Results
80-04-11 R2: 80-04-11 R2 ROCKWELL INTERNATIONAL: Amendment 39-3703 as amended by Amendment 39-3921 is further amended by Amendment 39-4611. Applies to Rockwell Model NA 265-60 and NA 265-80 airplanes completely or partially modified by The Raisbeck Group in accordance with Raisbeck STC's SA687NW or SA847NW. To prevent structural failure of the airframe, accomplish a comprehensive inspection of all areas modified by The Raisbeck Group as follows: A. Before further flight, inspect for deviations from the supplemental type design in accordance with Paragraphs I through IV and VI of FAA approved Raisbeck Service Bulletin No. 25. Inspect for discrepancies such as: 1. Plugged holes 2. Oblong, eggshaped, oversized, or irregular holes 3. Tapered holes 4. Excess holes 5. Inadequate edge distances 6. Gouges 7. Improper fasteners (type and number) 8. Improper clearances 9. Any other irregularities which are not consistent with standard aircraftpractice. B. Deleted by Amendment 39-3921. C. Before accumulation of 2000 flight hours time in service after modification by STC SA687NW or STC SA847NW, inspect the wing leading edge in accordance with Raisbeck Service Bulletin No. 33. Repeat this inspection every 300 flight hours time in service thereafter. D. Deleted by Amendment 39-4611. E. Inspections are to be conducted at facilities specifically authorized by the Manager, Aircraft Certification Branch, FAA, Northwest Mountain Region. F. Discrepancies discovered as a result of the inspections are to be reported to the Manager, Aircraft Certification Branch, FAA, Northwest Mountain Region. Repair or modifications required because of these problems are to be FAA approved by the Manager, Aircraft Certification Branch, FAA, Northwest Mountain Region or specifically authorized DER's. G. Airplanes may be ferried, in accordance with FAR 21.199, to a maintenance base for the purpose of complying with this AD. H. The inspections noted herein may be accomplished as noted or in a manner approved by the Manager, Aircraft Certification Branch, FAA, Northwest Mountain Region. I. Deleted by Amendment 39-4611. The manufacturer's specifications and procedures identified and described in this directive are 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 these documents from the manufacturer may obtain copies upon request from Rockwell International, Sabreliner Division, 6161 Aviation Drive, St. Louis, Missouri 63134. These documents may also be examined at FAA, Central Region, Wichita Aircraft Certification Office, Room 238, Terminal Building 2299, Mid-Continent Airport, Wichita, Kansas, or FAA, Northwest Mountain Region, Office of Regional Counsel, 17900 Pacific Highway South, Seattle, Washington 98168, telephone (206) 764-7019. Amendment 39-3703 became effective upon publication in the Federal Register and was effective earlier to all recipients of the telegraphic AD T80-NW-2 dated January 17, 1980. Amendment 39-3921 became effective October 1, 1980. This Amendment 39-4611 becomes effective April 13, 1983.
2010-17-11R2: We are revising airworthiness directive (AD) 2010-17-11R1, which applies to all Dowty Propellers R408/6-123-F/17 model propellers. AD 2010-17-11R1 required initial application of sealant between the bus bar assembly and the backplate assembly of certain line-replaceable units (LRUs) and repetitive re-applications of sealant on all R408/6- 123-F/17 model propellers. AD 2010-17-11R1 also provided an optional terminating action to the repetitive re-application of sealant. This AD increases the interval allowed between the required re-application of sealant, and specifies an additional acceptable sealant. This AD was prompted by failure of the propeller de-ice bus bar due to friction or contact between the bus bar and the backplate assembly, consequent intermittent short circuit, and possible double generator failure. We are issuing this AD to prevent an in-flight double generator failure, which could result in reduced control of the airplane.
2014-24-01: We are adopting a new airworthiness directive (AD) for all Harry E. Williams de Havilland Model DH 82A airplanes, all Cliff Robertson de Havilland Model DH 82A airplanes, and all de Havilland Model DH 83 airplanes. This AD was prompted by reports of structural failure of the attachment of the wing to the fuselage that resulted from failed lateral fuselage tie rods. This AD requires inspecting the aircraft maintenance records to determine the date of installation or the date of last replacement of the lateral fuselage tie rods. This AD also requires repetitively replacing all lateral fuselage tie rods and attaching nuts at a specified life limit interval. We are issuing this AD to correct the unsafe condition on these products.
