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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.