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85-16-07: 85-16-07 MCDONNELL DOUGLAS: Amendment 39-5103. Applies to McDonnell Douglas Model DC-9 and C-9 (Military) series airplanes, certificated in any categories. Compliance required as indicated unless previously accomplished. \n\n\tTo assure the fire containment capability of the lavatory waste containers, accomplish the following: \n\n\tA.\tWithin 18 months after the effective date of this airworthiness directive (AD), modify the forward and/or aft lavatory waste containers in accordance with the Accomplishment Instructions of McDonnell Douglas DC-9 Service Bulletin 25-259, dated April 11, 1984, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \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 these documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). 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. \n\n\tThis amendment becomes effective August 26, 1985.
98-10-02: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that requires replacement of certain wheel tie bolts with new bolts; and placing a life limit on these wheel tie bolts. 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 metal fatigue failure of the wheel tie bolts, which could result in a tire burst or loss of the main wheel/tire assembly, and consequent reduced controllability of the airplane.
99-21-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Falcon 2000 series airplanes, that requires a detailed inspection for interference between the safety-lock hooks and upper cowls, and corrective action, if necessary. This amendment also requires modification of the attachment supports of the inner locking hooks; and a detailed inspection of the safety-lock hooks on the lower engine cowl for proper operation and for clearance between the outer edges of the upper and lower cowls; 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 prevent unintended disengagement of the engine cowl hooks during ground maintenance, which could result in in-flight loss of an engine cowl from the airplane and possible damage to the airplane and persons or property on the ground.
98-06-35: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model SA-366G1 helicopters. This action requires initial and repetitive inspections of the tail rotor blade Kevlar tie-bar (Kevlar tie-bar) for delaminations. This amendment is prompted by a report of delamination of a Kevlar tie-bar. The actions specified in this AD are intended to detect delaminations of the Kevlar tie-bar, that could result in loss of anti-torque function and subsequent loss of control of the helicopter.
98-03-17: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model HS 748 series airplanes. This action requires repetitive inspections to detect discrepancies of the gust locks of the flight control system, re-rigging of the gust lock system; and corrective action, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect and correct failure of the flight control gust lock system, which could result in reduced controllability of the airplane.
85-14-51 R2: 85-14-51 R2 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39- 5185 as amended by Amendment 39-5440, is further amended by Amendment 39-6207. Applicability: Model DHC-8-100 series airplanes, serial numbers up to and including 93, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To minimize the danger of lightning transient-induced damage to the electronic engine control units, accomplish the following: A. Prior to further flight, incorporate the following limitations into the Limitations Section of the Airplane Flight Manual (AFM). This may be accomplished by including a copy of this AD in the AFM: 1. To preclude unacceptable loss of power during critical phases of flight, takeoff is prohibited when lightning or thunderstorms are observed or reported within 5 nautical miles of the takeoff climb path of the airplane, or when existing weather conditions may reasonably be expected to result in a lightning strike. 2. Operating with engine ignition selected to manual is required when operating below 1500 feet AGL with 5 nautical miles of any observed or reported lightning or thunderstorms, of any weather condition that may reasonably be expected to result in a lightning strike. B. Within 12 months after the effective date of this amendment, install the following modifications. Installation of all four of these modifications constitutes terminating action for this AD, and the operating limitations required by paragraph A., above, may then be removed from the AFM. 1. Modification No. 8/0597, installation of left and right shielded harnesses incorporating electronic control unit (ECU) and signal conditioning unit (SCU) wiring, in accordance with de Havilland DHC-8 Service Bulletin 8-73-7, Revision E, dated October 14, 1988. 2. Modification No. 8/0598, installation of improved engine grounding jumpers, in accordance with de Havilland DHC-8 Service Bulletin 8-71-10, Revision B, dated October 14, 1988. 3. Modification 8/0964, replacement of the electrical wiring harness assembly, in accordance with de Havilland DHC-8 Service Bulletin 8-72-2, Revision A, dated October 14, 1988. 4. Modification 8/0813, installation of an SCU grounding strap on Pratt & Whitney PW120A engines, in accordance with de Havilland DHC-8 Service Bulletin 8-72-4, Revision A, dated October 14, 1988. C. 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, New York Aircraft Certification Office (ANE-170), FAA, Engine and Propeller Directorate, Aircraft Certification Service. NOTE: If appropriate, the request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment, and then send it to the Manager, New York Aircraft Certification Office. D. 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 the appropriate service documents from the manufacturer may obtain copies upon request to Boeing of Canada Ltd., de Havilland Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the FAA, New York Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, 181 South Franklin Avenue, Room 202, Valley Stream, New York. Amendment 39-5185, AD 85-14-51 became effective December 26, 1985, as to all persons, except those persons to whom it was made immediately effective by telegraphic AD T85- 14-51 issued July 12, 1985. Amendment (39-5440, AD 85-14-51 R1) became effective on October 27, 1986. This amendment (39-6207, AD 85-14-51 R2) becomes effective on June 9, 1989.