2000-06-04: This document adopts a new airworthiness directive (AD) that applies to all Fairchild Aircraft Corporation (Fairchild) SA226 and SA227 series airplanes that are equipped with pneumatic deicing boots. This AD requires revising 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 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 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.
2014-24-02: We are superseding Airworthiness Directive (AD) 2014-07-51 for AgustaWestland S.p.A. Model AB139 and AW139 helicopters with certain main rotor (M/R) rotating scissors installed. AD 2014-07-51 required repetitively inspecting the M/R rotating scissors for play of the lower half scissor spherical bearing (bearing) and removing the bearing if there was play beyond allowable limits. AD 2014-07-51 also required removing all affected bearings. AD 2014-07-51 was prompted by reports of certain bearings dislodging from certain M/R rotating scissors. This new AD retains the requirements of AD 2014-07-51, expands the applicability, and requires installing a special nut. These actions are intended to detect excessive play of the bearing and prevent failure of the M/R rotating scissors and subsequent loss of control of the helicopter.
79-06-06 R2: 79-06-06 R2 AVCO LYCOMING DIVISION: Amendment 39-3440 as amended by Amendment 39-3506 is further amended by Amendment 39-3795. Applies to all LTS101-600A, -600B, -600A-2, and -650A-2 turboshaft and LTP101-600 and -600A turboprop engines. Compliance required as indicated. 1. To prevent undetected lubrication system contamination leading to oil starvation of engine bearings and subsequent engine stoppage, accomplish the following within the next 5 hours of engine operation unless already accomplished and every 25 hours thereafter: Perform a spectrometric oil analysis as outlined in the applicable Avco Lycoming Engine Maintenance Manual, Chapter 71-00-00, and in accordance with Avco Lycoming Alert Notice, Reference 3V- W714, dated February 16, 1979, or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. If any of the following spectrometric oil analysis limits are exceeded, inspect and repair, prior to further flight, in accordance with Chapter 72-00-00, Paragraph 13, of the appropriate Avco Lycoming Engine Maintenance Manual: a. Iron content, six parts per million. b. Between consecutive spectrometric oil analysis, iron content increases by three parts per million. c. Any other metal, five parts per million. NOTE: Engine operation not to exceed 4 calendar days or 25 hours between extraction of oil sample and obtaining spectrometric oil analysis results is authorized. 2. For LTP101-600 and 600A turboprop engines, S/N LE 50001 through S/N LE 50017, the requirements of paragraph 1 may be discontinued after the power turbine rotor assembly P/N 4-143-010-01/-02 is replaced with either: a. Rotor assembly P/N 4-143-010-01/02 with "APOLS93277" etched on rear face of wrenching surface, or b. Rotor assembly P/N 4-143-010-03, in accordance with Avco Lycoming Service Bulletin No. LTP101-72-0003, Revision 1, dated May 21, 1979, or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. 3. For LTS101-600A, -600B, -600A-2, and -650A-2 turboshaft engines, the requirements of Paragraph 1 may be discontinued if the engine installation incorporates a full flow scavenge chip detector, TEDECO P/N A615 or equivalent, installed in accordance with STC SH2929SW or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. 4. For all engines affected by this AD, the requirements of Paragraph 1 may be discontinued if the equivalent means of detecting lubrication system contamination, approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region, are effected. Avco Lycoming Alert Notice, Reference 3V-W714, dated February 16, 1979, and Service Bulletin No. LTP101-72-0003, Revision 1, dated May 21, 1979, refer to this subject. The manufacturer's Alert Notice, Service Bulletin, and Manuals identified and described in this directive are incorporated herein and madea part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Director, Customer Service, Avco Lycoming Division, 550 South Main Street, Stratford, Connecticut 06514. These documents may also be examined at Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. Amendment 39-3440 became effective upon publication in the FEDERAL REGISTER except for recipients of the Emergency AD, dated February 23, 1979, for whom it became effective upon receipt. Amendment 39-3506 became effective upon publication in the FEDERAL REGISTER. This Amendment 39-3795 becomes effective June 2, 1980.
