafts which are cracked or which have a wear step on the flank of the spline. (c) Inspect the internal splines of the input pinion and collector gears for wear. Replace before further flight gears which have a wear step on the flank of the spline. (d) Inspect holes in oil jets P/N 107D2268-1 and P/N 107D2214-1 to determine that they are free and clear. (e) As an alternative means of compliance with this directive, the following may be accomplished: (1) Install the tapered gasket seal type shim, P/N 107DS218-3 between the mixbox and aft transmissionin place of the existing gasket seal, and replace the aft transmission mounting lug bushings with new eccentric type bushings in accordance with Vertol Service Bulletin No. 107-182 dated October 7, 1964. (2) Modify the aft transmission lower case for new quill shaft lubrication in accordance with Part II of Vertol Service Bulletin NO. 107-182. This involves discarding the P/N 107D2214-1 plug jet, adding two higher capacity screened type jets and altering the P/N 107D2268-1 oil jet. (3) During reassembly of the transmission following the rework described in (1) and (2), the gear box inspections specified in Parts I and II of Vertol Service Bulletin No. 107- 182 shall be accomplished. These inspections shall include quill shaft lubrication inspection, gear box oil flow check, bearing pre-load, and back lash check, and gear box mating surface and pilot diameter dial indicator check. Quill shafts which have accumulated prior service time up to a maximum of 120 hours, may be installed for further service after a magnaglo and wear inspection in accordance with Vertol Service Bulletin No. 107-182. (4) Reidentify the aft transmission assembly, sub assemblies, and components in accordance with Part II of Vertol Service Bulletin No. 107-182. (f) Upon completion of all modifications and reidentification of gearbox units as described in (e), the 120-hour quill shaft retirement life and repetitive inspections required by (a), (b), (c), and (d) of this AD are no longer required. (Vertol Service Bulletin No. 107-113 dated October 28, 1963, and NO. 107-113A dated November 22, 1963, cover (a), (b), (c), and (d) of this AD. Vertol Service Bulletin No. 107-182 dated October 7, 1964, covers (e)). This directive effective upon publication in the Federal Register to all persons except those to whom it was made effective immediately by telegram dated November 1, 1963. Revised October 15, 1964.
70-07-03: 70-07-03 BELL: Amdt. 39-962. Applies to Model 206A Helicopters with transmissions incorporating Planetary Gear Support Spider, P/N 206-040-041-1. Compliance required as indicated: a. Planetary Gear Support Spiders P/N 206-040-041-1, with less than 450 hours' time in service on the effective date of this airworthiness directive must be removed from service prior to accumulating 500 hours' time in service. b. Planetary Gear Support Spiders, P/N 206-040-041-1, with more than 450 hours' time in service on the effective date of this airworthiness directive must be removed from service within 50 hours' time in service after the effective date of this directive. c. Retired Planetary Gear Support Spiders may be replaced with either the redesigned, heavy duty, Planetary Gear Support Spider P/N 206-040-080-3, using redesigned Shafts, P/N 206-040-043-5 (three required) in lieu of Shafts, P/N 206-040-043-3, or a serviceable Planetary Gear Support Spider, P/N 206-040-041-1, with less than 450 hours' total time in service. This latter item must be removed prior to accumulating 500 hours' total time in service. Removal and replacement is to be accomplished in accordance with the Maintenance and Overhaul Instructions for the Bell Model 206A helicopter or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Southwest Region. (Bell Helicopter Service Bulletin No. 206A-14, Revision B, dated 1-23-70, pertains to this subject.) This amendment becomes effective May 1, 1970.
79-20-03: 79-20-03 AVCO LYCOMING DIVISION: Amendment 39-3567. Applies to LTS101-600A, -600B, -600A-2, -650A-2, and -650B-1A turboshaft and LTP101-600, -600A, and -600A-1A turboprop engines. Compliance required prior to further flight, unless already accomplished. To prevent failure of the fuel control and fuel pump and oil pump drive gears accomplish the following: 1. LTS101 turboshaft model engines: Remove from service engine fuel control and fuel pump and oil pump and oil pump accessory drive gears, both P/N 4-081-080-04, and replace with gears, both P/N 4-081-080-05. Avco Lycoming Division Alert Notice, 3V-W733, dated July 31, 1979, refers to this subject. 2. LTP101 turboprop model engines: a. Remove from service engine fuel control and fuel pump accessory drive gears, P/N 4-083-020-01, and replace with P/N 4-083-020-02 gear. b. Remove from service engine oil pump accessory drive gear, P/N 4-081-080-02, and replace with P/N 4-081-080-06 gear. NOTE: Issuance of special flight permits in accordance with FAR Part 21.197, not to exceed 2 additional hours in service, is authorized. The manufacturer's Alert Notice identified and described in this directive is 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 this document from the manufacturer may obtain copies upon request to Customer Service Department, Avco Lycoming Division, 550 South Main Street, Stratford, Connecticut 06514. This document may also be examined at Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. This amendment becomes effective on September 26, 1979.
