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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.
81-23-02: 81-23-02 TELEDYNE CONTINENTAL MOTORS: Letter issued October 30, 1981. Applies to Teledyne Continental Motors Models TSIO-360-EB, S/N 311703 and 311704; LTSIO-360-EB, S/N 312685; TSIO-360- KB, S/N 315204, 315209 through 315259, 315262 through 315274, 315277, 315283, 315284, and 315323; LTSIO-360-KB, S/N 314195, 314204, 314208 through 314274, 314276, and 314277; and TSIO-360-GB, S/N 309600, 309601, 309603 through 309618, 309622 through 309627, 309629 through 309641 and 309655 aircraft engines. Compliance required prior to further flight after receipt of this letter. To prevent possible failure of the oil filter adapter gasket, accomplish the following: (a) Inspect the oil filter adapter (TCM P/N 641576) flange at the machined alternator relief cutout in accordance with the inspection procedure described in TCM Special Service Notice 10-81, dated October 19, 1981. (b) If the machined alternator relief cutout intrudes into the shoulder (no matter how little), replace the adapterTCM P/N 641576 with a serviceable part which meets the inspection criteria of TCM Special Service Notice 10-81. (c) Make appropriate maintenance record entries indicating compliance with this AD. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, P.O. Box 20636, Atlanta, Georgia 30320. Teledyne Continental Motors Special Service Notice 10-81, dated October 19, 1981, applies to this subject. This Airworthiness Directive becomes effective upon receipt.