2000-05-24: This amendment adopts a new airworthiness directive (AD) that applies to all aircraft equipped with a certain Honeywell International Inc. (Honeywell) KAP 140 or KFC 225 autopilot system. AlliedSignal Avionics Inc. manufactured these autopilot systems before transferring the design data to Honeywell. This AD requires that you inspect the autopilot servo actuator for a loose fastener and modify the autopilot servo actuator when a loose fastener is found. This AD is the result of a report of failure of the autopilot servo actuator to disengage when the autopilot power was removed. The actions specified by this AD are intended to detect and correct a loose fastener in the autopilot servo actuator, which could cause the autopilot servo actuator to not disengage when power to the autopilot is removed. This could cause the pilot to experience additional control forces.
53-11-02: 53-11-02 de HAVILLAND: Applies to Model DHC-2 (Beaver) Aircraft, Serial Numbers 1 to 445 Inclusive. Compliance required as indicated. Cases have been reported of chafing of the engine oil sump by section assemblies. (P/N C2-E-105ND) and (P/N C2-E-107ND) of accessory firewall. An enlarged flange clearance is required to be incorporated as soon as possible but not later than the next 100 hours. The FAA concurs in this mandatory action by the Canadian Department of Transport. (de Havilland Technical News Sheet, Series B, No. 64 dated March 23, 1953, available from de Havilland Aircraft of Canada, Ltd., Toronto, Ontario, Canada, covers this same subject and describes method of repair.)
90-25-16: 90-25-16 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39- 6827. Docket No. 90-NM-147-AD. Applicability: All de Havilland Model DHC-7 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent possible malfunction of the right main landing gear (MLG), accomplish the following: A. Within 100 landings after May 29, 1990 (the effective date of AD 90-09-02), and thereafter at intervals not to exceed 500 landings, conduct a visual inspection of the right MLG frame and attachment bolts, in accordance with paragraph A. of the Accomplishment Instructions in de Havilland Service Bulletin No. 7-24-66, Revision B, dated June 23, 1989. 1. If no damage is found, reassemble parts and return the airplane to service. 2. If damage is found, replace with serviceable parts prior to further flight, in accordance with the service bulletin. B. Within 180 days after the effective date ofthis AD, install Modification No. 7/2577, which relocates the external power grounding stud, in accordance with paragraph B of the Accomplishment Instructions in de Havilland Service Bulletin No. 7-24-66, Revision B, dated June 23, 1989. Installation of this modification constitutes terminating action for the repetitive inspections required by paragraph A., above. 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 (ACO), ANE-170. NOTE: The request should be submitted directly to the Manager, New York Aircraft ACO, ANE-170, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, New York ACO, ANE-170. 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. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York. Airworthiness Directive 90-25-16 supersedes AD 90-09-02, Amendment 39-6579. This amendment (39-6827, AD 90-25-16) becomes effective on January 14, 1991.
