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2015-13-03: We are adopting a new airworthiness directive (AD) for all Przedsiebiorstwo Doswiadczalno-Produkcyjne Szybownictwa ``PZL-Bielsko'' Model SZD-50-3 ``Puchacz'' sailplanes. 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 detachment of the rudder cable fitting block from the fuselage. We are issuing this AD to require actions to address the unsafe condition on these products.
2015-13-02: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by reports of corrosion in the low-rate discharge tubes of the fire protection system leading to the forward baggage compartment, and perforation of one or more tubes. This AD requires repetitive checks for leakage of the discharge tubes of the fire protection system. This AD also mandates eventual replacement of all existing aluminum tube assemblies with new, improved corrosion-resistant stainless steel tube assemblies. We are issuing this AD to prevent perforation of the low- rate discharge tubes, which could result in insufficient fire extinguishing agent reaching the forward baggage compartment in the event of a fire, which could result in damage to the airplane and injury to the occupants.
2000-11-14: This document adopts a new airworthiness directive (AD) that applies to all Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes that are equipped with pneumatic deicing boots. This AD requires you to revise the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident (on airplanes other than the affected Pilatus airplanes) that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The Pilatus Models PC-12 and PC-12/45 airplanes have a similar type design (as it relates to airframe pneumatic ice boots) to the incident and accident airplanes. The actions specified by this AD are intended to assure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle
92-04-02: 92-04-02 DASSAULT AVIATION (FORMERLY AVIONS MARCEL DASSAULT- BREGUET AVIATION): Amendment 39-8171. Docket 91-NM-31-AD. Applicability: Model Mystere Falcon 900 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent stiffness of the center engine power control and/or flight controls (elevator and rudder), and reduced controllability of the airplane, accomplish the following: (a) Within 30 days after the effective date of this AD, and thereafter at intervals not to exceed 7 days, accomplish paragraphs (a)(1) and (a)(2) of this AD: (1) Verify proper operation of the drain stub heating, in accordance with the manufacturer's Maintenance Manual (reference Procedure 30-700). (2) Verify freedom from clogging of the system by pressurizing the fuselage on the ground to a cabin pressure altitude of Z = -1,500 feet using the engines or APU, and by checking with the hand that air flows out of the drain stub, in accordance with the manufacturer's Maintenance Manual (reference Procedure 21-311). (b) Within 90 days after the effective date of this AD, perform the modifications and inspections specified by paragraphs (b)(1), (b)(2), and (b)(3) of this AD, which constitute terminating action for the requirements of paragraph (a) of this AD. (1) On drain stub Part Number C49RD0033, eliminate the 3 mm. diameter restrictor and enlarge the outlet cross-section, in accordance with Dassault Aviation Service Bulletin F900-38-1 (F900-82), dated October 4, 1990. (2) On the drainage system, add protective screens to the drainage holes of the water collector under the washbasin, in accordance with Dassault Aviation Service Bulletin F900-38-1 (F900- 82), dated October 4, 1990; and install a protective screen to the drainage holes on each side of the center beam, in accordance with Dassault Aviation Service Bulletin F900-53-5 (F900-57), dated October 4, 1990. (3) Following the installation of the modifications required by paragraphs (b)(1) and (b)(2) of this AD, prior to further flight, check the stub heating for proper operations, in accordance with Procedure 30-701 in the manufacturer's Maintenance Manual, and inspect and clean the modified drain holes. (c) Within 300 hours time-in-service after the effective date of this AD, or within 6 months after accomplishing the modifications required by paragraph (b) of this AD, whichever occurs first; and thereafter at intervals not to exceed 300 hours time-in-service or 6 months, whichever occurs first; accomplish paragraphs (c)(1), (c)(2), and (c)(3) of this AD, in accordance with Dassault Aviation Service Bulletins F900-38-1 (F900-82) or F900-53-5 (F900-57), both dated October 4, 1990, as applicable: (1) Check the stub heating for proper operation. (2) Inspect and clean the drain hole protective screens. (3) Verify correct water drainage via the frame 25 and washbasin collector drains. (d) Within 12 months after the effective date of this AD, modify the collector drains, in accordance with Dassault Aviation Falcon 900 Service Bulletin F900-38-2 (F900-83), dated April 25, 1991. Installation of this modification constitutes terminating action for the repetitive inspections required by paragraph (c) of this AD. (e) An alternative method 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. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. (f) 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. (g) The modifications and inspections shall be done in accordance with the Dassault Aviation Service Bulletin F900-38-1 (F900-82), dated October 4, 1990; Dassault Aviation Falcon 900 Service Bulletin F900-38-2 (F900-83), dated April 25, 1991; and Dassault Aviation Service Bulletin F900-53-5 (F900-57), dated October 4, 1990. 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 Falcon Jet Corporation, Customer Support Department, Teterboro Airport, Teterboro, New Jersey 07608. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (h) This amendment (39-8171, AD 92-04-02) becomes effective on March 16, 1992.
