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80-25-06 R1: 80-25-06 R1 TELEDYNE CONTINENTAL MOTORS: Amendment 39-3984 as amended by Amendment 39-4061. Applies to Models GTSIO-520-L, serial numbers 608324 through 608627; GTSIO-520-M, serial numbers 606619 through 606890; and GTSIO-520-N, serial numbers 610001 through 610107, engines with 100 hours or less total time in service on the effective date of this AD, installed on but not limited to certain Cessna Models 404 and 421C airplanes certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent engine failure due to loss of engine oil pressure, damage due to contaminated oil, and propeller shaft damage resulting from a malfunctioning thrust washer accomplish the following: (a) Before each flight and immediately after each flight until the accumulation of 100 hours total time in service, perform a special oil pressure check to determine the oil pressure with engine power at the same level as the magneto check. If oil pressure fluctuatesor is less than 30 psi, accomplish paragraphs (b)(1) and (b)(2) before further flight. This oil pressure check may be accomplished by the pilot as provided in FAR 43.3(h). (b) Prior to the next flight and at each oil change until the accumulation of 100 hours total time in service: (1) Remove the oil filter, disassemble the canister, and inspect the paper element between the pleats to determine the quantity of metallic material visually and by using a clean magnet. If total metallic contaminants are in excess of the quantity necessary to cover a 1/4 inch diameter surface, before further flight take the necessary maintenance action to replace those parts that are malfunctioning. NOTE: Exercise caution to prevent contamination of the filter element during disassembly. (2) Inspect to determine the end clearance (shaft end play) of the propeller drive shaft with engine at ambient temperature. If axial movement is in excess of .020 inch, before further flight take necessarymaintenance action to replace those parts that are malfunctioning. (c) Prior to the next flight, inspect the engine and airplane records and change oil if necessary to ensure that SAE No. 50 oil is installed for ambient temperatures above 40 degrees F or SAE No. 30 oil is installed for ambient temperatures below 40 degrees F. (d) Upon or before the accumulation of 25 hours, 50 hours and 100 hours total time in service, change oil and oil filter. Do not use multiviscosity oils within the first 100 hours time in service. (e) Make appropriate maintenance record entry when accomplishing each requirement of this AD. The airplanes equipped with affected engines may be flown in accordance with FAR 21.197 to a location where the AD compliance procedures can be accomplished. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. NOTE: Continental Motors Service Bulletin NO. M80-30, dated December 10, 1980, pertains to this subject. Amendment 39-3984 became effective December 5, 1980. This amendment 39-4061 becomes effective March 23, 1981.
2013-25-09: We are adopting a new airworthiness directive (AD) for certain AgustaWestland S.p.A. (Agusta) Model AB139 and AW139 helicopters. This AD requires inspecting the nose landing gear (NLG) pin installations for incorrect assembly. This AD is prompted by reports of incorrectly installed pins discovered on in-service aircraft. These actions are intended to detect incorrectly installed pins, which could result in collapse of the NLG during taxi or landing.
2010-15-10: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. (Piper) PA-28, PA-32, PA-34, and PA-44 series airplanes. This AD requires you to inspect the control wheel shaft on both the pilot and copilot sides and, if necessary, replace the control wheel shaft. This AD results from two field reports of incorrectly assembled control wheel shafts. We are issuing this AD to detect and correct any incorrectly assembled control wheel shafts. This condition, if left uncorrected, could lead to separation of the control wheel shaft, resulting in loss of pitch and roll control.
99-17-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires repetitive inspections to detect wear of the inboard flap trunnions, and to detect wear or debonding of the protective half-shells; and corrective actions, if necessary. 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 chafing and resultant wear damage on the inboard flap drive trunnions or on the protective half-shells, which could result in failure of the trunnion primary load path; this would adversely affect the fatigue life of the secondary load path and could lead to loss of the flap.
2022-15-05: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, - 113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, - 131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by a report that cracks were found on the web horizontal flange and inner cap on a certain frame (FR), left-hand (LH) and right-hand (RH) sides, at a certain stringer (STGR). This AD requires repetitive high frequency eddy current (HFEC) inspections for cracks on the web horizontal flange and inner cap, and applicable corrective actions, 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.
53-09-04: 53-09-04 CONTINENTAL: Applies to All Aircraft Equipped With Continental W-670-9A (Ordnance-Tank) Engines and Ground Adjustable Propellers Having Blades 11C1 (Hamilton Standard Model Designation) or 4350, 4350F, or 4350F1 (Navy Model Designation.) Compliance required not later than May 15, 1953. In the absence of suitable propeller vibration stress data, the following precautionary measures should be taken to minimize the possibility of propeller blade fatigue failures: (1) Disassemble propeller and inspect for cracks by etching the shank areas of the blades under the hub clamp rings. (2) Cut propellers to between 102 inches maximum and 100 inches minimum diameter. (3) Set blade angle so that static r.p.m. is between 1,500 and 1,975. (4) Install propeller on engine in the zero degree position (blades in line with crankthrow). (5) Placard airplane, "Do not exceed 1,900 r.p.m. for all operations except takeoff." (6) Remove all nicks and gouges from tip region andmaintain propeller blades as outlined in Civil Aeronautics Manual 18.
99-17-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200 and -300 series airplanes, that requires modification of the off-wing emergency evacuation slide system. This amendment is prompted by reports that a certain type of off-wing escape slide aboard several airplanes separated from the airplane during flight. The actions specified by this AD are intended to prevent separation of the emergency evacuation slide from the airplane, which could result in damage to the fuselage and unavailability of an escape slide during an emergency evacuation.