91-18-13: 91-18-13 SHORT BROTHERS, PLC: Amendment 39-8015. Docket No. 91-NM-92-AD. Supersedes AD 91-04-06. Applicability: Model SD3-30 series airplanes, as listed in Short Brothers Service Bulletin SD330-24-25, Revision 2, dated November 29, 1990; and Model SD3-60 series airplanes, as listed in Short Brothers Service Bulletin SD360-24-18, Revision 3, dated November 29, 1990; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent loss of power to the pitot/static heaters and subsequent incorrect airspeed and altitude information being provided to the pilot and/or co-pilot in the event of a generator or engine failure, accomplish the following: A. For Model SD3-30 series airplanes, Serial Numbers SH3002 through SH3072: Within 180 days after the effective date of this AD, revise the power source for the pitot/static heaters, in accordance with Part A of the Accomplishment Instructions in Short Brothers Service Bulletin SD330-24-25, Revision 2, dated November 29, 1990. Following accomplishment of this modification, revise the Emergency and Normal Procedures Sections of the FAA-approved Airplane Flight Manual (AFM) by inserting AFM Amendment Document No. SBH 3.3 (ref. change P/15) or SBH 3.6 (ref. change P/11), as applicable. B. For Model SD3-30 series airplanes, Serial Numbers SH3073 and subsequent: Within 180 days after the effective date of this AD, revise the power source for the pitot/static heaters, in accordance with Part B of the Accomplishment Instructions in Short Brothers Service Bulletin SD330-24-25, Revision 2, dated November 29, 1990. Following accomplishment of this modification, revise the Emergency and Normal Procedures Sections of the FAA-approved AFM by inserting AFM Amendment Document No. SBH 3.3 (ref. change P/15) or SBH 3.6 (ref. change P/11), as applicable. C. For Model SD3-60 series airplanes, Serial Numbers SH3601 through SH3619: Within 180 days after the effective date of this AD, revise the power source for the pitot/static heaters, in accordance with the Part A of the Accomplishment Instructions in Short Brothers Service Bulletin SD360-24-18, Revision 3, dated November 29, 1990. Following accomplishment of this modification, revise the Emergency and Normal Sections of the FAA-approved AFM by inserting AFM Amendment Document No. SB 4.3 (ref. change P/18), SB 4.6 (ref. change P/11), or SB 4.8 (ref. change P/8), as applicable. D. For Model SD3-60 series airplanes, Serial Numbers SH3620 through SH3676: Within 180 days after the effective date of this AD, revise the power source for the pitot/static heaters, in accordance with the Part B of the Accomplishment Instructions in Short Brothers Service Bulletin SD360-24-18, Revision 3, dated November 29, 1990. Following accomplishment of this modification, revise the Emergency and Normal Procedures Sections of the FAA-approved AFM by inserting AFM Amendment Document No. SB 4.3 (ref. change P/18),SB 4.6 (ref. change P/11), or SB 4.8 (ref. change P/8), as applicable. E. For Model SD3-60 series airplanes, Serial Numbers SH3677 through SH3762: Within 180 days after the effective date of this AD, revise the power source for the pitot/static heaters, in accordance with the Part C of the Accomplishment Instructions in Short Brothers Service Bulletin SD360-24-18, Revision 3, dated November 29, 1990. Following accomplishment of this modification, revise the Emergency and Normal Procedures Sections of the FAA-approved AFM by inserting AFM Amendment Document No. SB 4.3 (ref. change P/18), SB 4.6 (ref. change P/11), or SB 4.8 (ref. change P/8), as applicable. F. 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. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector,who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. G. 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. H. The modification requirement shall be done in accordance with Short Brothers Service Bulletin SD330-24-25, Revision 2, dated November 29, 1990, and Short Brothers Service Bulletin SD360-24-18, Revision 3, dated November 29, 1990. The revisions to the Airplane Flight Manual (AFM) shall be done in accordance with the following list of AFM Amendment Documents and related effective pages: AFM Amendment Document Number Page Number Section Number SBH 3.3 17 37 3 4 SBH.3.6 17 43 3 4 SB.4.3 15 43 3 4 SB.4.6 15 43 3 4 SB.4.8 15 43 3 4 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 Short Brothers, PLC, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3719. Copies may be inspected at the FAA, Transport Airplane Directorate, Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. Airworthiness Directive 91-18-13 supersedes AD 91-04-06 Amendment 39-6897. This amendment (39-8015, AD 91-18-13) becomes effective on October 16, 1991.
