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2020-04-01: The FAA is adopting a new airworthiness directive (AD) for all Pratt & Whitney (PW) PW1519G, PW1521G, PW1521GA, PW1524G, PW1525G, PW1521G-3, PW1524G-3, PW1525G-3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A model turbofan engines. This AD was prompted by reports of in-flight shutdowns due to oil leaking from the connection between the LP10 oil supply tube and the fuel oil cooler (FOC). This AD requires initial and repetitive gap inspections of the LP10 oil supply tube and the FOC and, if a gap is found, replacement of these parts. The FAA is issuing this AD to address the unsafe condition on these products.
83-07-16: 83-07-16 SHORT BROTHERS AND HARLAND, LTD.: Amendment 39-4618. Applies to Model SC-7 Series 3 (all serial numbers) airplanes certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD. To preclude looseness of either vertical fin accomplish the following: (a) Remove Access Panel Nos. T15, T16, and T17 from the vertical fins in accordance with Shorts Skyvan Maintenance Manual, Chapter 7-00, Page 6, Figure 4, and paragraph (A) (1) of Shorts Service Bulletin No. 55-53, Original Issue, dated June 25, 1979. (b) Apply 12-15 in-lbs torque to the 10-32 UNF bolts (one at a time) that attach the fins to the stabilizer (24 bolts in the front spar and 16 bolts in the rear spar). 1. If torque of 12-15 in-lbs can be applied to each bolt without rotating the bolt, replace Access Panel Nos. T15, T16, and T17 in accordance with Shorts Skyvan Maintenance Manual, Chapter 7-00, Page 6, Figure 4, and return the airplane to service. 2. If a bolt rotates with the application of 12-15 in-lbs of torque, remove each rotating bolt (one at a time) and inspect bolt hole for elongation. (i) If no elongation of the bolt hole is found, add additional washer under the bolt head or nut (maximum of 2 washers under the nut and 1 under the bolt head), apply 12-15 in-lbs torque to bolt and return airplane to service. NOTE: If less than 2 full threads protrude past nut after torquing, replace bolt with a bolt of the same type with a grip length increased by one over the original bolt grip length. (ii) If elongation of the bolt hole is found, reinstall bolts in accordance with paragraphs (b) 1 and 2 of this AD and within 200 hours time-in-service repair in accordance with instructions provided by Short Brothers Ltd., P.O. Box 241, Airport Road, Belfast BT3 9DZ and approved as an equivalent method of compliance in accordance with paragraph (e) of this AD. Replace Access Panel Nos. TI5, T16, and T17 in accordance with Shorts Skyvan Maintenance Manual, Chapter 7-00, Page 6, Figure 4, and return airplane to service. (c) The compliance times required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections and repairs concurrent with other scheduled maintenance of the airplane. (d) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (e) An equivalent method of compliance with this AD if used must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on April 14, 1983.
77-09-10: 77-09-10 PIPER AIRCRAFT CORP: Amendment 39-2892. Applies to models: PA-23-250 (6 place) S/Nos. 27-3837, 27-3944 to 27-4796 inclusive PA-24-260 S/Nos. 24-4783, 24-4804 to 24-5047 inclusive PA-30 S/Nos. 30-1717, 30-1745 to 30-2000 inclusive PA-31 and 31-300 S/Nos. 31-2 to 31-797 inclusive PA-31-350 S/Nos. 31-5001 to 31-5004 inclusive PA-31P S/Nos. 31P-1 to 31P-109 inclusive PA-39 S/Nos. 39-1 to 39-155 inclusive Compliance required within the next 100 hours in service after the effective date of this AD, unless already accomplished. (a) Modify the electric trim switch in accordance with instruction paragraph of Piper Service Bulletin No. 527, dated November 5, 1976, or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Upon request with substantiating data submitted through an FAA Maintenance Inspector, the compliance time specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment becomes effective May 12, 1977.
