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85-14-03: 85-14-03 BRITISH AEROSPACE: Amendment 39-5092. Applies to Model BAC 1-11 series 400 airplanes certificated in any category. Compliance is required as indicated. To prevent asymmetrical deployment of ground spoilers (lift dumpers) accomplish the following, unless previously accomplished within the last 1000 landings or one year, whichever occurred earlier: A. Within the next 100 landings or 30 days after the effective date of this AD, whichever occurs first, and thereafter at intervals not to exceed 5,000 landings from the last inspection, inspect the ground spoiler mechanical locks for misalignment, and adjust if necessary, in accordance with the accomplishment instructions of British Aerospace BAC 1-11 Alert Service Bulletin 27-A-PM5890, dated December 21, 1983. From the results of the inspection above: 1. If two or more mechanical locks out of the four per ground spoiler are found unserviceable, perform an operational check of the ground spoilers prior to further flight and thereafter at intervals not to exceed 600 landings or 150 days, whichever occurs earlier, until defective components are replaced in accordance with the accomplishment instructions of the service bulletin. 2. If one mechanical lock out of the four per ground spoiler is found unserviceable, perform an operational check of the ground spoilers prior to further flight and thereafter at intervals not to exceed 2,500 landings in accordance with the accomplishment instructions of the service bulletin until defective components are replaced. 3. If the mechanical lock system fails the operational check conducted in accordance with paragraphs A.1. or A.2., above, the locks must be repaired or the ground spoilers rendered inoperative in accordance with the accomplishment instructions of the service bulletin prior to further flight. 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 amendment becomes effective August 15, 1985.
2020-02-23: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, A350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. This AD requires repetitive inspections of the installation of the pull cables on the emergency float kits. This AD was prompted by the results of an accident investigation and subsequent reports of difficulty pulling the emergency float kit float activation handle installed on the pilot cyclic. The FAA is issuing this AD to address the unsafe condition on these products.
86-08-01: 86-08-01 SHORT BROTHERS, LTD.: Amendment 39-5286. Applies to Model SD3-30 and SD3-60 series airplanes; serial numbers SH3002 through SH3099, SH3102, and SH3105 (SD3-30 airplanes); SH3601 through SH3661 and SH3663 through SH3665 (SD3-60 airplanes); certificated in any category. Compliance is required as indicated below, unless previously accomplished: 1. Within seven days after the effective date of this AD, inspect the collector tank housing in accordance with Short Brothers Service Bulletin SD330-28-29, dated August 1985 (for SD3-30 series airplanes), and SD360-28-12, Revision 1, dated August 1985 (for SD3-60 series airplanes). If leaks are found, prior to further flight, replace the shrouds and seals in accordance with the applicable service bulletin instructions. If no leaks are found, repeat the inspection at intervals not to exceed 120 hours time in service. 2. Replacement of the existing shrouds and seals in accordance with the applicable service bulletin, referredto in paragraph 1. of this AD, constitutes terminating action for the requirement for the repetitive inspections set forth in paragraph 1., above. 3. 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, Northwest Mountain Region. 4. 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Short Brothers, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East MarginalWay South, Seattle, Washington. This amendment becomes effective April 28, 1986.
77-01-06: 77-01-06 PIPER: Amendment 39-2806. Applies to Models PA-31 and PA-31-325, Serial Nos. 31-7612060 through 31-7612080, 31-7612082 through 31-7612089, 31-7612091, 31- 7612096 and 31-7612099; Model PA-31-350, Serial Nos. 31-7652105 through 31-7652115, 31- 7652117, 31-7652118, 31-7652120 through 31-7652146, 31-7652148 through 31-7652162, 31- 7652164, 31-7652165 and 31-7652168 and above model aircraft which have had a replacement horizontal stabilizer installed in the field subsequent to April 1976, certificated in all categories. To prevent possible hazards in flight associated with missing horizontal stabilizer skin- stiffener rivet attachments, accomplish the following within the next fifty hours in service from the effective date of this AD unless previously accomplished: (a) Inspect and, if required, repair the horizontal stabilizer skin-stiffener rivet attachment in accordance with the "Instructions" section of Piper Service Bulletin No. 521 or equivalent procedures approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective January 19, 1977.