89-03-14: 89-03-14 AIRBUS INDUSTRIE: Amendment 39-6125. Applicability: Model A300-600 series airplanes, as listed in Airbus Industrie Service Bulletin A300-53-6024, Revision 1, dated July 8, 1988. Compliance: Required as indicated, unless previously accomplished. To prevent separation of the rear passenger/crew door from the airplane and subsequent rapid decompression, accomplish the following: A. Prior to the accumulation of 8,000 landings or within the next 1,000 landings after the effective date of this AD, whichever occurs later, inspect frame 73A RH and LH between beams 5 and 7 in accordance with Airbus Industrie Service Bulletin A300-53-6024, Revision 1, dated July 8, 1988. 1. If cracks are detected that are less than 0.4 inch, modify the frame within the next 2,500 landings, in accordance with Airbus Industrie Service Bulletin A300-53-6019, Revision 3, dated October 13, 1988. The inspection must be repeated at intervals not to exceed 1,250 landings until the modification is accomplished. 2. If cracks are detected that are equal to or more than 0.4 inch but less than 0.8 inch, modify the frame within the next 1,500 landings, in accordance with Airbus Industrie Service Bulletin A300-53-6019, Revision 3, dated October 13, 1988. The inspection must be repeated at intervals not to exceed 750 landings until the modification is accomplished. 3. If cracks are detected that are equal to or more than 0.8 inch, prior to further flight, modify the frame in accordance with Airbus Industrie Service Bulletin A300-53- 6019, Revision 3, dated October 13, 1988. 4. If no cracks are detected, repeat the inspection at intervals not to exceed 4,000 landings. B. The repetitive inspections required by paragraph A., above, may be terminated following completion of the modification of the door frame structure in accordance with Airbus Service Bulletin A300-53-6019, Revision 3, dated October 13, 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, 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. D. 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 inspections and/or modifications required by 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6125, AD 89-03-14) becomes effective March 7, 1989.
2000-06-02: This document adopts a new airworthiness directive (AD) that applies to all Dornier Luftfahrt GmbH (Dornier) 228 series airplanes that are equipped with pneumatic deicing boots. This AD requires revising 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 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 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.
2000-05-27: This amendment supersedes an existing airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146-100A, -200A, and -300A series airplanes, that currently requires either a one-time nondestructive test (NDT) inspection or a detailed visual inspection for cracking of the fuselage skin in the vicinity of frame 29 between stringers 12 and 13, and repair, if necessary. This amendment requires that the current thresholds for these inspections be reduced and that repetitive inspections be performed. 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 fatigue cracking of the fuselage skin in the specified area, which could result in reduced structural integrity of the airplane.
2000-05-19: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 727 series airplanes, that requires a one-time detailed visual inspection of the fuselage skin and bonded doubler area above the forward entry doorway to detect fatigue cracking or the existence of certain repairs, and follow-on corrective actions, if necessary. This action also requires a preventive modification or full-sized repair doubler, as applicable. This amendment is prompted by reports of fatigue cracking in the fuselage skin and bonded doublers in the forward and aft corners above the forward entry doorway. The actions specified by this AD are intended to prevent such fatigue cracking of the fuselage skin and bonded doubler, which could result in reduced structural integrity and consequent loss of cabin pressurization.
2000-06-03: This document adopts a new airworthiness directive (AD) that applies to all Bombardier Inc. (Bombardier) Models DHC-6-1, DHC-6-100, DHC-6-200, and DHC-6-300 airplanes that are equipped with pneumatic deicing boots. This AD requires revising 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 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 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.