2000-11-06: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 767 series airplanes. This AD requires repetitive inspections to detect discrepancies of the wiring and surrounding Teflon sleeves of the fuel tank boost pumps and override/jettison pumps; replacement of the sleeves with new sleeves, for certain airplanes; and repair or replacement of the wiring and sleeves with new parts, as necessary. This amendment is prompted by reports of chafing of Teflon sleeves that surround and protect electrical wires inside conduits installed in the fuel tanks. The actions specified by this AD are intended to ensure adequate protection to the fuel pump wire insulation. Such chafing of the wire insulation could eventually result in exposure of electrical conductor, permit arcing from the wire to the conduit, and create a potential for a fuel tank fire or explosion.
96-24-02: 96-24-02 DORNIER: Amendment 39-9828. Docket 95-NM-230-AD. Applicability: Model 328-100 series airplanes, serial numbers 3005 through 3024 inclusive; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent debonding of the edges of the acoustic damping foils, which could result in short circuiting of parts of the overhead switch panel due to contact with loose edges of the foils, and consequent smoke and/or fire in the cockpit; accomplish the following: (a) Within 90 days after the effective date of this AD, remove the acoustic damping foils having part number 001A258A1101204 at the skin behind the overhead switch panel in accordance with Dornier Service Bulletin SB-328-25-072, dated December 16, 1994. (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, Standardization Branch, ANM-113, FAA, Transport 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, Standardization Branch, ANM-113. NOTE 2: Information concerning theexistence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The removal shall be done in accordance with Dornier Service Bulletin SB-328-25-072, dated December 16, 1994. 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 Dornier Luftfahrt GmbH, P.O. Box 1103, D-82230 Wessling, Germany. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on December 27, 1996.
69-09-03 R3: 69-09-03 R3 SENSENICH PROPELLER MANUFACTURING COMPANY INC.: Amendment 39-9583. Docket 95-ANE-03. Revises AD 69-09-03 R2, Amendment 39-1102. Applicability: Sensenich Propeller Manufacturing Company Inc. Models M76EMM, M76EMMS, 76EM8, and 76EM8S( ) metal propellers. Paragraphs (a) and (b) of this airworthiness directive (AD) do not apply to those propellers installed on the following solid crankshaft Textron Lycoming O-360 series reciprocating engines: O-360-A4A, -A4D, -A4G, -A4J, -A4K, -A4M, -A4N, -A4P, and -A5AD, or additional engines identified by suffixes having a digit "4" or higher in the second position. These propellers are installed on but not limited to the following aircraft: Piper PA-28-180, PA-28-181, American General Aircraft Holding Co. Inc. (formerly Gulfstream American) AA-5 series, Beech B23 and C23, Cessna 172Q, Avions Pierre Robin R-3000/160, and aircraft modified under various Supplemental Type Certificates (STC's). NOTE: This AD applies to each propeller identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For propellers that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (f) to request approval from the Federal Aviation Administration (FAA). This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any propeller from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent propeller blade tip fatigue failure, which can result in loss of control of the aircraft, accomplish the following: (a) Commencing with the next flight after the effective date of this AD, do not operate the engine in continuous operation between 2,150 and 2,350 RPM. (b) Within the next 25 hours time in service (TIS) after the effective date of this AD, mark engine tachometer with a red arc from 2150 RPM to 2350 RPM. (c) For propellers with 500 or more total hours TIS, or unknown TIS on the effective date of this AD, inspect and rework, within the next 50 hours TIS after the effective date of this AD, in accordance with Sensenich Propeller SB No. R-14A, dated July 28, 1995. Remove from service those propellers that do not meet the inspection and rework requirements of Sensenich Propeller SB No. R-14A, dated July 28, 1995. (d) For propellers with less than 500 total hours TIS on the effective date of this AD, inspect, and rework or replace, as necessary, prior to accumulating 550 total hours TIS, in accordance with Sensenich Propeller SB No. R-14A, dated July 28, 1995. Remove from service those propellers that do not meet the inspection and rework requirements of Sensenich Propeller SB No. R-14A, dated July 28, 1995. (e) Mark with a suffix letter "K" propellers that have been inspected and, reworked in accordance with Sensenich Propeller SB No. R-14A, dated July 28, 1995, and found satisfactory. (f) An alternative method of compliance or adjustment of the initial compliance time that provides an acceptable level of safety may be used if approved by the Manager, New York Aircraft Certification Office. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, New York Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York Aircraft Certification Office.(g) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished. (h) The actions required by this AD shall be done in accordance with the following Sensenich Propeller SB's: Document No. Pages Revision Date No. R-13 A7 Original April 11, 1969. Total pages: 1. No. R-14A 1 Original July 28, 1995. Total pages: 1. 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 Sensenich Propeller Manufacturing Company Inc., 519 Airport Road, Lititz, PA 17543; telephone (717) 569-0435, fax (717) 560-3725. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (i) This amendment becomes effective on June 13, 1996.