81-20-02: 81-20-02 VARGA AIRCRAFT CORPORATION (MORRISEY): Amendment 39- 4341. Applies to Model 2150A, certified in any category. COMPLIANCE: Required as indicated, unless already accomplished. To prevent engine fuel starvation due to obstruction of the fuel vent system, prior to further flight, accomplish the following: a. Inspect vent tube assemblies, P/N 26016-42 and -66, for free airflow between all branches of the vent tubes. b. Replace obstructed vent tube assemblies with a serviceable part of the same part number prior to return to service. c. Special flight permits may be issued in accordance with FAR 21.197 to operate aircraft to a base for the accomplishment of inspections required by this AD. d. Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Western Aircraft Certification Field Office, Northwest Mountain Region, Federal Aviation Administration, 15000 Aviation Boulevard, Hawthorne, California 90261; telephone (213) 536-6352. Varga Service Bulletin SB-13, entitled Fuel Vent Drain Inspection, refers to the subject matter of this AD. This amendment becomes effective March 15, 1982, to all persons except those to whom it was made immediately effective by priority mail as Emergency AD 81-20-02, dated September 28, 1981.
2020-02-18: The FAA is adopting a new airworthiness directive (AD) for all Gulfstream Aerospace Corporation (Gulfstream) Models GVI, GVII-G500, and GVII-G600 airplanes. This AD requires revising the airplane flight manual (AFM) by attaching an airplane flight manual supplement (AFMS), which contains new or revised operating limitations, abnormal procedures, and emergency procedures. This AD was prompted by reports of continued flight after a flight control surface shutdown. If flight is continued after a flight control surface shutdown, the airplane is left without protection against flight control surface hard-over and force fight events on the remaining, operable flight control surfaces. The FAA is issuing this AD to address the unsafe condition on these products.
77-01-03: 77-01-03 PIPER AIRCRAFT CORPORATION: Amendment 39-2801. Applies to Model PA-28-151 airplanes, serial numbers 28-7415001 through 28-7715278 and 28-7715289 certificated in all categories. \n\n\tCompliance required within the next 10 hours' time in service after the effective date of this AD, unless already accomplished. \n\n\tTo detect and correct those carburetor air filter boxes that do not contain a drain hole, accomplish the following: \n\n\t(a)\tOpen the top right side engine cowl door to gain access to the carburetor air filter box, Piper Part Number 35462-00, at the right hand bottom section of the engine compartment. \n\n\t(b)\tCheck visually and by feel to determine whether the carburetor air filter box contains a drain hole in the lower rear corner of the outside half of the carburetor air filter box. (See figure) This check may be performed by the pilot. \n\n\n\nAD 77-01-03 \n\n\t(c)\tIf the box contains a drain hole, accomplish (f). \n\n\t(d)\tIf the box does not contain a drain hole, accomplish (e) and (f). \n\n\t(e)\tModify the carburetor air filter box as follows: \n\n\t\t(1)\tRemove and disassemble the carburetor air filter box. \n\n\t\t(2)\tDrill a .19 inch diameter hole in the lower rear corner of the outside half of the carburetor air filter box. (See figure) \n\n\t\t(3)\tReassemble and reinstall the carburetor air filter box. \n\n\t(f)\tClose the engine cowl and return the airplane to service. \n\n\tPiper Service Bulletin 536 also pertains to this subject. \n\n\tThis amendment becomes effective January 14, 1977.
76-06-09: 76-06-09 PIPER: Amendment 39-2559 as amended by amendment 39-3325. Applies to Piper Model PA-31P airplanes. Compliance required as indicated unless already accomplished. To preclude failure of the engine exhaust system installed on Model PA-31P airplanes, accomplish the following: (a) On airplanes serial numbers 31P-1 through 31P-7730003 within 50 hours after the effective date of this amendment, and every 50 hours thereafter, visually inspect turbocharger exhaust V-band couplings, vibration isolators and support brackets (if installed) for cracks, looseness, and distortion. Any part found cracked or distorted shall be replaced prior to further flight. (b) On airplane serial numbers 31P-1 through 31P-7630001 and on 31P-7630003 within 50 hours time in service after the effective date of this AD perform exhaust pipe slip joint modification in accordance with Lycoming Service Bulletin 393A or an equivalent approved alteration. (c) On airplanes serial numbers31P-1 through 31P-7630009 within 50 hours time in service after the effective date of this AD install bracket and clamp assembly, Piper Kit No. 760 974, in accordance with Piper Service Bulletin 462A or an equivalent approved alteration. (d) On airplanes serial numbers 31P-1 through 31P-7730003 the repetitive inspections of paragraph (a) shall be accomplished until the replacement one-piece turbine tailpipe clamp coupling P/N 556053 is installed in accordance with the "Instructions" sheet in Piper Service Bulletin No. 534 and vibration isolators installed in accordance with Piper Service Bulletin No. 492. NOTE: When replacing the turbine tailpipe clamp coupling, preload the tailpipe against the turbine flange as specified in Piper Service Bulletin Nos. 534 and 462A. (e) Aircraft may be flown to a base where the maintenance required by this airworthiness directive is to be performed per FAR's 21.197 and 21.199. (f) The Chief, Engineering and Manufacturing Branch, FAA Eastern Region may adjust the inspection interval specified in this airworthiness directive upon request of an owner or operator submitted with substantiating data through an FAA maintenance inspector. All equivalent alterations or parts must be approved by the said Branch Chief. (Piper Service Bulletin No. 430 also pertains to this subject.) Amendment 39-2559 was effective March 31, 1976. This amendment 39-3325 is effective October 31, 1978.
