2010-11-02: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
* * * * *
Incomplete closure of the MED [main entry door] may be followed by in-flight opening of the door. As a result, the MED and the adjacent fuselage structure may be damaged during opening and landing impact. Damage to the left engine by flying debris and objects may also occur.
We are issuing this AD to require actions to correct the unsafe condition on these products.
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97-08-02 R1: This document clarifies information in an existing airworthiness directive (AD) that applies to certain Schempp-Hirth K.G. (Schempp-Hirth) Models Standard-Cirrus, Nimbus-2, Nimbus-2B, Mini-Nimbus HS-7, Mini-Nimbus B, Discus a, and Discus b sailplanes. That AD currently requires accomplishing a load test of the elevator control system, and replacing the elevator vertical actuating tube either immediately or at a certain time period depending on the results of the load test. The actions specified in that AD are intended to prevent corrosion in the elevator caused by water entering the elevator control rod, which could result in elevator failure and consequent loss of control of the sailplane. The Schempp-Hirth Models Nimbus 2, Mini-Nimbus HS-7, and Standard Cirrus sailplanes are not equipped with elevator control systems, and should not be affected by the current AD. This action eliminates all reference to the Shempp-Hirth Models Nimbus 2, Mini-Nimbus HS-7, and Standard Cirrus sailplanes in the current AD.
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2012-17-05: We are adopting a new airworthiness directive (AD) for certain Honeywell International Inc. models TFE731-4, -4R, -5, -5R, -5AR, and - 5BR series turbofan engines. This AD was prompted by a report of a rim/ web separation of a first stage low-pressure turbine (LPT1) rotor assembly. This AD requires replacing affected LPT1 rotor assemblies with assemblies eligible for installation. We are issuing this AD to prevent uncontained disk separation, engine failure, and damage to the airplane.
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2012-16-01: We are adopting a new airworthiness directive (AD) for Pratt & Whitney Division PW4052, PW4152, PW4056, PW4156A, PW4060, PW4060A, PW4060C, PW4062, PW4062A, PW4158, PW4460, PW4462, PW4164, PW4164C, PW4164C/B, PW4168, and PW4168A turbofan engines with certain high- pressure turbine (HPT) stage 1 front hubs installed. This AD was prompted by Pratt & Whitney's updated low-cycle-fatigue analysis that indicated certain HPT stage 1 front hubs could initiate a crack prior to the published life limit. This AD requires removing the affected HPT stage 1 front hubs from service using a drawdown plan. We are issuing this AD to prevent failure of the HPT stage 1 front hub, which could lead to an uncontained engine failure and damage to the airplane.
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2012-16-16: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 757 airplanes. This AD was prompted by a report of extensive corrosion of the ballscrew of the drive mechanism of the horizontal stabilizer trim actuator. This AD requires repetitive detailed inspections for discrepancies of the horizontal stabilizer ballscrew assembly; repetitive lubrication of the horizontal stabilizer trim control system; repetitive measurements for discrepancies of the ballscrew to ballnut freeplay; and corrective actions, if necessary. We are issuing this AD to prevent undetected failure of the primary and secondary load paths for the ballscrew in the horizontal stabilizer, which could lead to loss of control of the horizontal stabilizer and consequent loss of control of the airplane.
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98-07-18: This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires replacing certain propeller de-icing controllers with ones that are not susceptible to electromagnetic interference (EMI). This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent improper operation of the propeller de-icing controller caused by EMI, which could result in ice build-up on the propeller with possible airplane controllability problems.
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69-25-09: 69-25-09 BRITISH AIRCRAFT CORPORATION: Amdt. 39-890 as amended by Amendment 39-898 is further amended by Amendment 39-966. Applies to BAC 1-11 Model Airplanes.
Compliance is required as indicated, unless already accomplished.
(a) For airplanes with a passenger dropout system control panel not modified in accordance with Part (C) of British Aircraft Corporation Model BAC 1-11 Service Bulletin No. 33- PM4169, Revision 2, dated 1 October 1969 within the next 75 hours' time in service after the effective date of this AD, add the following to the operating limitations section of Airplane Flight Manual:
(1) Under normal operating conditions when oxygen is not required for use by the passengers, the passenger oxygen system shut-off valve located on the right hand console must be maintained in the OFF position.