81-13-07: 81-13-07 GATES LEARJET: Amendment 39-4139. Applies to Models 23 (Serial Numbers 003 through 099), Model 24 Series (Serial Numbers 003 through 357), Model 25 Series (Serial Numbers 003 through 341 except 337), Model 28 (Serial Numbers 001 through 005), Model 29 (Serial Numbers 001 through 003), Model 35 Series (Serial Numbers 001 through 415) and Model 36 Series (Serial Numbers 001 through 047) airplanes. COMPLIANCE: Required as indicated unless already accomplished. To ensure operation without fuel starvation, within the next 50 hours time-in-service after the effective date of this AD, accomplish the following: A) Insert in the Airplane Flight Manual the FAA Approved temporary changes shown hereinafter as Figures I, II, and III or the FAA Approved Flight Manual changes (temporary or permanent) supplied by the manufacturer and containing the same information as the above figures. B) Operate the airplane in accordance with instructions in the Airplane Flight Manual changes specified in Paragraph A of this AD. C) Any equivalent method of compliance with this AD must be approved by the Chief, Aircraft Certification Program Office, Room 238, Terminal Building 2299, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 942-4285. This Amendment becomes effective on June 25, 1981. FIGURE I TEMPORARY FLIGHT MANUAL CHANGE Description of Change: Add Limitation to Section I of the Airplane Flight Manual. Filing Instructions: Insert this page adjacent to the "Takeoff and Landing operational Limits" in section 1 -Limitations in your Airplane Flight Manual: Amend Section I - TAKEOFF AND LANDING OPERATIONAL LIMITS by adding the following Limitation: FUEL LOAD - MINIMUM 600 POUNDS IN EACH WING REQUIRED FOR TAKEOFF AND INTENTIONAL GO-AROUND. FIGURE II TEMPORARY FLIGHT MANUAL CHANGE Description of Change: ADD Minimum Fuel Quantity Warning to Section II of the Airplane Flight Manual Filing Instructions: Insert this page adjacent to the "After Takeoff checklist of Section II - NORMAL PROCEDURES in your Airplane light Manual. Add the following warning: AFTER TAKEOFF: WARNING: When the fuel quantity gage indicates 600 pounds of less remaining in either wing tank, prolonged nose up attitude of 10 degrees or more may cause fuel to be trapped in the aft area of the wing tank outboard of the wheel well. Fuel starvation and engine flameout may occur. Reducing pitch attitude and thrust to minimum required will prevent this situation. FIGURE III TEMPORARY FLIGHT MANUAL CHANGE Description of Change: ADD Minimum Fuel Quantity Warning to Section II of the Airplane Flight Manual Filing Instructions: Insert this page adjacent to the "Go-Around/Balked Landing" checklist of Section II-NORMAL PROCEDURES in your Airplane Flight Manual. ADD the following warning: GO-AROUND/BALKED LANDING (ONE OR TWO ENGINE): WARNING: When the fuel quantity gage indicates 600 pounds or less remaining in either wing tank, prolonged nose up attitude of 10 degrees or more may cause fuel to be trapped in the aft area of the wing tank outboard of the wheel well. Fuel starvation and engine flameout may occur. For go-around conditions with low fuel, on first steady indication by the LOW Fuel warning light, reduce climb attitude and thrust to minimum required.