92-27-08: 92-27-08 CESSNA: Amendment 39-8442. Docket No. 92-NM-228-AD. Applicability: Citation Model 650 series airplanes, having serial numbers -0001 thru -0219, inclusive, and -7001 thru -7013, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the potential loss of elevator control, accomplish the following: (a) Within 25 hours time-in-service after the effective date of this AD: Perform an inspection of the inboard attach fittings of the left-hand and right-hand elevator torque tubes to determine minimum material wall thickness in accordance with Cessna Citation Alert Service Letter A650-27-30, dated November 12, 1992; and perform a visual inspection of the fittings to detect cracking. (1) If the material thickness of the inboard attach fitting, at all locations, is 0.045 inch or thicker, and if no cracked fitting is found, no further action is required by this AD. (2) If the materialthickness of the inboard attach fitting, at any location, is equal to or greater than 0.040 inch but less than 0.045 inch, and if no cracked fitting is found, within 150 flight hours, replace the inboard attach fitting in accordance with the service letter. (3) If the material thickness of the inboard attach fitting, at any location, is thinner than 0.040 inch, or if a cracked fitting is found, prior to further flight, replace the fitting with a fitting having part number 6234132-8, in accordance with the service letter. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Wichita Aircraft Certification Office (ACO), FAA, Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The inspection and replacement shall be done in accordance with Cessna Citation Alert Service Letter A650-27-30, dated November 12, 1992. 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 Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, Kansas 67277. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on January 4, 1993.
86-21-09: 86-21-09 BRITISH AEROSPACE (BAe): Amendment 39-5447. Applies to BAe Jetstream Model 3101 (all serial numbers) airplanes certificated in any category which have incorporated Arkansas Modification Center (AMC) Supplemental Type Certificate (STC) No. SA5900SW baggage pod serial numbers 002 through 044 inclusive. Compliance: Required within the next fifty (50) landings after the effective date of this AD, unless already accomplished. NOTE: If landings are not recorded, one hour time-in-service (TIS) equals two landings. To prevent possible chafing of the flap jack lock valve pressure pipe and loss of hydraulic fluid, accomplish the following: (a) Visually inspect flap jack lock valve hydraulic pressure pipe BAe Part Number (P/N) 616302 for evidence of chafing in accordance with Section 2. "ACCOMPLISHMENT INSTRUCTIONS," Paragraph B "ACCOMPLISHMENTS," of BAe Alert Service Bulletin (ASB) No. 27-A-JA860226, dated August 11, 1986. (1) If chafing has occurred, before further flight, (i) Replace hydraulic pressure pipe P/N 616302 with a serviceable airworthy part, in accordance with BAe S/B No. 27-A-JA860226, and (ii) Modify pod by incorporating an aperture in accordance with Section 2., "ACCOMPLISHMENT INSTRUCTIONS," paragraphs 1 through 8 of revised AMC Service Bulletin (S/B) No. 25-0002(-2), dated September 11, 1986. (iii) Accomplish paragraph (b) of this AD. (2) If no chafing has occurred, before further flight, (i) modify pod by incorporating an aperture in accordance with Section 2., "ACCOMPLISHMENT INSTRUCTIONS," paragraphs 1 through 8 of AMC S/B No. 25-0002(-2), and (ii) accomplish paragraph (b) of this AD. (b) Measure the clearance distance between the flap jack lock valve hydraulic pressure pipe, P/N 616302 and the pod membrane smoke detector mounting screws, over the whole flap position operating range, in accordance with Section 2., "ACCOMPLISHMENT INSTRUCTIONS". If the clearance at all flap positions is: (1) 0.50 inches or more, install the aperture cover plate provided in AMC Kit P/N 31-5179-37 and accomplish paragraphs 14 through 17 of Section 2., "ACCOMPLISHMENT INSTRUCTIONS," of AMC S/B No. 25-0002(-2), and return the airplane to service. (2) Less than 0.50 inches, (i) Modify the pod in accordance with paragraphs 18 through 29 of Section 2., "ACCOMPLISHMENT INSTRUCTIONS," of AMC S/B No. 25-0002(-2), and (ii) Install baggage pod and repeat the actions specified in paragraph (b) of this AD. (c) Aircraft may be flown in accordance with FAR 21.197 to a location where this Airworthiness Directive (AD) can be accomplished. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, FAA, Southwest Region, Special Programs Branch, ASW-190, 4400 Blue Mound Road, Post Office Box 1689, Fort Worth, Texas 76101. All persons affected by this AD may obtain copies of Arkansas Modification Center, Inc., (AMC) Service Bulletin (S/B) No. 25-0002(-2) dated July 22, 1986, Revised September 11, 1986, referred to herein upon request to the Arkansas Modification Center, Inc., Post Office Box 3356, Adams Field, Little Rock, Arkansas 72203, and Alert Service Bulletin No. 27-A- JA860226, dated August 11, 1986, referred to herein upon request to the British Aerospace, Engineering Department, Post Office Box 17414, Dulles International Airport, Washington, D.C. 20041; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective October 29, 1986.
2022-15-02: The FAA is adopting a new airworthiness directive (AD) for certain Cameron Balloons Ltd. (Cameron) Stratus double burner assemblies installed on hot air balloons. This AD was prompted by reports 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 identifies the unsafe condition as fatigue cracking of the weld on Stratus double burner hangers. This AD requires repetitively inspecting certain Stratus double burner hangers and replacing certain Stratus double burners, and prohibits installing certain parts. The FAA is issuing this AD to address the unsafe condition on these products.