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88-26-03: 88-26-03 BELL HELICOPTER TEXTRON, INC. (BHTI): Amendment 39-6058. Applies to Model 206L helicopters, S/N's 45001 through 45153 and S/N's 46601 through 46617, and to Bell Model 206L-1 helicopters, S/N's 45154 through 45840, certificated in any category, with fuel system flow switches, P/N's 206-063-635-001, 206-064-601-001, -003, -101, or -103 installed. (Airworthiness Docket No. 88-ASW-2) Compliance is required as indicated, unless already accomplished. To prevent a possible fuel system failure due to the malfunction of the fuel system flow switches which could result in an engine flameout and subsequent loss of the helicopter accomplish the following: (a) Within the next 250 hours' time in service after the effective date of this AD, remove and replace the fuel system flow switches, P/N's 206-063-635-001, 206-064-601-001, - 003, -101, or -103, whichever is installed, with fuel system flow switch retrofit kit, P/N 206-703- 004-101 and relocate the in-line fuelfilters, P/N 206-063-693-001, in accordance with Bell Helicopter Textron, Inc., Alert Service Bulletin No. 206L-88-52, dated June 10, 1988. (b) An alternate method of compliance which provides an equivalent level of safety with this AD may be used when approved by the Manager, Helicopter Certification Branch, Federal Aviation Administration, Fort Worth, Texas 76193-0170. The procedure shall be done in accordance with Bell Helicopter Textron, Inc., Alert Service Bulletin No. 206L-88-52, dated June 10, 1988. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a)(1) and 1 CFR Part 51. Copies may be obtained from Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101, Attention: Customer Support. Copies may be inspected at the Office of the Regional Counsel, FAA, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas, or at the Office of the Federal Register, 1100 L Street, NW., Room 8401, Washington, D.C. This amendment (39-6058, AD 88-26-03) becomes effective January 18, 1989.
82-07-03: 82-07-03 JANITROL AERO DIVISION (MIDLAND-ROSS CORPORATION): Amendment 39-4354. Applies to Models B1500, B2030, B3040, and B4050 combustion heaters marked as meeting the standards of FAA TSO-C20, installed in aircraft certificated in any category. COMPLIANCE: Required as indicated, unless already accomplished. To detect and prevent the failure of affected combustion heater tube assemblies, accomplish the following: a) For installed affected heaters with 450 or more heater-hours time-in-service, since last overhauled or installed new, on the effective date of this AD, comply with paragraph e) within the next fifty (50) heater-hours time-in-service or twelve (12) months from effective date of this AD, whichever occurs first, and thereafter at intervals not to exceed 100 heater-hours time-in-service or twenty-four (24) months, whichever occurs first. b) For installed affected heaters with less than 450 heater-hours time-in-service, since last overhauled or installed new, on the effective date of this AD, comply with paragraph e) before the accumulation of 500 heater-hours time-in-service since last overhauled or installed new, or twelve (12) months from effective date of this AD, whichever occurs first, and thereafter at intervals not to exceed 100 heater-hours time-in-service or twenty-four (24) months, whichever occurs first. c) For uninstalled out-of-service/overhauled heaters without a new combustion tube assembly that are installed in aircraft subsequent to the effective date of this AD, comply with paragraph e) before the accumulation of 250 heater-hours time-in-service or twelve (12) months, whichever occurs first, and thereafter at intervals not to exceed 100 heater-hours time-in-service or twenty-four (24) months, whichever occurs first. d) For uninstalled affected new or overhauled heaters with a new combustion tube assembly that are installed in aircraft subsequent to the effective date of this AD, comply with paragraph e) beforethe accumulation of 500 heater-hours time-in-service or twenty-four (24) months, whichever occurs first, and thereafter at intervals not to exceed 100 heater-hours time-in-service or twenty-four (24) months, whichever occurs first. e) Conduct 100 hour inspection of affected heaters in accordance with Janitrol's Maintenance and Overhaul Manual, Instruction P/N 24E25-1, dated October 1981. Prior to further flight, overhaul any heater that does not pass the combustion pressure decay test required by this inspection. For all affected Janitrol Aircraft Heaters installed in Cessna or Piper Aircraft, conduct the required overhaul in accordance with the appropriate Cessna or Piper Aircraft Heater Overhaul Manual or Janitrol Overhaul Manual, P/N 24E25-1, dated October 1981. f) A HEATER HOURMETER may be used to establish heater operating time. If a HEATER HOURMETER is not used, count one (1) heater hour for each two (2) flight hours for normal aircraft flight operation. g) Upon request of an operator, the Chief, Chicago Aircraft Certification Office, FAA, Central Region, may adjust the compliance time specified in paragraphs a), b), c), and d) of this AD provided such requests are made through an FAA maintenance inspector, and the request contains substantiating data to justify the request for that operator. h) An equivalent method of compliance with this AD may be used when approved by the Chief, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des Plaines, Illinois 60018; telephone (312) 694-7357. This AD supersedes AD 80-09-10. This amendment becomes effective May 6, 1982.