2015-12-10: We are adopting a new airworthiness directive (AD) for all Pratt & Whitney Division (PW) PW6122A and PW6124A turbofan engines. This AD requires initial and repetitive borescope inspections (BSIs) of the high-pressure compressor (HPC) 7th stage integrally bladed (IB) rotor aft integral arm for cracks until replacement of the HPC 7th stage IB rotor using non-silver-plated nuts. This AD was prompted by reports of crack finds in the HPC 7th stage IB rotor. We are issuing this AD to prevent HPC 7th stage IB rotor fractures, which could lead to uncontained engine failure and damage to the airplane.
88-25-07: 88-25-07 FOKKER B.V.: Amendment 39-6084. Applies to Model F-28 Mark 1000, 2000, 3000, and 4000 series airplanes, certificated in any category. Compliance is required within 12 months after the effective date of this AD, unless previously accomplished: To ensure the proper operation of the emergency lighting system when required during an emergency situation, accomplish the following: A. Verify that a three position emergency lighting switch (i.e., OFF, ON, and ARMED) is installed in the cockpit. If such a switch is not installed in the cockpit, install one in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: Operators may wish to refer to Fokker Service Bulletin F28/33-26, dated October 12, 1983, in determining the means to be used to install a three position switch. B. Verify that the emergency lighting system illuminates upon loss of normal electrical power when the three position cockpit mounted switch is placed in the armed position. NOTE: (1) Normal electrical power is considered to be the F-28 AC generator power. (2) For the purpose of this requirement, the emergency lighting system is considered to consist of both the emergency lights and the evacuation lights; however, all affected operators should be aware that for operations under FAR Part 121, an airplane's emergency lighting system also includes the floor emergency escape path lighting. Any modification to the emergency lighting system should ensure the proper operation of the floor emergency escape path lighting. C. Accomplish one of the following: 1. Modify the emergency lighting system, in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region, so that upon loss of normal electrical power, the emergency lighting system is powered by its own dedicated battery packs; or 2. Measure the minimum airplane battery voltage necessary to provide the required emergency lighting illumination levels. Modify the emergency lighting control circuit, in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region, to switch from the airplane batteries to the emergency lighting system battery packs prior to dropping below the above determined minimum airplane battery voltage. D. 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. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. E. 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 modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Fokker Aircraft, USA, Inc., 1199 N. Fairfax Street, Alexandria, Virginia 22314. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment, (39-6084, AD 88-25-07), becomes effective January 9, 1989.
91-02-07: 91-02-07 CESSNA: Amendment 39-6825. Docket No. 90-CE-68-AD. Applicability: Models 411 and 411A airplanes (all serial numbers), certificated in any category. Compliance: Required within the next 30 calendar days after the effective date of this AD, unless already accomplished. To ensure that the correct takeoff performance information is available to the pilot, accomplish the following: (a) Using pen and ink, modify the Airplane Flight Manual and Owner's Manual as follows: NOTE 1: It is recommended that any locally developed pilot's checklists be modified in accordance with the following paragraphs. (1) Change the liftoff (rotation) airspeed to 108 miles per hour indicated airspeed (MPH IAS) for all weights. (2) Change the speed used upon reaching a height of 50 feet above the takeoff surface to 114 MPH IAS for all weights. (3) Increase all listed takeoff distances by 500 feet to account for the higher takeoff airspeeds. (4) If the Owner's Manual contains charts identified as "Normal Takeoff Distances", "Single Engine Takeoff Performance" or "Accelerate Stop Distance", mark each chart with large letters stating "DO NOT USE". NOTE 2: Cessna has published a booklet entitled "Pilot Safety and Warning Supplements", dated October 2, 1985, that provides material related to the subject matter of this AD, specifically the subjects "Single Engine Flight Information" and "Aircraft Loading". (b) FAR 43.3 notwithstanding, the actions required by this AD may be performed by a pilot and must be recorded in accordance with FAR Section 43.9. (c) An alternate method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; Telephone (316) 946-4400. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. This amendment (39-6825, AD 91-02-07) becomes effective on January 22, 1991.
