Results
85-16-08: 85-16-08 SHORT BROTHERS LTD.: Amendment 39-5101. Applies to Model SD3-60 airplanes as listed in Short Brothers Ltd. Service Bulletin SD360-53-11, Revision 1, dated November 1984, certificated in any category. Compliance is required within twelve months after the effective date of this AD, unless previously accomplished. To prevent structural failure under ditching conditions, accomplish the following: A. Install Cherrymax rivets in the bottom section of fuselage frame 475 in accordance with Short Brothers Ltd. Service Bulletin SD360-53-11, Revision 1, dated November 1984. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. C. 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 inspections and/or modifications required by this AD. This amendmentbecomes effective August 22, 1985.
99-19-40: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires a detailed visual inspection to detect damage to the terminal lugs on the 12XC and 15XE connectors and the mounting lugs on the 15XE connector; and repair or replacement of the terminal lugs or the 15XE connector with new parts, if necessary. This amendment is prompted by the issuance of a mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct broken terminal and mounting lugs on the 15XE and 12XC connectors in the 101VU panel in the avionics compartment, which could result in loss of electrical power from the standby generator.
2020-04-18: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-941 airplanes. This AD was prompted by reports indicating premature aging of certain chemical oxygen generators. This AD requires repetitively removing the affected chemical oxygen generators and replacing them with serviceable parts, 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.
79-11-01: 79-11-01 SHORT BROTHERS LIMITED: Amendment 39-3476. Applies to Model SD3-30 airplanes, S/N's 3003 through 3017, certificated in all categories. Compliance is required prior to the accumulation of 6000 total landings or prior to the accumulation of 25 landings after the effective date of this AD, whichever occurs later, unless already accomplished. To prevent fatigue failure of the bolts, P/N A111-5-G (10 places) and A111-5-J (2 places), attaching the engine support tube brackets to the engine ring, replace the bolts and associated hardware with new bolts, P/N MS. 21250-05008 (10 places) and MS. 21250-06008 (2 places), and associated hardware in accordance with Section 2, "ACCOMPLISHMENT INSTRUCTIONS," of Short Brothers Limited Service Bulletin No. SD3-71-04, dated February 14, 1978, or an FAA-approved equivalent. This amendment becomes effective June 25, 1979.
2008-04-17: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: Several cases have been reported where the pilot, co-pilot or observer utility light system has failed, resulting in a burning smell within the cockpit. An investigation has revealed that, due to the orientation and location of the carbon molded potentiometers used to control the intensity of the light, the potentiometers can fail and overheat in such a way that burning of the ceiling panel and the associated insulation blanket could occur. This could lead to the presence of smoke in the cockpit, requiring that the pilots carry out the appropriate emergency procedure. We are issuing this AD to require actions to correct the unsafe condition on theseproducts.
87-15-07: 87-15-07 BELL HELICOPTER TEXTRON, INC.: Amendment 39-5643. Applies to Model 222, 222B, and 222U helicopters, certified in any category, with flapping bearing P/N 222-310-114-003/-105 installed. Compliance is required as indicated unless already accomplished. Compliance schedules required on page 1 of BHTI Alert Service Bulletins (ASB) Nos. 222-86-39, Rev. A and 222U-86-14, Rev. A are not required by this AD. To prevent failure of the M/R flapping bearing, accomplish the following: (a) Within the next 25 hours time in service after the effective date of this AD, perform Part I of the "Accomplishment Instructions" of BHTI ASB No. 222-86-39, Rev. A, dated January 14, 1987, for Model 222 and 222B helicopters and ASB No. 222U-86-14, Rev. A, dated January 14, 1987, for the Model 222U helicopter. If a crack is detected during the inspections, replace the M/R flapping bearing before further flight. (b) Within the next 100 hours time in service after the effective date of this AD, perform Part II of the "Accomplishment Instructions" of BHTI ASB No. 222-86-39, Rev. A, dated January 14, 1987, for the Model 222 and 222B helicopters and ASB No. 222U-86-14, Rev. A, dated January 14, 1987, for the Model 222U helicopters. (c) Comply with Part III of the "Accomplishment Instructions" of BHTI ASB No. 222-86-39, Rev. A, dated January 14, 1987, for the Model 222 and 222B helicopters and ASB No. 222U-86-14, Rev. A, dated January 14, 1987, for the Model 222U helicopter on the effective date of this AD. (d) Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Manager, Helicopter Certification Branch, Southwest Region, Department of Transportation, Federal Aviation Administration, Fort Worth, Texas 76193-0170. The above procedures shall be done in accordance with BHTI ASB Nos. 222-86-39, Rev. A, dated January 14, 1987, or 222U-86-14, Rev. A, dated January 14,1987, as appropriate. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) (1) and 1 CFR Part 51. Copies may be obtained from BHTI, P.O. Box 482, Fort Worth, Texas 76101. Copies may be inspected at the Office of the Regional Counsel, FAA, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas, or at the Office of the Federal Register, 1100 L Street, NW., Room 8401, Washington, D.C. This amendment, 39-5643 becomes effective on August 7, 1987.