2000-05-23: This amendment adopts a new airworthiness directive (AD) that applies to all Ayres Corporation (Ayres) S2R series airplanes that are equipped with at least one main landing gear fuselage attach bolt with a grease fitting installed through the shank. This AD requires replacing the main landing gear fuselage attach bolts that are drilled with a grease fitting with undrilled (no grease access) attach bolts. This AD is the result of a report of cracks found in all four main landing gear fuselage attach bolts on one of the affected airplanes. The actions specified by this AD are intended to prevent collapse of the main landing gear caused by cracked main landing gear fuselage attach bolts, which could result in main landing gear collapse with possible wing fuel tank rupture and consequent fire
87-16-02: 87-16-02 HARTZELL: Priority letter issued July 31, 1987. Applies to Model HC-B5MP- 3C/M10876K propellers installed on Short Brothers Model SD3-60 aircraft. This priority letter AD is effective immediately upon receipt. Compliance is required, as indicated, unless already accomplished. To prevent propeller blade separation near the hub which could result in engine separation from the aircraft, accomplish the following: (a) Until compliance with paragraph (b), remove propeller from aircraft, disassemble propeller, penetrant inspect and rework, as required, the blade pilot tube bore, in accordance with Hartzell Service Bulletin No. 136D, dated May 23, 1986, in accordance with the following schedule: TIME SINCE NEW (TSN) - HOURS INSPECT/REWORK Less than or equal to 3000 Prior to exceeding 3000 hours time in service or 250 additional flights from the effective date of this priority letter AD, whichever occurs later, and thereafter at intervals not to exceed 300 flights. Greater than 3000 and have accumulated excess of 300 flights since last inspection per Service Bulletin 136D Reinspect/rework prior to accumulation of an additional in 250 flights from the effective date of this priority letter AD, and thereafter at intervals not to exceed 300 flights. Greater than 3000 and have accumulated less than or equal to 300 flights since last inspection per Service Bulletin 136D. Reinspect/rework prior to accumulation of 300 flights since last inspection or 250 additional flights from the effective date of this priority letter AD, whichever occurs later, and thereafter at intervals not to exceed 300 flights. (b) Remove from service (retire) and replace blade Model M10876K with new design blade Model M10876ASK, or Federal Aviation Administration (FAA) approved equivalent, prior to March 31, 1988. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations (FAR's) 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 priority letter AD may be approved by the Manager, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des Plaines, Illinois 60018. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Manager, Chicago Aircraft Certification Office, may adjust the compliance time specified in this priority letter AD. Documents pertinent to this priority letter AD may be obtained from Hartzell Propeller Products Division, TRW Aircraft Components Group, 350 Washington Avenue, Piqua, Ohio 45356, or may be examined at the Office of the Regional Counsel, FAA, Rules Docket No. 87- ANE-27, 12 New England Executive Park, Burlington, Massachusetts 01803. Federal Register publication to follow. This priority letter AD issued July 31, 1987, is effective immediately upon receipt.
92-06-05 R1: 92-06-05 R1 BRITISH AEROSPACE: Amendment 39-8251. Revises amendment 39-8185, AD 92- 06-05. Docket No. 91-NM-209-AD. Applicability: Model DH/BH/HS/BAe 125 series airplanes, except Model BAe 125-1000A series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the fuselage and subsequent decompression of the airplane, accomplish the following: (a) Prior to the accumulation of 4,000 landings, or within 60 days after the effective date of this AD, whichever occurs later, accomplish the following in accordance with British Aerospace Service Bulletin 53-73, Revision 2, dated May 18, 1991: (1) Perform a visual inspection of the nose landing gear (NLG) bay left and right sidewalls to detect the presence of washers or spotface under nuts. (i) If no spotface is found, perform a visual inspection to detect damage to the web caused by nuts or washers. (ii) Blend out any damage found, excluding cracking, prior to further flight. (2) Perform either a dye penetrant or eddy current inspection to detect cracks on the NLG bay left and right sidewalls. If cracks are found, repair prior to further flight, in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (b) 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. (c) 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. (d) The inspections shall be done in accordance with British Aerospace Service Bulletin 53- 73, Revision 2, dated May 18, 1991. This incorporation by reference was previously approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51 as of April 21, 1992 (57 FR 9170, March 17, 1992). Copies may be obtained from British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC. 20041-0414. 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. (e) This amendment is effective April 21, 1992.
2014-23-07: We are superseding Airworthiness Directive (AD) 2004-16-01 for certain Airbus Model A330-200 and -300 series airplanes and Model A340- 200 and -300 series airplanes. AD 2004-16-01 required repetitive inspections for cracking of the chromed area of the left and right piston rods for the main landing gear (MLG) retraction actuators, and related investigative and corrective actions if necessary. This new AD requires repetitive draining of any fluid from the retraction actuator piston rod internal volume and sealing of the vent hole; repetitive ultrasonic inspections of the upper end of the piston rods, and corrective actions if necessary; a one-time ultrasonic inspection (longitudinal and circumferential) of the full length of the piston rod, and corrective actions if necessary; and a terminating modification of the left-hand and right-hand MLG retraction actuators. This AD was prompted by reports of the piston rods for the MLG retraction actuators rupturing during flight. We areissuing this AD to prevent cracking of the piston rods for the MLG retraction actuators, which could result in rupture of a piston rod, non-damped extension of the MLG, high loads on the fully extended MLG, and consequent reduced structural integrity of the MLG.