68-07-07: 68-07-07 CESSNA: Amdt. 39-575. Applies to Models 188 and A188 aircraft up to and including Serial Number 188-0317, except Serial Numbers 188-0052, 188-0055, 188-0212, 188- 0215, 188-0217, 188-0219, 188-0220, 188-0225, 188-0246, 188-0263, 188-0279, 188-0287, 188- 0288, 188-0290, 188-0298, 188-0304, 188-0306, 188-0307, 188-0308, 188-0310, 188-0311, 188- 0312, and 188-0314. Compliance: Required as indicated, unless already accomplished. To prevent the separation of the rudder pedal assembly from the pedal shaft at the stub tube weld, accomplish the following: Within the next 25 hours' time in service after the effective date of this airworthiness directive, modify the rudder pedal assembly in accordance with either of the 2 methods contained in Cessna Service Letter 67-47, dated August 22, 1967, or any other method approved as an equivalent by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Central Region. This amendment becomeseffective April 11, 1968.
2015-12-09: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model EC135P1, EC135T1, EC135P2, EC135T2, EC135P2+, EC135T2+, and MBB-BK 117 C-2 helicopters. This AD requires inspecting certain washers for movement and making appropriate repairs if the washers move. This AD was prompted by play found between the Smart Electro Mechanical Actuator (SEMA) and the control rod during installation work on a helicopter. The actions of this AD are intended to prevent loss of concerned control axis and subsequent loss of control of the helicopter.
2000-11-03: This amendment adopts a new airworthiness directive (AD) that is applicable to all Dassault Model Falcon 2000, Mystere-Falcon 900, Falcon 900EX, Fan Jet Falcon, Mystere-Falcon 50, Mystere-Falcon 20, and Mystere-Falcon 200 series airplanes. This action requires revising the Airplane Flight Manual to include speed limitations in the event of failure indications of the pitch feel system. These limitations are intended to mitigate severe pitch oscillations of the airplane.
87-13-02: 87-13-02 PILATUS BRITTEN-NORMAN, Ltd.: Amendment 39-5649. Applies to Models BN-2A Mk III, BN-2A Mk III-1, BN-2A Mk 111-2, and BN-2A Mk 111-3 (all serial numbers) Trislander airplanes certificated in any category. Compliance: Required within 30 days after the effective date of this AD, unless already accomplished, and every 24 calendar months thereafter. To prevent structural failure of the elevator trim tab operating rods, accomplish the following: (a) Remove the two (2) elevator trim tab operating rod assemblies in accordance with the instructions contained in the "INSPECTION" section of Pilatus Britten-Norman, Ltd., Mandatory Service Bulletin (MSB) No. BN-2/SB.179, Issue 1, dated January 30, 1987 (hereinafter referred to as MSB BN-2/SB.179). (1) Disassemble one end of each control rod and visually examine the rod (tube) internally and externally for corrosion, rust, or cracks. (i) If any corrosion, rust, or crack is found, before further flight, replacethe control rod and accomplish paragraphs (a) (1) through (a) (3) of this AD on the replacement unit. (ii) If no defect is found, clean and apply corrosion protection to the rod in accordance with the "RECTIFICATION" instructions of MSB BN-2/SB.179, and (2) Visually inspect each ball end or fork fitting and sleeve (Part Number (P/N) NB-45- 2627), after removing any surface rust, for pitting, discoloration, or cracks. If any evidence of corrosion, pitting, discoloration, or crack is found, before further flight: (i) Replace the defective part with a serviceable unit. (ii) Remove the fitting and sleeve from the other end of the associated control rod and repeat the inspection specified in paragraph (a) (2) of this AD. (3) Reassemble the control rods in accordance with the "RECTIFICATION" instructions of MSB BN-2/SB.179. (4) Reinstall the control rod in accordance with the "RETURNING THE AIRCRAFT TO SERVICE" instructions of MSB BN-2/SB.179. (b)Aircraft may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, B- 10O0 Brussels, Belgium. All persons affected by this directive may obtain copies of the document referred to herein upon request to Pilatus Britten-Norman, Ltd., Bembridge, Isle of Wight, England; or may examine the document referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment, 39-5649, becomes effective on July 27, 1987.
2022-20-10: The FAA is adopting a new airworthiness directive (AD) for all Vulcanair S.p.A. Model P.68, P.68B, P.68C, P.68C-TC, P.68 ''Observer,'' P.68TC ''Observer,'' P.68 ''Observer 2,'' and P.68R airplanes. 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 identifies the unsafe condition as corrosion causing failure of the upper rudder hinge. This AD requires repetitively inspecting the upper and lower rudder hinges for corrosion, cracking, and damage, and depending on the inspection results, taking corrective action. The FAA is issuing this AD to address the unsafe condition on these products.