(2) Operation with passengers above 30,000 feet is prohibited.
(b) For all airplanes within the next 200 hours' time in service after the effective date of this AD, inspect the center roof panel "E" for signs of overheating, damage, and fouls in accordance with British Aircraft Corporation Model BAC 1-11 Alert Service Bulletin No. 33-A-PM 4169, Issue 1, dated 22 May 1969, or later ARB-approved issue or FAA-approved equivalent.
(c) For airplanes with passenger drop-out oxygen system control panel installed which has not been modified in accordance with Part (C) of British Aircraft Corporation Model BAC 1-11 Service Bulletin No. 33- PM 4169, Revision 2, dated 1 October 1969 (or an FAA- approved equivalent), within the next 200 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 200 hours' time in service since the last test, test the passenger drop-out oxygen system control panel for leaks in accordance with British Aircraft Corporation Model BAC 1-11 Alert Service Bulletin No. 33-A-PM 4169, Issue 1, dated 22 May 1969, or later ARB-approved issue or FAA-approved equivalent.
(d) If leaks are found during the test required by paragraph (c), replace the passenger drop-out oxygen system control panel with a serviceable panel of the same part number or with a serviceable panel which has been modified in accordance with Part (C) of British Aircraft Corporation Model BAC 1-11 Service Bulletin No. 33- PM 4169, Revision 2, dated 1 October 1969, or an FAA-approved equivalent. Test the passenger drop-out oxygen system in accordance with the following:
(1) If the passenger drop-out oxygen system control panel is replaced with a serviceable panel of the same part number, continue to test the passenger drop-out oxygen system control panel for leaks in accordance with paragraph (c).
(2) If the passenger drop-out oxygen system control panel is replaced with a serviceable panel which has been modified in accordance with Part (C) of British Aircraft Corporation Model BAC 1-11 Service Bulletin No. 33-PM 4169, Revision 2, dated 1 October 1969 (or an FAA-approved equivalent),within the next 1,000 hours' time in service after the date of installation and thereafter at intervals not to exceed 1,000 hours' time in service since the last test, test the passenger drop-out oxygen system control panel for leaks in accordance with British Aircraft Corporation Model BAC 1-11 Alert Service Bulletin No. 33-A-PM 4169, Issue 1, dated 22 May 1969, or later ARB-approved issue or FAA-approved equivalent.
(e) For airplanes with a passenger drop-out oxygen system control panel installed which has been modified on or before the effective date of this AD in accordance with Part (C) of British Aircraft Corporation Model BAC 1-11 Service Bulletin No. 33-PM 4169, Revision 2, dated 1 October 1969 (or an FAA-approved equivalent), within the next 200 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 1,000 hours' time in service since the last test, test the passenger drop-out oxygen system control panel for leaks in accordancewith British Aircraft Corporation Model BAC 1-11 Alert Service Bulletin No. 33- A-PM 4169, Issue 1, dated 22 May 1969, or later ARB-approved issue or FAA-approved equivalent.
(f) If leaks are found during the test required by paragraph (e), replace the passenger drop-out oxygen system control panel with a serviceable panel which has been modified in accordance with Part (C) of British Aircraft Corporation Model BAC 1-11 Service Bulletin No. 33-PM 4169, Revision 2, dated 1 October 1969, or an FAA-approved equivalent and continue to inspect in accordance with Paragraph (e).
(g) Upon request of the operator an FAA maintenance inspector (subject to prior approval of the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region) may adjust the repetitive inspection intervals specified in paragraph (e) of this AD to permit compliance at an established inspection of the operator, if the request contains substantiating data to justify the increase for the operator.
(h) For all airplanes on or before 1 July 1970, modify the flight deck roof lighting control panel "E" and panel installation in accordance with Parts (a1), (d1), (d2), (f), (g), and (h) of British Aircraft Corporation Model BAC 1-11 Service Bulletin No. 33-PM 4169, Revision 2, dated 1 October 1969, or an FAA-approved equivalent.
(i) For all airplanes on or before 1 July 1970, replace the existing passenger drop- out oxygen system control panel with a serviceable panel which has been modified to incorporate rigid oxygen pipes in lieu of flexible hoses in accordance with Part (C) of British Aircraft Corporation Model BAC 1-11 Service Bulletin No. 33-PM 4169, Revision 2, dated 1 October 1969, or an FAA-approved equivalent.