2017-25-10: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by a report indicating that wear of the bearing plate slider bushings could cause disconnection of certain elevator hinges, which could excite the horizontal stabilizer under certain in-flight speed/altitude conditions and lead to degradation of the structure. This AD requires repetitive inspections and checks of certain elevator hinges and related components, repetitive replacements and tests of the bearing plate, and related investigative and corrective actions, if necessary. We are issuing this AD to address the unsafe condition on these products.
60-10-02: 60-10-02 BRANTLY: Amdt. 151 Part 507 Federal Register May 12, 1960. The AD published in the Federal Register as Amendment 143 was superseded by the following: Applies to All B-2 Helicopters With 248-40 and 248-46 Main Rotor Blades Installed. Compliance required as indicated. The retirement time on 248-40 and 248-46 blades is increased from 50 hours of time in service specified in Amendment 143 of Part 507, to 500 hours of time in service, provided the following inspection is performed prior to flight subsequent to each refueling: (a) (1) Visually inspect upper and lower skin for cracks in the vicinity of rivet heads on the inboard one-third of the outboard main rotor blades. (2) Blades found with more than one crack or with a single crack exceeding one inch in length must be replaced prior to further flight. (3) Blades found with a single crack of one inch or less in length must be stop-drilled with a 1/8 (0.125) inch diameter drill prior to further flight. Revised March 10, 1961.
62-17-06: 62-17-06 PRATT & WHITNEY: Amdt. 470 Part 507 Federal Register August 1, 1962. Applies to All JT3C-12 Turbojet Engines. Compliance required as indicated. To preclude fatigue cracking in the rear face of the P/N 359708 eighth stage compressor rotor disc, accomplish the following: (a) For discs previously inspected by the procedure described in paragraph (c), reinspect in accordance with paragraph (c) every 90 hours' time in service from the last inspection. (b) For discs not previously inspected by the procedure described in paragraph (c), inspect in accordance with paragraph (c) as follows: (1) Inspect discs with 1,000 or more hours' time in service within the next 90 hours' time in service and every 90 hours' time in service thereafter. (2) Inspect discs with less than 1,000 hours' time in service prior to the accumulation of 1,090 hours' time in service and every 90 hours' time in service thereafter. (c) Incorporate an inspection hole and plugin the compressor case and eighth stage stator shroud in accordance with Pratt & Whitney Aircraft letter dated June 21, 1962, and its attached sketch number L-53852. Using an American Cystoscope Markers, Inc. Model B-175-AS-15 or FAA approved equivalent viewing instrument inserted through this hole, inspect each eighth stage compressor rotor disc rear blade dovetail area and the entire circumferential area of the eighth stage disc spacer for possible cracks. If any crack indications are found, remove the engine prior to further flight and disassemble for confirmation of the indications. Replace cracked discs. (d) Remove all eighth stage compressor rotor discs P/N 359708 from further service after 4,800 hours' time in service. (e) Upon request of the operator, an FAA Maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection intervals specified in this AD to permit complianceat an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. (Pratt & Whitney Aircraft telegraphic message dated June 13, 1962, to Eastern Air Lines and Pratt & Whitney Aircraft letter dated June 21, 1962, and attached sketch L-53852 to Eastern Air Lines covers the same subject.) This directive effective August 1, 1962. Revised February 20, 1963.
2017-22-08: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2C10 (Regional Jet Series 700, 701, & 702), Model CL-600-2D15 (Regional Jet Series 705), Model CL-600-2D24 (Regional Jet Series 900), and Model CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a report indicating that a number of rubber bull gear (RBG) wheels installed in the horizontal stabilizer trim actuator (HSTA) were manufactured using an incorrect material specification. This AD requires replacement of the affected RBG wheels. We are issuing this AD to address the unsafe condition on these products.