95-08-08: 95-08-08 BOEING : Amendment 39-9197. Docket 95-NM-46-AD.\n\n Applicability: Model 737-200 and -200C airplanes equipped with dB Partners Hush Kit installed in accordance with Supplemental Type Certificate (STC) SA5730NM, certificated in any category.\n\n NOTE 1: This AD applies to each airplane 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 airplanes 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 (c) to request approval from the 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 airplane from the applicability of this AD.\n Compliance: Required as indicated, unless accomplished previously. \n To prevent separation of the nose cowl from the engine following turbine blade failure, accomplish the following:\n (a) Within 30 days after the effective date of this AD, install fail-safe straps onto the existing attach ring, in accordance with Nordam Service Bulletin SB 71-03, dated March 17, 1995.\n (b) As of the effective date of this AD, fail-safe straps must be installed onto the existing attach ring of the nose cowl, in accordance with Nordam Service Bulletin SB 71-03, dated March 17, 1995, prior to installation of STC SA5730NM on any airplane.\n (c) 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, Seattle Aircraft Certification Office (ACO), 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, Seattle ACO.\n NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. \n (d) 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.\n (e) The installation shall be done in accordance with Nordam Service Bulletin SB 71-03, dated March 17, 1995. 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 The Nordam Group, 624 East 4th Street, Tulsa, Oklahoma 74120. 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.\n (f) This amendment becomes effective on May 2, 1995.
98-13-38: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that requires installation of a warning placard for the fire extinguisher exhaust port located in the rear baggage bay. 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 blockage of the fire extinguisher exhaust port, which could result in reduced fire protection in the rear baggage bay and consequent injury to the passengers and crewmembers.
98-13-34: This amendment adopts a new airworthiness directive (AD) that is applicable to all EMBRAER Model EMB-145 series airplanes. This action requires repetitive emergency extension (free-fall) functional tests of the nose landing gear (NLG), and lubrication of all NLG hinge points, to ensure that the NLG extends and locks down properly; 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 prevent failure of the NLG to extend and lock down properly, which could result in damage to the airplane structure, and consequent reduced controllability of the airplane upon landing.
93-20-02: 93-20-02 MCDONNELL DOUGLAS: Amendment 39-8709. Docket 92-NM-220-AD. Supersedes AD 92-02-05, Amendment 39-8141. \n\n\tApplicability: Model DC-8-61, -62, -63, and -73 series airplanes equipped with a cargo conversion modification installed in accordance with Supplemental Type Certificate (STC) SA1802SO; and Model DC-8-21, -32, -33, and -51 series airplanes equipped with a cargo conversion modification installed in accordance with STC SA421NW; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent loss of the cargo door, damage to flight control surfaces, and reduced controllability of the airplane, accomplish the following: \n\n\t(a)\tWithin 7 days after the effective date of this AD, revise the Limitations Section of the appropriate FAA-approved Airplane Flight Manual Supplement (AFMS) by replacing item 5 in the AFMS for SA1802SO, and item 6 in the AFMS for SA421NW, with the following. (This may be accomplished by inserting a copy of this AD into the AFMS.) \n\n\t"Prior to initiating the cargo door closing sequence, a flight crew member must verify that the cargo door warning light is illuminated. After the door closing sequence is complete, and visual verification has been made that the latches are closed and the lockpins are properly engaged, a flight crew member must verify that the cargo door warning light is extinguished, and then conduct a PRESS-TO-TEST of the warning light to ensure that the light is operational. Pull the cargo door circuit breakers labeled "pump" and "valve" prior to takeoff. Methods for documentation of compliance with the preceding procedures must be approved by the FAA Principal Maintenance Inspector (PMI)." \n\n\t(b)\tWithin 7 days after January 21, 1992 (the effective date of AD 92-02-05, Amendment 39-8141), and thereafter at intervals not to exceed 100 hours time-in-service, perform the following inspections: \n\n\t\t(1)\tInspect the cargo door wire bundle between the exitpoint of the cargo liner and the attachment point on the cargo door to detect crimped, frayed, or chafed wires; and inspect for damaged, loose, or missing hardware mounting components. Prior to further flight, repair any damaged wiring or hardware mounting components in accordance with FAA-approved maintenance procedures. \n\n\t\t(2)\tInspect the cargo door latch rollers in the lower sill of the cargo door opening of the airplane to ensure that all twelve rollers can be freely rotated by hand. Prior to further flight, replace any discrepant roller components found, and repair any rollers that cannot be rotated freely by hand, in accordance with FAA-approved maintenance procedures. \n\n\t(c)\tAn 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, Atlanta Aircraft Certification Office (ACO), ACE-115A, FAA, Small 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, Atlanta ACO. \n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO. \n\n\t(d)\tSpecial 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. \n\n\t(e)\tThis amendment becomes effective on November 17, 1993.