2015-12-07: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 747-8F and 747-8 series airplanes. This AD was prompted by reports of delamination damage to leading edge (LE) variable camber krueger (VCK) flaps. This AD requires repetitive inspections to detect delamination damage of the lightning strike applique (LSA) on certain LE VCK flaps, and corrective actions if necessary. We are issuing this AD to detect and correct delamination damage to certain LE VCK flaps, which can reduce the lightning strike protection capability on certain LE VCK flaps and result in an uncommanded motion of the trailing edge flap system; such uncommanded flap motion, without shutdown of the trailing edge or leading edge flaps, could cause unexpected changes in lift, potentially resulting in asymmetric lift and loss of control of the airplane.
87-23-06: 87-23-06 GENERAL ELECTRIC: Amendment 39-5746. Applies to General Electric (GE) CF6-50 and -45 series turbofan engines. Compliance is required as indicated, unless already accomplished. To prevent failure of the high pressure turbine (HPT) impeller spacer which may cause an uncontained engine failure, accomplish the following: (a) Eddy current inspect impeller spacers part numbers (P/N's) 9190M82P02, PO3; 9234M25P01 through P04, inclusive; 9348M85P01; 9045M59P07, P08, P10, P12; 9173M55P01, P02, P03; and 9198M92P01 through P10, inclusive, in accordance with GE Service Bulletin (SB) 72-906, dated August 21, 1987, as follows: (1) For HPT impeller spacers with 9,000 cycles since new (CSN) or greater on the effective date of this AD, inspect at the next shop visit or within 300 cycles in service (CIS) from the effective date of this AD, whichever occurs first. (2) For HPT impeller spacers with 8,000 CSN or greater but less than 9,000 CSN on the effective dateof this AD, inspect at the next shop visit or within 600 CIS from the effective date of this AD, or prior to accumulating 9,300 CSN, whichever occurs first. (3) For HPT impeller spacers with 7,000 CSN or greater but less than 8,000 CSN on the effective date of this AD, inspect at the next shop visit or within 900 CIS from the effective date of this AD or prior to accumulating 8,600 CSN, whichever occurs first. (4) For HPT impeller spacers with 6,000 CSN or greater but less than 7,000 CSN on the effective date of this AD, inspect at the next shop visit or within 1,200 CIS from the effective date of this AD or prior to accumulating 7,900 CSN, whichever occurs first. (5) For HPT impeller spacers with 2,500 CSN or greater but less than 6,000 CSN on the effective date of this AD, inspect at the next shop visit or within 2,000 CIS from the effective date of this AD or prior to accumulating 7,200 CSN, whichever occurs first. (6) For HPT impeller spacers with less than2,500 CSN on the effective date of this AD, inspect at the next shop visit or prior to accumulating 4,500 CSN, whichever occurs first. NOTE: Eddy current inspections of HPT impeller spacers completed prior to the effective date of this AD in accordance with GE SB 72-906, dated August 21, 1987, or with GE CF6-50/-45 Engine Shop Manual, Chapter 72-53-06, temporary revision 72-0593 are an alternate means of compliance with paragraph (a). (b) Remove from service, HPT impeller spacers found cracked in accordance with the inspection requirements of paragraph (a) above and replace with a serviceable part. (c) Reinspect impeller spacers, previously inspected in accordance with paragraph (a) above, at intervals not to exceed 2,500 cycles since last inspection in accordance with GE SB 72-906, dated August 21, 1987. Remove from service, impeller spacers found cracked and replace with a serviceable part. (d) Remove, after October 30, 1990, impeller spacers listed by P/N's in this AD at the next shop visit or within 2,500 cycles since last inspection, whichever occurs first. NOTE: Shop visit is defined as any time the high pressure turbine module is disassembled to a state where the impeller spacer is exposed. Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance times specified in this AD. General Electric SB 72-906, dated August 21, 1987, identified and described in this document, is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request to General Electric, 1 Neumann Way, Cincinnati, Ohio 45215. This document also may be examined in the Office of the Regional Counsel, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket Number 87-ANE-30, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment becomes effective on November 5, 1987.