81-25-03: 81-25-03 McDONNELL DOUGLAS: Amendment 39-4271. Applies to McDonnell Douglas Model DC-9-10, -20, -30, -40, -50, and -80 series airplanes, including C-9A, C-9B, and VC-9C airplanes, certificated in all categories. Compliance required within six months from the effective date of this AD, unless already accomplished. To assure that proper windshield heat generation is available for bird impact protection and anti-ice functions on aircraft fuselage numbers 894 through 1021 and on aircraft that have had left, center, or right windshield panels replaced since November 1, 1978, accomplish the following: \n\n\tA.\tInspect windshield panels to determine manufacturer and year of manufacture. Windshield panels may be identified by the manufacturer's logo "PPG" or "LOF" in large capital letters with part number, specification, and serial number adjacent to logo. These are located at the top of the panel on the left and right-hand windshield panels, and at the bottom or top of the center windshield panel. \n\n\t\t1.\tPanels manufactured by Libbey Owens Ford (LOF), no further action is required. \n\n\t\t2.\tPanels manufactured by PPG Industries: \n\n\t\t\ta.\tDetermine the year of manufacture, which is contained in the serial number. Serial number samples are shown below: \n\n\t\t\t\t8-H-10-20-220-315 (first digit indicates year of manufacture, 1978; third digit indicates month, October) \n\n\t\t\t\t9-H-5-21-315-373 (first digit indicates year of manufacture, 1979; third digit indicates month, May) \n\n\t\t\t\t0-H-4-6-219-215 (first digit indicates year of manufacture, 1980; third digit indicates month, April) \n\n\t\t\t\t1-H-3-6-317-212 (first digit indicates year of manufacture, 1981; third digit indicates month, March) \n\n\t\t\tb.\tWindshield panels with an October 1978 or prior manufacturing date coded, or January 1981 or subsequent manufacturing date coded, no further action is required. \n\n\t\t\tc.\tAircraft with less than 200 flight hours since new or on aircraft with less than 200 flight hours onreplacement panel(s), accomplish the following heating element resistance check on PPG November 1, 1978, through December 31, 1980, date coded windshield panels: \n\n\t\t\t\t(1)\tOpen anti-ice circuit breaker on lower electrical panel center for windshield to be checked. \n\n\t\t\t\t(2)\tDisconnect electrical connector from windshield panel to be checked. \n\n\t\t\t\t(3)\tUsing an ohmmeter, check resistance between Pins L and P at receptacle on left (right) windshield panel. Resistance reading should measure 61.2-82.8 ohms. \n\n\t\t\t\t(4)\tUsing an ohmmeter, check resistance between Pins E and G at receptacle on center windshield panel. Resistance should measure 67.5-92.5 ohms. \n\n\t\t\t\t(5)\tIf windshield resistance is: \n\n\t\t\t\t\t(a)\tWithin tolerance on all three panels, aircraft may be continued in service, and panels must be repetitively inspected at 50-hour intervals until the accumulation of 200 flight hours. \n\n\t\t\t\t\t(b)\tWithin tolerance after the accumulation of 200 flight hours, no further actionis required. \n\n\t\t\t\t(6)\tIf resistance is out of tolerance on one or more of the three windshield panels: \n\n\t\t\t\t\t(a)\tCenter panel out of tolerance, install the following placard in full view of the pilot: "Do Not Exceed 260 kts IAS Below 10,000 Feet Altitude." \n\n\t\t\t\t\t(b)\tOnly side panel(s) out of tolerance, install the following placard in full view of the pilot: "Do Not Exceed 285 kts IAS Below 10,000 Feet Altitude." \n\n\t\t\t\t\t(c)\tIf windshield resistance of any panel, left, right, or center is greater than 130 ohms, install the following placard in full view of the pilot: "Flight into known icing conditions is prohibited." If left (right) windshield panel(s) resistance is 82.9 to 130 ohms, and/or center windshield panel resistance is 92.6 to 130 ohms, the panel(s) must be repetitively inspected at 50-hour intervals until the accumulation of 200 flight hours to ascertain that resistance remains at or below 130 ohms. After the accumulation of 200 flight hours, the repetitive inspection interval can be extended to 1,500 flight hours. \n\n\t\t\t\t\t(d)\tThe above restrictions can be removed when the out-of-tolerance panel(s) is/are replaced with panel(s) manufactured by LOF or any PPG manufactured panel(s) with a date code other than November 1, 1978, through December 31, 1980. \n\n\t\t\t\t(7)\tReconnect electrical connector to windshield panel and close circuit breakers. \n\n\t\t\td.\tFor November 1, 1978, through December 31, 1980, date coded windshield panels which have over 200 flight hours, accomplish the following: \n\n\t\t\t\t(1)\tPerform heating element resistance check, as outlined in paragraphs c(1) through c(4). If windshield resistance is within tolerance on panel(s), reconnect electrical connector to panel(s). No further action is required. \n\n\t\t\t\t(2)\tIf resistance is out of tolerance on any of the three panels, accomplish the instructions as outlined under paragraph c(6). \n\n\tB.\tAlternate inspections, repairs, or other action to be accomplished on or after the effective date of this AD, which provide an equivalent level of safety, may be used when approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA Northwest Mountain Region. \n\n\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. \n\n\tThis amendment becomes effective January 4, 1982.