91-14-22: 91-14-22 TEXTRON LYCOMING: Amendment 39-6916. Docket No. 89-ANE-10. Applicability: Textron Lycoming (formerly Avco Lycoming) direct drive piston aircraft engines (except: O-320-H, O-360-E, LO-360-E, TO-360-E, LTO-360-E and TIO-541 series engines). Compliance: Required at each engine overhaul, after a propeller strike, sudden stoppage, or whenever gear train repair is required. A propeller strike for the purpose of this AD, is defined as a sudden engine stoppage, or loss of a propeller blade or tip. NOTE: Avco Lycoming Service Letter No. L163B dated December 23, 1977, "Recommendations Regarding Accidental Engine Stoppage, Loss of Propeller Blade or Tip," contains additional information on the subject. To prevent loosening or failure of the crankshaft gear retaining bolt, which may cause sudden engine failure, accomplish the following: (a) Inspect the crankshaft counterbored recess, the alignment dowel, the retaining bolt and lock plate, the bolt hole threads, and the crankshaft gear for wear, galling, corrosion, and fretting in accordance with Sections 1 through 7, including all tables and figures in Textron Lycoming Service Bulletin (SB) No. 475, Revision A, dated July 16, 1990. (b) Prior to further flight, repair, rework, or replace damaged or worn parts as identified in paragraph (a) of this AD. (1) Repair and rework crankshaft pilot diameter in accordance with Textron Lycoming SB 475, Revision A, dated July 16, 1990, and replace dowel pin with appropriate size dowel as shown in Table 1 of the service bulletin. (2) Insure that the tapped threads in the gear retaining bolt hole of the crankshaft are clean and undamaged. If threads are damaged, replace crankshaft with a serviceable unit, or have threads repaired by an FAA approved facility specifically approved to do that repair. (3) Inspect the counterbored gear mounting face of the crankshaft to ensure there is no damage due to fretting or galling, as damageof this nature is unrepairable. (4) Repair crankshaft counterbore pilot diameter, if necessary, in accordance with Section 3 of Textron Lycoming SB No. 475, Revision A, dated July 16, 1990. (5) Verify that the crankshaft gear incorporates three .75 inch radius scallops on the flange as shown in Figure 5 of Textron Lycoming SB No. 475, Revision A, dated July 16, 1990. Assemble gear onto crankshaft using a new retaining bolt and lockplate and insure fit of mating parts as described in Section 6 and Figure 6 of the Textron Lycoming Service Bulletin No. 475, Revision A, dated July 16, 1990. (c) Aircraft maybe ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (d) Upon submission of substantiating data by an owner or operator through an FAA Inspector (maintenance, avionics, or operations, as appropriate), an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedule specified in this AD may be approved by the Manager, New York Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, FAA, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. The inspection procedures shall be done in accordance with the following Textron Lycoming document: DOCUMENT NO. PAGE NO. ISSUE/REV. DATE SB 475 1-4 A 07/16/90 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 Textron Lycoming, Oliver Street, Williamsport, Pennsylvania 17701. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, Massachusetts 01803, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC. This amendment (39-6916, AD 91-14-22) becomes effective on August 19, 1991.
98-12-34: This amendment adopts a new airworthiness directive (AD), applicable to certain CASA Model CN-235 series airplanes, that requires modification of the forward beam of the vertical stabilizer by the installation of a structural reinforcement plate. 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 in-flight structural deformation or failure of the vertical stabilizer, resulting in reduced controllability of the airplane.