92-09-01: 92-09-01 AEROSPATIALE: Amendment 39-8226. Docket No. 92-NM-66-AD. Applicability: Model ATR42-200 and -300 series airplanes, as listed in Aerospatiale Service Bulletin ATR42-76-0009, Revision 1, dated December 5, 1991; and Model ATR72-100 and -200 series airplanes, as listed in Aerospatiale Service Bulletin ATR72-76-1002, Revision 1, dated December 5, 1991; certificated in any category. Compliance: Required within 60 days after the effective date of this AD, unless accomplished previously. To prevent the crew's inability to increase or decrease engine power, accomplish the following: (a) Install a heat deflector on the rear upper cowl, and a thermal bridge between the teleflex controls and the air conditioning duct, in accordance with Aerospatiale Service Bulletin ATR42-76-0009, Revision 1, dated December 5, 1991; or Aerospatiale Service Bulletin ATR72- 76-1002, Revision 1, dated December 5, 1991; as applicable. (b) An alternative method of compliance oradjustment 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. (c) 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. (d) The installations shall be done in accordance with Aerospatiale Service Bulletin ATR42-76-0009, Revision 1, dated December 5, 1991; or Aerospatiale Service Bulletin ATR72- 76-1002, Revision 1, dated December 5, 1991; as applicable. These service bulletins include the following list of effective pages: Service Bulletin Page Revision Number Date 1-6, 8-12, 15-17 1 December 5, 1991 ATR42-76-0009, Revision 1 7, 13-14, 18 Original April 11, 1991 1-2, 6-10, 13-14 1 December 5, 1991 ATR72-76-1002 Revision 1 3-5, 11-12, 15-16 Original April 11, 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. 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. (e) This amendment becomes effective on May 8, 1992.
2014-23-05: We are adopting a new airworthiness directive (AD) for all Airbus Model A318 series airplanes, Model A319 series airplanes, Model A320-211, -212, -214, -231, -232, and -233 airplanes, and Model A321 series airplanes. This AD was prompted by a report of a circumferential crack at the gland retaining-ring groove of certain retraction actuators on the main landing gear (MLG). This AD requires an inspection to identify the part numbers of MLG retraction actuators and replacement of certain MLG retraction actuators. We are issuing this AD to prevent MLG retraction actuator failure that could prevent the full extension and/or down-locking of the MLG, possibly resulting in MLG collapse during landing or rollout, and consequent damage to the airplane and injury to the occupants.
2000-05-29: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -300, -400, and -500 series airplanes, that requires repetitive inspections to detect cracking of various areas of the forward pressure bulkhead, and repair, if necessary. This amendment also provides for certain optional preventive modifications, which, if accomplished, would terminate the repetitive inspections for the affected areas. This amendment is prompted by reports indicating that numerous fatigue cracks were found on critical areas of the forward pressure bulkhead. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in rapid decompression of the airplane fuselage.
2000-05-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300, A310, and A300-600 series airplanes, that requires repetitive eddy current inspections to detect cracking on the door edge frames of the fuselage bulk cargo compartment, 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 cracks in the door edge frames of the fuselage bulk cargo compartment, which could result in reduced structural integrity of the airframe.
2021-17-06: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 747-100, -100B, -100B SUD, -200B, -200C, - 200F, -300, -400, -400D, -400F, 747SR, and 747SP airplanes. This AD was prompted by reports of cracks found in the front spar shear tie and at the intercostal lug fitting at certain locations. This AD requires repetitive detailed and surface high frequency eddy current (HFEC) inspections of the front spar shear tie and intercostal lug fitting at certain locations for any cracking, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2014-23-02: We are adopting a new airworthiness directive (AD) for certain Agusta Model A109E, A109K2, A119, and AW119 MKII helicopters. This AD requires repetitively performing a magnetic particle inspection of the Gleason crown for a crack. This AD was prompted by a report of a crack that was found on a Gleason crown, which if not detected, could cause damage to or loss of the main rotor drive and subsequent loss of control of the helicopter.