74-08-09: 74-08-09 TRANSPORT CATEGORY AIRCRAFT: Amendment 39-1818 as amended by Amendment 39-1917. Applies to all transport category aircraft having one or more lavatories equipped with paper or linen waste receptacles. NOTE: The following is a partial list of aircraft some or all models of which are type certificated in the transport category and have lavatories equipped with paper or linen waste receptacles: Boeing Models B-707, 720, 727, 737, and 747 Series; British Aircraft Corporation Model BAC-1-11; Convair Models CV-880 and 990 Series; McDonnell Douglas Models DC-8, 9, and 10 Series; Lockheed Model L-1011; Boeing Model B-377; Convair Models CV-580, 600, and 640 Series; Fairchild Model F-27; Fairchild-Hiller Model FH-227; Grumman Model G-159; Hawker Siddeley Model HS-748; Lockheed Models L-188 and 382 Series; Short Brothers and Harlin Model SC-7; Nihon Model YS-11; Fairchild Model C-82; Convair Models 240, 340, and 440 Series; Curtiss-Wright Model CW-46; Douglas Models DC-3, 4, 6, and 7 Series; Lockheed Model L-1049; and Martin Model M-404 aircraft. Compliance required as indicated, unless already accomplished. To prevent possible fires that could result from smoking materials being dropped into lavatory paper or linen waste receptacles: (a) Within 60 days after the effective date of this AD, or before the accumulation of any time in service on a new production aircraft after delivery, whichever occurs later, except that new production aircraft may be flown in accordance with Parts 21.197 and 21.199 to a base where compliance may be accomplished, accomplish the following: (1) Install a placard on each side of each lavatory door over the door knob containing the legible words "No Smoking in Lavatory" or "No Smoking" to indicate that smoking is prohibited in the lavatory. The signs must be of sufficient size and contrast and be located so as to be conspicuous to lavatory users. Note: A "No Smoking" symbol may be included on the placard.(2) Install a placard on or near each lavatory paper or linen waste disposal receptacle door containing the legible words "No Cigarette Disposal." (b) Within 30 days after the effective date of this AD, establish a procedure that requires that, not later than a time immediately after the "NO SMOKING" sign is extinguished following takeoff, an announcement be made by a crewmember to inform all aircraft occupants that smoking is prohibited in the aircraft lavatories; except that, if the aircraft is not equipped with a "No Smoking" sign, the required procedure must provide that the announcement be made prior to each takeoff. (c) Within 180 days after the effective date of this AD, or before the accumulation of any time in service on a new production aircraft after delivery, whichever occurs later, except that new production aircraft may be flown in accordance with Part 21.197 and Part 21.199 to a base where compliance may be accomplished, install a self-contained, removableashtray on or near the entry side of each lavatory door, except that one ashtray may serve more than one lavatory door if the ashtray can be seen readily from the cabin side of each lavatory door served. (d) Within 30 days after the effective date of this AD, unless already accomplished within 30 days prior to the effective date of this AD and, thereafter, at intervals not to exceed 1,000 hours time in service from the last inspection, accomplish the following: (1) Inspect all lavatory paper and linen waste receptacle enclosure access doors and disposal doors for proper operation, fit, sealing, and latching for the containment of possible trash fires. (2) Correct all defects found during the inspections required by subparagraph (d)(1). (e) Upon request of the operator, a principal FAA maintenance inspector, may adjust the 1,000 hour repetitive inspection interval specified in subparagraph (d)(1) of this AD to permit compliance at an established inspection period of the operator if the request contains data to justify the requested change in the inspection interval. Amendment 39-1818 became effective April 30, 1974. This Amendment 39-1917 becomes effective August 6, 1974.