88-19-03 R1: 88-19-03 R1 BOEING: Amendment 39-6001 as revised by Amendment 39-6532. Docket No. 89-NM-156-AD.\n \n\tApplicability: Model 767 series airplanes, line numbers 001 through 175, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent a condition that could lead to depressurization of the airplane, accomplish the following: \n\n\tA.\tPrior to the accumulation of 6,000 flight cycles or within the next 1,000 flight cycles after September 26, 1988, (effective date of Amendment 39-6001), whichever occurs later, unless accomplished within the last 5,000 flight cycles, and thereafter at intervals not to exceed 6,000 flight cycles, perform a detailed visual inspection of the aft side of the entire body station 1582 pressure bulkhead for damage (as defined in the Structural Repair Manual) and cracking, in accordance with Boeing Service Bulletin 767-53-0026, dated November 19, 1987, or Revision 1, dated March 16, 1989. \n\n\tB.\tPriorto the accumulation of 25,000 flight cycles, and thereafter at intervals not to exceed 6,000 flight cycles, perform an eddy current inspection of the body station 1582 pressure bulkhead, in accordance with paragraph C. of the Accomplishment Instructions of Boeing Service Bulletin 767-53-0026, Revision 1, dated March 16, 1989. \n\n\tC.\tRepair all damage and cracking prior to further flight in accordance with NOTE 4 in the Accomplishment Instructions of Boeing Service Bulletin 767-53-0026, Revision 1, dated March 16, 1989. \n\n\tD.\tFor the purpose of complying with this AD, the number of flight cycles may be determined to equal the number of pressurization cycles where the cabin pressure differential was equal to or greater than 2.0 PSI. \n\n\tE.\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 will either concur or comment, and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tF.\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 FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis AD revises AD 88-19-03, Amendment 39-6001. \n\tThis amendment (39-6532, AD 88-19-03 R1) becomes effective on April 13, 1990.
2019-21-07: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by a report of cracked external lugs of the aluminum cargo door latch fittings in the lower part of the forward and aft cargo doors. This AD requires repetitive detailed inspections of the external lugs of the aluminum cargo door latch fittings for cracks, and corrective actions if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. Accomplishing the installation of new aluminum cargo door latch fittings constitutes terminating action for the repetitive detailed inspections. The FAA is issuing this AD to address the unsafe condition on these products.
82-27-02 R1: 82-27-02 R1 McCAULEY ACCESSORY DIVISION: Amendment 39-4521 as amended by Amendment 39-4564. Applies to the following McCauley Accessory Division C200, C300, and C400 series constant speed propellers with blade serial numbers as identified below that are installed on, but not limited to, the aircraft listed below: AIRCRAFT PROPELLER MODEL/BLADE MODEL Cessna R172K 2A34C203/90DCA-10 or 90DCA-14 Cessna 172RG B2D34C220/80VHA-3.5 Cessna 177RG B2D34C207/78TCA-0 Cessna 180G-J 2A34C201/90DA-8 Cessna 180G-J 2A34C203/90DCA-2 or 90DCA-8 Cessna 180K C2A34C204/90DCB-8 Cessna 182M-P 2A34C201/90DA-8 Cessna 182M-P 2A34C203/90DCA-8 Cessna 182Q C2A34C204/90DCB-8 Cessna R182 (pre-1980) B2D34C214/90DHB-8 Cessna R182 (1980-on) B2D34C218/90DHB-8 Cessna TR182 (pre-1980) B2D34C217/90DHB-8 Cessna TR182 (1980-on) B2D34C219/90DHB-8 Cessna T182 B2D34C219/90DHB-8 Cessna A185F D3A34C403/80VA-0 Cessna T188C D3A34C402/90DFA-10 Cessna TU206G D3A34C402/90DFA-10 Cessna U206G D3A34C404/80VA-0 Cessna 207A D3A34C404/80VA-0 Cessna T207A D3A34C401/90DFA-10 Cessna P210N:T210M,N D3A34C402/90DFA-10 Cessna 210N D3A34C404/80VA-0 Cessna