64-16-05: 64-16-05 LYCOMING: Amdt. 765 Part 507 Federal Register July 10, 1964. Applies to O-320, O-340, O-360 and O-540 Series Engines Equipped With AC Fuel Pumps, AC 5623-467 (Lycoming P/N 74082), AC 5656880 (Lycoming P/N 74082) and AC 6440152 (Lycoming P/N 74798), and to IO-320-B1A, IO-360-A1A, -B1B, HIO-360-B1A, -B1B and IO-540-C-B5 Engines Equipped With AC Fuel Pumps, AC 5623466 (Lycoming P/N 73973) and AC 5656696 (Lycoming P/N 73870), Except for Recent Production Engines and Remanufactured Engines Listed in Lycoming Service Bulletin No. 298, Which Have Already Incorporated the Modification. Compliance required within 25 hours' time in service after the effective date of this AD unless already accomplished. To preclude the possibility of engine oil being drained overboard as a result of oil seal failure in AC light weight fuel pumps, modify AC pumps with part numbers listed herein in accordance with the instructions contained in Lycoming Service Bulletin No. 298. This directive effective July 10, 1964.
2017-21-07: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes. This AD was prompted by a report of reduction of the de-icing performance of the pitot probe over time that could remain hidden to the flight crew. This [[Page 48907]] AD requires repetitive detailed inspections of the pitot probe heater insulation resistance, and replacement of the pitot probe heater if necessary. We are issuing this AD to address the unsafe condition on these products.
60-18-01: 60-18-01 VICKERS: Amdt. 196 Part 507 Federal Register August 23, 1960. Applies to All Viscount 745D and 810 Series Aircraft. Compliance required as indicated. (It will be necessary for operators to maintain a record of flights to ascertain compliance with this AD. If past records are unavailable, the number of flights prior to this AD may be estimated.) As a result of failures of the trunnion attaching the nose gear retraction jack to the oleo leg, it is necessary to limit the time in service of the various parts forming the attachments of the retraction jack. The following parts must be replaced upon accumulating the specified total time in service: Retirement Time Part 745D aircraft flights 810 Series aircraft flights Trunnion P/N 60925-525 300 * Trunnion P/N 70126-97 20,000 20,000 Trunnion P/N 70126-651 15,000 15,000 Trunnion P/N 70126-661 20,000 20,000 Trunnion P/N 74426-25 300 300 Pin P/N 60926-529 4,000 4,000 Pin P/N 70026-25 20,000 20,000 Pin P/N 70126-659 20,000 20,000 Attachment Bolt P/N 70126-137 1,000 * Attachment Bolt P/N 70126-187 20,000 20,000 Attachment Bolt P/N 74426-23 20,000 20,000 Cylinder P/N 70026-1 30,000 * Cylinder P/N 70726-41 30,000 30,000 Ram P/N 70026-5 30,000 30,000 Fork End P/N 70026-7 20,000 20,000 End Nut P/N 70026-9 20,000 20,000 * Not applicable. (Vickers-Armstrongs Co. PTL 161 Issues 5 and 6 (for 700 Series) and PTL 22 Issues 5 and 6 (for 800/810 Series) cover this subject.) This supersedes AD 58-09-04. This amendment shall become effective 30 days after date of its publication in the Federal Register. Revised November 8, 1960.