2020-05-11: The FAA is adopting a new airworthiness directive (AD) for Robinson Helicopter Company Model R44 and R44 II helicopters with an agricultural spray system installed by Supplemental Type Certificate (STC) SR00286BO (spray system). This spray system is also known as a Simplex Manufacturing Company (Simplex) Model 244 spray system. This AD was prompted by a report of an in-flight failure of the spray system elbow pump fitting (pump fitting). This AD requires repetitive inspections of the spray system pump fitting, corrective action if necessary, replacement of the spray system pump fitting, and installation of hose supports and a pump outlet cover. The FAA is issuing this AD to address the unsafe condition on these products.
78-23-09: 78-23-09 PIPER: Amendment 39-3342. Applies to Piper Model PA-38-112 Serial Nos. 38-78A0001, 38-78A0004 thru 38-78A0016, 38-78A0018 thru 38-78A0040, 38-78A0042 thru 38-78A0224, 38-78A0226 thru 38-78A0232, 38-78A0234 thru 38-78A0236, 38-78A0238 thru 38-78A0250, 38-78A0252 thru 38-78A0266, 38-78A0268, 38-78A0270 thru 38-78A0273, 38-78A0276, 38-78A0277, 38-78A0279 thru 38-78A0284, 38-78A0286 thru 38-78A0289, 38-78A0291, 38-78A0298, 38-78A0315 thru 38-78A0318, 38-78A0324, 38-78A0326, 38-78A0329 certificated in all categories. To prevent possible separation of the control wheel from the control shaft, accomplish the following: Before further flight, unless already accomplished, inspect and alter or replace the pilot and co-pilot control wheels in accordance with the "Instructions" section of Piper Service Bulletin No. 609 dated June 17, 1978, or equivalent which must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Upon submission of substantiating data 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. The affected airplanes may be flown in accordance with FAR 21.197 to a location where the AD compliance procedures can be accomplished. This amendment is effective November 13, 1978.
81-19-01: 81-19-01 BELL HELICOPTER TEXTRON (BHT): Amendment 39-4207. Applies to Model 212 series helicopters certificated in all categories (Airworthiness Docket No. 81-ASW- 38). To prevent possible failure of main rotor yoke Part Number 204-011-102 (all dash numbers), accomplish the following: a. Unless Bell Helicopter Textron Alert Service Bulletin No. 212-81-23 has been previously complied with, within 10 days after the effective date of this Airworthiness Directive: (1) Create a component history card for yoke Part Number 204-011-102 (all dash numbers). (2) Record the operating time accumulated on the yoke as follows: a. For each flight hour of passenger or internal cargo operation, enter 1 hour on the component history card. b. For each flight hour involving external load operations where more than four lifts per hour occur, including those conducted under Federal Aviation Regulation Parts 133 and 137, enter 5 hours on the component history card.c. If operating time for the yoke is unknown, enter 2,400 hours on the component history card. (3) Yokes with more than 3,300 hours time on the compliance date of this AD must be retired prior to obtaining an additional 300 hours time. (4) Yokes with less than 3,300 hours time on the compliance date of this AD must be retired on or before attaining 3,600 recorded hours. b. The 3,600-hour life and the above method of recording flight hours on the yoke component history card shall continue in effect on all Part Number 204-011-102 yokes. c. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. d. In accordance with FAR 21.197 flight is permitted to a base where the requirements of this AD may be accomplished. This amendment becomes effective September 30, 1981.
64-16-03: 64-16-03 FAIRCHILD: Amdt. 771 Part 507 Federal Register July 23, 1964. Applies to Model F-27 Series Aircraft. Compliance required within 300 hours' time in service after the effective date of this AD, unless already accomplished. Rebalance the rudder in accordance with the procedures specified in Section 2, "Accomplishment Instructions", of Fairchild Service Bulletin 27-38, or an equivalent approved by the Engineering and Manufacturing Branch, FAA Eastern Region. (Fairchild Service Bulletin 27-38 dated May 4, 1964, covers this same subject.) This directive effective July 23, 1964.