91-01-01: 91-01-01 AIRBUS INDUSTRIE: Amendment 39-6845. Docket No. 90-NM-148-AD. Applicability: Model A320-111, -211, and -231 series airplanes; Serial Numbers 003 through 058, 060 through 067, 069 through 072, 074 through 083, and 085; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent loss of the emergency electrical generation system, accomplish the following: A. Within 150 days after the effective date of this AD, in Zone 125 of the avionics compartment, remove one GCU identified as 1XE part number (P/N) 520754, and install a modified GCU identified as 1XE P/N 520915, in accordance with Airbus Industrie Service Bulletin A320-24-1035, Revision 1, dated February 27, 1990. Following installation, perform an operational test of the Emergency Generation System, the Emergency Generator Control Unit from Centralized Fault Display System, and the Static Inverter, in accordance with the service bulletin. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6845, AD 91-01-01) becomes effective on January 28, 1991.
98-20-22: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300, A310, and A300-600 series airplanes, that requires repetitive visual inspections to detect cracked or broken door stop fittings on the fuselage frame of the forward passenger doors, and replacement of any cracked or broken fitting with a new fitting. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct cracked or broken door stop fittings of the forward passenger doors, which could result in failure of the door stop fittings, consequent reduced structural integrity of the door support structure, and sudden loss of cabin pressure in the passenger compartment.
2008-15-03: This amendment adopts a new airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model 369A, OH-6A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, and 369HS helicopters that requires repetitive tap inspections of each tail rotor (T/R) blade abrasion strip. This amendment is prompted by an incident in which an abrasion strip separated from a T/R blade. The actions specified by this AD are intended to prevent disbonding and subsequent separation of an abrasion strip from a T/R blade, which could result in vibration, loss of the T/ R, and subsequent loss of control of the helicopter.
87-25-08: 87-25-08 GULFSTREAM AMERICAN (FRAKES AVIATION): Amendment 39-5790. Applies to Model G-73 (Mallard) series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent jamming of the elevator control system, accomplish the following: A. Within 15 days after the effective date of this AD, visually inspect the overlapping contact surface between the elevator control torque tube arm, P/N 109410, and the elevator up stop bolt hex head, P/N G19-5-22, in accordance with Frakes Aviation Service Bulletin G-73-FA26, dated May 1, 1987 (hereinafter referred to as SB G-73-FA26), or later FAA-approved revisions. 1. If the elevator control torque tube arm is not overlapping the stop bolt hex head by one-half or more of the stop bolt hex head dimension, or if the center lines of the stop bolt hex head and the elevator control torque tube arm are not aligned within 1/8 inch (0.125 inch) side to side, prior to further flight install Frakes Aviation Stop Kit, P/N FA112723K1, in accordance with SB G-73-FA26, or later FAA-approved revision. 2. If the elevator control tube arm is overlapping the stop bolt hex head by one-half or more of the stop bolt hex head dimension, and if the center lines of the stop bolt hex head and the elevator control torque tube are aligned within 1/8 inch (0.125 inch) side to side, within the next 100 hours time-in-service install Frakes Aviation Stop Kit, P/N FA112723K1, in accordance with SB G-73-FA26, or later FAA-approved revisions. B. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the requirements of this AD. C. An alternate means of compliance, which provides an acceptable level of safety, may be used when approved by the Manager, Airplane Certification Branch, FAA, Southwest Region. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Frakes Aviation, Cleburne Airport, Route 3, Box 229-B, Cleburne, Texas 76031. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas. This amendment becomes effective January 19, 1988.
98-13-27: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires a one-time inspection to detect discrepancies of circuit breaker panels 10VE and 11VE; follow-on corrective actions; modification of the contact points; and installation of a high capacity fuse. This amendment also requires replacement of power relays 32HB and 36HB on relay panel 22VE with new parts. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent electrical short circuits of the contact points and power relays on the circuit breaker panels, which could result in increased risk of smoke and fire damage in the flight compartment.
2007-26-15: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: In some cases the electric motor of the spindle drive detached itself from the spindle drive, causing the powerplant to retract itself after engine shutdown. In another case the attachment fork on the spindle drive failed with the same consequences. We are issuing this AD to require actions to correct the unsafe condition on these products.