(j) When paragraph (i) has been accomplished, the operating limitations required by paragraph (a) may be removed from the Airplane Flight Manual.
Amendment 39-890 effective December 15, 1969.
Amendment 39-898 effective December 19, 1969.
Thisamendment (39-966) becomes effective March 31, 1970.
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2022-06-02: The FAA is superseding Airworthiness Directive (AD) 2013-25- 11, which applied to all Airbus SAS Model A318-111, -112, -121, and - 122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2013-25-11 required repetitive inspections of the 80VU rack lower lateral fittings, upper fittings, and shelves for damage, repetitive inspections of the 80VU rack lower central support for cracking, and corrective action if necessary. AD 2013-25-11 also specified optional terminating action for the repetitive inspections. Since the FAA issued AD 2013-25-11, new damage occurrences have been reported, and a different compliance time has been determined for certain inspections, depending on airplane configuration. This AD expands the applicability, removes the optional terminating action, and requires new repetitive inspections; 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.
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2010-10-14: We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS332L2 helicopters. This AD results from a mandatory continuing airworthiness information (MCAI) AD issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI AD states that the AD was issued after the discovery of broken swashplate bearing attaching screw heads. Failure of these screw heads could lead to the loss of the coupling between the non-rotating and the rotating swashplate. This AD is intended to prevent loss of power to the rotating swashplate and subsequent loss of control of the helicopter.
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93-11-10: 93-11-10 CORPORATE JETS, LIMITED, (FORMERLY BRITISH AEROSPACE): Amendment 39-8602. Docket 93-NM-40-AD.
Applicability: Model BAe 125-1000A series airplanes, as listed in Corporate Jets, Limited, Alert Service Bulletin S.B. 71-A43, dated February 9, 1993; certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To ensure the fireproof integrity of the engine fan duct material, which will reduce the hazards associated with an engine fire, accomplish the following:
(a) Within 7 days after the effective date of this AD, conduct a detailed visual inspection along the longitudinal seams of the outside surface of the outer fan duct on the right and left engines to detect fluid contamination or disbonding at the edges of the seams, in accordance with Corporate Jets, Limited, Alert Service Bulletin S.B. 71-A43, dated February 9, 1993.
(b) If no fluid contamination or disbonding is detected, accomplish paragraphs (b)(1) and (b)(2) of this AD.
(1) Thereafter repeat the visual inspection required by paragraph (a) of this AD at intervals not to exceed 14 days until the modification required by paragraph (b)(2) of this AD is accomplished.
(2) Within 300 hours time-in-service after the effective date of this AD, modify the longitudinal seams of the outside surface of the outer fan duct on the right and left engines, in accordance with Corporate Jets, Limited, Service Bulletin SB.71-43-3644A, dated February 8, 1993. Accomplishment of this modification constitutes terminating action for the repetitive inspections required by paragraph (b)(1) of this AD.
(c) If fluid contamination only is detected, accomplish paragraphs (c)(1) and (c)(2) of this AD.
(1) Repeat the detailed visual inspection required by paragraph (a) of this AD prior to the first flight of each day until the modification required by paragraph (c)(2) of this AD is accomplished.
(2) Within 50 hours time-in-service after the effective date of this AD, modify the longitudinal seams of the outside surface of the outer fan ducts on the right and left engines, in accordance with Corporate Jets, Limited, Service Bulletin SB.71-43-3644A, dated February 8, 1993. Accomplishment of this modification constitutes terminating action for the repetitive inspections required by paragraph (c)(1) of this AD.
(d) If disbonding is detected at the longitudinal seams, prior to further flight, modify the longitudinal seams of the outside surface of the outer fan duct on the right and left engines, in accordance with Corporate Jets, Limited, Service Bulletin SB.71-43-3644A, dated February 8, 1993.
(e) 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.
(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 inspection shall be done in accordance with Corporate Jets, Limited, Alert Service Bulletin S.B. 71-A43, dated February 9, 1993. The modification shall be done in accordance with Corporate Jets, Limited, Service Bulletin SB.71-43-3644A, dated February 8, 1993. 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 Corporate Jets, Inc., 22070 Broderick Drive, Sterling, Virginia 20166. 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.
(h) This amendment becomes effective on June 29, 1993.
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