85-07-10: 85-07-10 MCDONNELL DOUGLAS: Amendment 39-5034. Applies to McDonnell Douglas Model DC-9 and C-9 (Military) series airplanes, fuselage numbers 1 through 855, certificated in all categories. Compliance required as indicated unless previously accomplished. \n\n\tTo eliminate a potential ignition source from the forward and aft lavatories, accomplish the following: \n\n\tA.\tWithin 12 months after the effective date of this airworthiness directive (AD), reroute the toilet flush motor power wire harness in the forward and aft lavatories in accordance with the Accomplishment Instructions of McDonnell Douglas DC-9 Service Bulletin 24-76, dated November 7, 1984, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \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 these documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). 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. \n\n\tThis amendment becomes effective May 13, 1985.
87-05-01: 87-05-01 HARTZELL PROPELLER PRODUCTS DIVISION: Amendment 39-5554. Applies to Hartzell Model HC-B5MP-3( )/M10876( ) propellers installed on Short Brothers Ltd. Model SD3-60 aircraft. Compliance required prior to accumulating 3,000 hours time in service since new, or within 30 days after the effective date of this AD, whichever occurs later, unless already accomplished. To prevent propeller blade separation near the hub which could result in cabin penetration and/or engine separation from the aircraft, accomplish the following: (a) Remove propeller from aircraft. (b) Accomplish the following in accordance with Hartzell Service Bulletin No. 136C, dated March 3, 1986, or FAA approved equivalent: (1) Disassemble propeller and visually inspect the blade pilot tube bore area. Particular attention shall be made to the area between the inner needle bearing assembly and bearing spacer. (2) Remove all evidence of scratches, tool marks, corrosion, scrapes, pitting, or other surface irregularities in the blade pilot tube bore area. Do not exceed the maximum rework limitations defined in the service bulletin. (3) Etch the blade pilot tube bore area prior to penetrant inspection. Ensure removal of all etching solution. (4) Penetrant inspect the blade pilot tube bore area. (5) Coat the blade pilot tube bore area with alodine. (6) Install bearing spacer and inner needle bearing assembly. Pilot tube bore must be lubricated to facilitate bearing installation. (c) Replace, prior to further flight, all blades showing evidence of cracks or other unairworthy conditions with airworthy blades. NOTES: 1) Propeller blades with serial numbers subsequent to F75966 have had the requirements of this AD incorporated during manufacture and are not affected by this AD. 2) Compliance with Hartzell Service Bulletins 136, dated August 26, 1982, 136A, dated July 12, 1983, or 136B, dated January 28, 1986, does not constitute compliance with this AD. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations (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, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des Plaines, Illinois 60018. Hartzell Service Bulletin No. 136C, dated March 3, 1986, 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 Hartzell Propeller Products Division, TRW Aircraft Components Group, 350 Washington Avenue, Piqua, Ohio 45356. This document also may be examined at the Office of the Regional Counsel, FAA, Attn: Rules Docket No. 87-ANE- 2, 12 New England Executive Park, Burlington, Massachusetts 01803, weekdays, except Federal holidays, between 8:00 a.m. and 4:30 p.m. This amendment becomes effective on March 12, 1987.
86-18-04: 86-18-04 BOEING: Amendment 39-5385. Applies to Model 737 series airplanes, line numbers 930 and above, listed in Boeing Service Letter 737-SL-27-38, dated January 16, 1986, certificated in any category. To detect nuts installed at the Body Buttock Line (BBL) 70.85 wing-to-body splice plate, the thrust reverser secondary deactivation pin, and the vertical fin front spar to closure rib attachments, that have insufficient self-locking torque characteristics, accomplish the following, unless already accomplished: \n\n\tA.\tWithin the next 18 months after the effective date of this AD, check the self- locking nuts, P/N BACN10JC12CM and P/N BACN10JC12CD, for proper self-locking torque in accordance with Paragraph II of Boeing Service Letter 737-SL-27-38, dated January 16, 1986, or later FAA-approved revision. If any self-locking nut does not meet the torque criteria specified in the service letter, replace it prior to further flight with an appropriate nut which meets the torque criteria. \n\n\tB.\tAn alternate means of the 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\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. 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. \n\n\tThis amendment becomes effective September 11, 1986.
2000-15-13: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires a one-time inspection to verify correct wire terminations of certain circuit breakers in the cockpit overhead switch panel; and correction of incorrect wire termination. That AD also requires that operators submit a report of the inspection results to the FAA. That AD was prompted by incidents in which the wiring of circuit breakers on the overhead switch panel lighting were found to be terminated improperly during production of the airplane, which bypassed the circuit breaker protection. This amendment expands the applicability of the existing AD to include additional airplanes, and removes the reporting requirement. The actions specified in this AD are intended to prevent smoke and possible fire in the overhead switch panel lighting circuitry due to an overload condition, as a result of lack of circuit breaker protection. \n\n\tThe incorporation by reference of McDonnell Douglas Alert Service Bulletin MD11-33A027, dated March 10, 1999, as listed in the regulations, was approved previously by the Director of the Federal Register as of May 7, 1999 (64 FR 19695, April 22, 1999).\n\n\tThe incorporation by reference of certain other publications listed in the regulations is approved by the Director of the Federal Register as of August 23, 2000.\n\n\tComments for inclusion in the Rules Docket must be received on or before October 10, 2000.