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84-03-05: 84-03-05 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-4808. Applies to Lockheed Model L-1011-385 series airplanes, certificated in all categories. Compliance required as indicated unless previously accomplished.
To prevent the possibility of a fire hazard due to electrical arcing in two aft body compartments, accomplish the following:
A. Prior to 300 flight hours after the effective date of this AD, perform the aircraft wiring inspection and corrective action, if necessary, in accordance with Part 2, Accomplishment Instructions, in Lockheed-California Company L-1011 Service Bulletin 093-27-285, dated July 12, 1983, or later revision approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.
B. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.
NOTE: Airplanes previously inspected inaccordance with Lockheed L-1011 Service Bulletin 093-27-285, dated July 12, 1983, or in accordance with alternate inspection procedures since June 24, 1983, approved by an FAA Principal Maintenance Inspector (PMI), are considered to comply with the inspection requirements of this AD.
C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.
All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Support Contracts, Dept. 63-11, U-33, B-1. These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California.
This amendment becomes effectiveFebruary 21, 1984.
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2007-15-02: The FAA is adopting a new airworthiness directive (AD) for all Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD requires revising the Certification Maintenance Requirements and the Maintenance Review Board Report sections of the Canadair Regional Jet Maintenance Requirements Manual to include changes and additions to checks of the aileron power control units (PCUs) and a change to the interval of the backlash check of the aileron control system. This AD results from a report that data collected from in- service airplanes show that approximately 19 percent of aileron backlash checks conducted at 4,000-flight-hour intervals reveal that aileron backlash wear limits are being exceeded. We are issuing this AD to prevent exceeded backlashes in both aileron PCUs, which, if accompanied by the failure of the flutter damper, could result in aileron vibration/flutter and reduced controllability of the airplane.
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2007-15-03: We are adopting a new airworthiness directive (AD) for the products listed above. 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:
Service experience showed that the connection screw of the propeller blade follower type 10AP-VM may break and the main part of the blade follower can be lost in flight. This condition, if not corrected, could lead to high vibration during powered flight and consequently result in decreased control of the aircraft.
We are issuing this AD to require actions to correct the unsafe condition on these products.
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2019-21-03: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-1A11 (600), CL-600-2A12 (601), and CL-600-2B16 (601-3A and 601-3R Variants) airplanes. This AD was prompted by reports of the loss of all air data system information provided to the flightcrew, which was caused by icing at high altitudes. This AD requires revising the existing airplane flight manual (AFM) to provide the flightcrew with procedures for ``Unreliable Airspeed'' that stabilize the airplane's airspeed and attitude. The FAA is issuing this AD to address the unsafe condition on these products.
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2007-14-07: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211-524 and -535 series turbofan engines. This AD requires initial and repetitive fluorescent penetrant inspections (FPI) of the high pressure (HP) compressor stage 1 and 2 rotor discs for cracks. This AD results from reports of low-cycle- fatigue cracks found at overhaul in the interface weld between the HP compressor stage 1 and 2 rotor disc. We are issuing this AD to prevent uncontained engine failure and damage to the airplane.
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99-16-01: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Industrie Model A300-600 series airplanes, that currently requires repetitive high frequency eddy current inspections to detect cracks in bolt holes where parts of the main landing gear are attached to the rear spar, and repair, if necessary. This amendment requires repetitive ultrasonic inspections to detect cracking in certain bolt holes of the rear spar, and repair, 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 cracking of the rear spar of the wing, which could result in reduced structural integrity of the airplane.
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89-07-10: 89-07-10 BOEING: Amendment 39-6175. \n\tApplicability: All Model 767 series airplanes, identified in Boeing Alert Service Bulletin 767-25A0104, Revision 1, dated September 29, 1988, certificated in any category. \n\n\tCompliance: Required within 6 months after the effective date of this AD, unless previously accomplished. \n\n\tTo ensure that the off-wing escape slide does not inadvertently deploy due to a disengaged integrator hook, accomplish the following: \n\n\tA.\tReplace the integrator hook and rig the latch opening actuator and compartment door opening actuator, in accordance with Boeing Alert Service Bulletin 767-25A0104, Revision 1, dated September 29, 1988. \n\n\tB.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6175, AD 89-07-10) becomes effective on April 28, 1989.
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2019-22-01: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by a report of an escapement from the wing spar terminal fitting supplier indicating that the engineering requirements provided by Boeing for controlling machine mismatch were incorrect for part faying surfaces, which can result in a reduced fatigue capability at the interface of the side of body (SOB) rib. This AD requires repetitive inspections for fatigue cracking and applicable on-condition actions for the SOB rib webs where fastener locations attach the terminal fittings. The FAA is issuing this AD to address the unsafe condition on these products.
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99-27-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires wiring modifications to the engine and auxiliary power unit (APU) fire detection system. 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 the fire warning from terminating prematurely, which could result in an unnoticed, uncontained engine/APU fire.
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95-04-07: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-10 series airplanes and KC-10A (military) airplanes. This action requires inspections to determine the condition of the lockwires on the forward engine mount bolts and correction of any discrepancies found. This action also provides for termination of the inspections for some airplanes by installing retainers on the bolts. This amendment is prompted by reports of stretched or broken lockwires on the forward engine mount bolts. The actions specified in this AD are intended to prevent broken lockwires, which could result in loosening of the engine mount bolts, and subsequent separation of the engine from the airplane.\n\n\tComments for inclusion in the Rules Docket must be received on or before May 1, 1995.
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