2017-18-20: We are adopting a new airworthiness directive (AD) for The Boeing Company Model 707 airplanes equipped with a main cargo door (MCD). This AD was prompted by analysis of the cam support assemblies of the MCD that indicated the repetitive high frequency eddy current (HFEC) inspections required by the existing maintenance program are not adequate to detect cracks before two adjacent cam support assemblies of the MCD could fail. This AD requires repetitive ultrasonic inspections for cracking of the cam support assemblies of the MCD, and replacement if necessary. We are issuing this AD to address the unsafe condition on these products.
61-14-04: 61-14-04 CONVAIR: Amdt. 302 Part 507 Federal Register July 7, 1961. Applies to All Model 22 (880) Series Aircraft. Compliance required as indicated. One instance has been reported where the rivets attaching the forward rod end P/N 22- 04442-1, to the rudder flight tab rod P/N 22-46257, were not installed. This resulted in the rod end P/N 22-04442-1, becoming separated from the tab rod P/N 22-46257, with ensuing loss of the rudder flight tab control. The effects of this malfunction on operational safety is such as to require accomplishment of the following: (a) Prior to further flight unless already accomplished in accordance with Convair Alert Service Bulletin 27-40 dated June 14, 1961, inspect rod P/N 22-46257 and rod end P/N 22- 04442-1 to insure that they are attached by two AN 435 MC rivets per Convair Drawing 22- 46257. (b) If the rivets in paragraph (a) are not installed, rod end P/N 22-04442-1 shall be attached to rod end P/N 22-46257 per Convair Alert Service Bulletin 27-40 dated June 14, 1961, or FAA approved equivalent, prior to further flight. (c) Rod end assemblies attached with NAS 464-3 bolts must be replaced within 250 hours' time in service on bolt by parts complying with Convair Drawing 22-46257. (Convair Alert Service Bulletin 27-40 covers this same subject.) This directive becomes effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated June 16, 1961.
2017-19-24: We are superseding Airworthiness Directive (AD) 2014-26-10, which applied to all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2014-26-10 required revising the maintenance or inspection program to incorporate maintenance requirements and airworthiness limitations. This new AD requires revising the maintenance or inspection program, as applicable, to incorporate new or revised airworthiness limitation requirements. 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.
82-16-10: 82-16-10 PRATT & WHITNEY AIRCRAFT: Amendment 39-4417. Applies to all JT9D-20 engines installed in wing positions on DC-10-40 aircraft. Compliance required on installed engines prior to March 31 1984, unless already accomplished. To preclude "B" flange separation under adverse conditions, rework fan exit case assembly, incorporate riveted segmented strengthening plates along with improved "B" flange attachment hardware, and reidentify components in accordance with Pratt & Whitney JT9D-20 Service Bulletin No. 5335, dated September 3, 1981, or later revision approved by the Chief, Engine Certification Branch, FAA, New England Region. NOTE: Rework, replacement, and addition of various airframe brackets are necessary to ensure compatibility with the flange modifications specified in Pratt & Whitney Aircraft Service Bulletin No. 5335. All persons affected by this directive who have not already received the referenced service bulletin from the manufacturer may obtaincopies upon request to Pratt & Whitney Aircraft, Division of United Technologies Corporation, 400 Main Street, East Hartford, Connecticut 06108. This document may also be examined at Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. A historical file on this AD which includes the material in full is maintained by the FAA at the New England Region Office. This amendment becomes effective on August 16, 1982.
2017-19-13: We are superseding Airworthiness Directive (AD) 2001-16-01, which applied to certain Airbus Model A330-301, -321, -322, -341, and - 342 airplanes, and certain Model A340 series airplanes; and AD 2014-17- 06, which applied to all Airbus Model A330-200 series airplanes, Model A330-200 Freighter series airplanes, and Model A330-300 series airplanes. AD 2001-16-01 required inspections for cracking of the aft cargo compartment door, and corrective action if necessary. AD 2014-17- 06 required revising the maintenance or inspection program, as applicable, to incorporate structural inspection requirements. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new or revised airworthiness limitation requirements; and removing 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 onthese products.