T337G,H:P337H D2AF34C308/90DEA-12 Cessna 337G,H D2AF34C310/90DEA-12 Mooney M20J (201) B2D34C214/90DHB-16E Mooney M20K (231) 2A34C216/90DHB-16E Reims FR172K 2A34C203/90DCA-14 Reims F177RG B2D34C207/78TCA-0 Reims F182P 2A34C201/90DA-8 Reims F182P 2A34C203/90DCA-8 Reims F182Q C2A34C204/90DCB-8 Reims FR182 (pre-1980) B2D34C214/90DHB-8 Reims FR182 (1980-on) B2D34C218/90DHB-8 Reims F337G D2AF34C310/90DEA-12 Reims FT337GP D2AF34C308/90DEA-12 APPLICABLE BLADE SERIAL NUMBERS SERIAL NUMBER BLADE TYPE B117210 thru B117249 90DEA-12 and 90DA-8 B117290 thru B117329 90DCB-8 B117410 thru B117529 90DHB-16E and 78TCA-0 B117610 thru B117649 90DCB-8 B117730 thru B117769 90DHB-8 and 78TCA-0 B117890 thru B117969 90DCB-8 B118090 thru B118169 90DHB-8 B118254 thru B118369 90DHB-8 B119170 thru B119249 90DHB-16E and 90DHB-8 B119290 thru B119449 90DCA-2, 90DCA-8, 90DCA-10, and 90DCA- 14 B119450 thru B119489 90DA-8 B119490 thru B119529 90DEA-12 B120345 thru B120364 90DCA-14 B120485 thru B120524 90DEA-12 B120667 thru B120686 90DCA-10 B120687 thru B120929 90DHB-16E B121063 thru B121262 90DCB-8 and 90DHB-16E B121450 thru B121489 90DCB-8 B121690 thru B121969 90DHB-8 B121970 thru B122049 90DCA-14 B122050 thru B122089 90DCA-8 B122090 thru B122129 90DHB-16E B126956 thru B126979 90DFA-10 BC 551 thru BC638 80VA-0 BC 719 thru BC750 80VA-0 BC752 thru BC790 80VA-0 BC815 thru BC839 80VA-0 BC893 thru BC908 80VA-0 BC910 thru BC919 80VA-0 BC951 thru BC974 80VA-0 BC991 thru BC1030 80VA-0 BK321 thru BK362 80VA-0 BK371 thru BK400 80VA-0 BK441 thru BK460 80VA-0 BK481 thru BK560 80VA-0 BI001 thru BI200 80VHA-3.5 BJ081 thru BJ160 80VA-0 BJ181 thru BJ200 80VA-0 BJ253 thru BJ260 80VA-0 BJ262 thru BJ280 80VA-0 BJ282 thru BJ320 80VA-0 NOTE: McCauley Accessory Division Service Bulletin 146 provides additional background information for identifying propeller applicability. Compliance required, within the next 10 hours time in service after the effective date of this AD, unless already accomplished. To prevent possible propeller blade shank failure, accomplish the following: (a) Dye penetrant inspect the blade shank area for cracks or forging "folds" in accordance with McCauley Accessory Division Service Bulletin SB146 dated December 3, 1982, or FAA approved equivalent. Extreme caution must be exercised when removing paint and blade anodize to prevent corrosive liquids from entering the propeller hub. If evidence of cracks or forging "folds" is found replace the blade with a serviceable blade before further flight. (b) A special flight permit may be issued in accordance with Federal Aviation Regulations (FARs) 21.197 and 21.199 to operate the aircraft to a base where this AD can be accomplished. (c) Upon request of the operator, 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. Amendment 39-4521 became effective December 30, 1982. This Amendment 39-4564 becomes effective February 22, 1983.
88-24-09: 88-24-09 FOKKER: Amendment 39-6064. Applies to Model F-27 series airplanes Serial Numbers 10102 to 10692, inclusive, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent jamming of the main landing gear, accomplish the following: A. Within 90 days after the effective date of this AD, perform a one-time inspection of the main landing gear torque links, and repair, if necessary, in accordance with Fokker Service Bulletin F27/32-157, dated December 18, 1987. NOTE: Fokker Service Bulletin F27/32-157, dated December 18, 1987, references Dowty-Rotol Service Bulletins 32-49SW, 32-82S, and 32-161B for procedures for the inspection and repair. B. 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 throughan FAA Principal Maintenance Inspector (PMI), who may add any comments 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 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, 39-6064, becomes effective December 21, 1988.