2000-11-08: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 and 767 series airplanes, that currently requires revising the FAA-approved Airplane Flight Manual (AFM) to prohibit the use of certain fuels; and either replacing an existing placard with a new placard, or replacing all dribble flow fuel nozzles (DFFN) with standard fuel nozzles, which terminates the requirements for the new placard and AFM revision. This amendment continues these requirements and adds identical requirements applicable to airplanes on which standard fuel nozzles are not installed. This amendment is prompted by a report of an engine flameout due to use of JP-4 or Jet B fuel during certification testing on an engine with DFFN's installed. The actions specified by this AD are intended to prevent such engine flameouts and consequent engine shutdown.
2015-05-51: We are publishing a new airworthiness directive (AD) for Agusta Model A109A and A109A II helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD requires replacing a certain part-numbered blade with an approved part- numbered blade. This AD is prompted by an error in the Illustrated Parts Catalog (IPC) that incorrectly allows installation of a certain part-numbered blade on the affected helicopters. These actions are intended to prevent blade failure and subsequent loss of control of the helicopter.
2000-11-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires repetitive inspections of the sliding tube subassembly on the main landing gear (MLG) to detect cracks, and replacement of a cracked subassembly with a new subassembly. This amendment also eventually requires a more extensive, one-time inspection of the same area and corrective actions, if necessary; which terminates the repetitive inspections. 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 cracking of the MLG sliding tube subassembly, which could result in collapse of the MLG.
2000-11-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-200, -300, and -400 series airplanes, that currently requires repetitive high frequency eddy current (HFEC) inspections to detect cracking of the front spar web of the center section of the wing, and repair, if necessary. This amendment requires that the existing inspection be accomplished at a reduced threshold, and adds a requirement that the existing HFEC inspection be accomplished on repaired areas. This amendment is prompted by reports of cracking in repaired areas of the front spar web and cracking of the front spar web on an airplane that had accumulated fewer flight cycles than the inspection threshold of the existing AD. The actions specified by this AD are intended to prevent the leakage of fuel into the forward cargo bay, as a result of fatigue cracking in the front spar web, which could result in a potential fire hazard.
92-21-03: 92-21-03 FOKKER: Amendment 39-8383. Docket No. 92-NM-83-AD. Applicability: Model F28 series airplanes; serial numbers 11003 through 11161, inclusive, 11991, and 11992; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent potential failure of the wing-to-fuselage connection, accomplish the following: (a) Prior to the accumulation of 30,000 landings, or prior to June 1, 1997, whichever occurs later, install improved connection angles with reinforcement angles, in accordance with Fokker Service Bulletin F28/53-101, dated May 31, 1991. (b) Accomplishment of the installation required by paragraph (a) of this AD constitutes terminating action for the inspection identified as item 53-10-14 in the Fokker F28 Structural Integrity Program (SIP), which is required by AD 89-07-16 R1, Amendment 39-6444. (c) 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, Standardization Branch, ANM-113, FAA, Transport 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, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (d) 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. (e) The installation shall be done in accordance with Fokker Service Bulletin F28/53-101, dated May 31, 1991. 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on November 24, 1992.
2000-03-18: This document adopts a new airworthiness directive (AD) that applies to all Partenavia Costruzioni Aeronauticas S.p.A. (Partenavia) Models AP68TP 300 "Spartacus" and AP68TP 600 "Viator" airplanes that are equipped with pneumatic deicing boots. This AD requires you to revise the Airplane Flight Manual (AFM) to include requirements for activating the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to assure that flightcrews have the information necessary to activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. Without this information, flightcrews could experience reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
50-17-02: 50-17-02 STINSON: Applies to All Model 108 Series Aircraft. Compliance required as indicated. A number of cases have been reported of broken core strands in the rudder cables where they pass over the pulley at fuselage Station 18.75 (first pulley aft of rudded pedals). To preclude failures, the following is therefore required: 1. Within the next 25 hours and at every 100 hours thereafter the following should be accomplished. Remove the rudder cables from the pulleys, bend the cables in a tight "U" where they pass over the pulley, being careful that permanent kinks are not formed, and inspect either visually or by touch. Replace all cables showing signs of breakage. 2. The above inspection may be discontinued and the normal inspections resumed if the following is done: Remove the AN 210-3A pulleys at fuselage Station 18.75; modify the pulley brackets and install larger pulleys, P/N 41001-2, and two cable guards, P/N SK253-2, in accordance with detailed instructions in PiperService Bulletin No. 114 or an equivalent modification.