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98-26-09: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC 9-10, -20, -30, -40, and -50 series airplanes, and C-9 (military) airplanes, that requires a one-time visual inspection to determine if the doorstops and corners of the doorjamb of the forward passenger door have been modified, various follow-on repetitive inspections, and modification, if necessary. This amendment is prompted by reports of fatigue cracks found in the fuselage skin and doubler at the corners and doorstops of the doorjamb of the forward passenger door. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane.
98-26-05: This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace (Operations) Limited (British Aerospace) Model B.121 Series 1, 2, and 3 airplanes. This AD requires repetitively inspecting (using visual methods) the internal and external surfaces of the brake torque tube assemblies in the cockpit area for cracks. This AD also requires obtaining and incorporating repair procedures for any brake torque tube assembly found cracked. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to detect and correct cracks in the brake torque tube assemblies, which could result in reduced brake efficiency with possible reduced and/or loss of airplane control.
2013-14-01: We are adopting a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. Model PC-6/B2-H4 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as faulty rivets installed in the airframes during production could reduce the structural integrity of the airplane. We are issuing this AD to require actions to address the unsafe condition on these products.
81-21-03: 81-21-03 BRITISH AEROSPACE CORPORATION: Amendment 39-4229. Applies to all operators of DH-114 Heron Series 1B and all series 2 airplanes which have been modified in accordance with Modification 154 or 469. To ensure wing leading edge access doors remain properly secured, accomplish the following unless already accomplished: 1. Within 350 hours time in service after the effective date of this AD, modify the wing leading edge access doors in accordance with British Aerospace Corp. Manufacturer's Technical News Sheet W.1 1, Issue 2, and Modification No. Heron 1171 (Amendment No. 1 incorporated) dated October 17, 1961, or a later FAA approved revision. 2. Alternate means of compliance may be used which provide an equivalent level of safety when approved by the Chief, Seattle Area Aircraft Certification Office, FAA, Northwest Region. 3. Airplanes may be flown to a maintenance base for repairs or replacement in accordance with FAR 21.197. 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 to the addresses listed above. These documents may also be examined at FAA, Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment becomes effective October 18, 1981.
51-04-02: 51-04-02 WARNER: Applies to All Engines Except Those With the Letter "A" Stamped After the Serial Number on the Engine Nameplate. The Letter "A" Indicates That the Modifications Hereinafter Discussed Have Already Been Accomplished. Compliance required as indicated. As a precautionary measure to preclude serious flight hazards resulting from failure of the 5/16-inch cylinder holddown studs P/N S506, the following inspections or replacements should be accomplished. A. Compliance required as soon as possible but not later than April 1, 1951 and at each 100 hours of operation thereafter. 1. Check the cylinder holddown nuts to determine that they are tightened to a torque of 180 inch- pounds desired to a 200 inch-pounds maximum. (a) If one or more of the studs is found to be broken, replace all of the studs for the particular cylinder. (b) Loose cylinder holddown nuts are a good indication that the stud may have stretched to the extent that fatigue failure may soon result. If one or more of the nuts is found loose, it is recommended that all of the studs in the cylinder be replaced. (c) When installing a cylinder with oil on the stud threads, tighten nuts to 200 inch-pounds desired to 225 inch-pounds maximum. (Warner Service Letter No. A-15 discusses procedures for inspecting and replacing 5/16-inch studs and nuts.) B. Compliance not required, but will eliminate foregoing mandatory inspections. 1. Replace cylinder stud P/N S506 and nut N-511 with 3/8-inch stud S-911 and nut N-910. 2. Replace gasket between cylinder barrel and crankcase with an "O" type ring. 3. Stamp letter "A" after serial number on engine nameplate when this modification has been completed. (Warner Service Letter No. A-17 explains the details connected with the replacement of these parts.) The Warner Aircraft Co., P. O. Box 229, Niles, Mich., which purchased the assets of the Warner Division of the Clinton Machine Co., Detroit, Mich., have a large supply of replacement part stocks that will be held in their inventory for an indefinite period. Warner Service Letter No. A-17 should be consulted before ordering these replacement parts. If either Letter A-17 or Letter A-15 is not available, copies may be obtained from the Warner Aircraft Co., Box 229, Niles, Mich.
2010-17-11R1: We are revising an existing airworthiness directive (AD) that applies to all Dowty Propellers R408/6-123-F/17 model propellers. That AD currently requires initial applications of sealant between the bus bar assembly and the backplate assembly of certain line-replaceable units, and repetitive applications of sealant on all R408/6-123-F/17 model propellers. This new AD requires the same actions and allows the use of an equivalent sealant as prescribed in revised service information. This AD was prompted by the need to add an optional terminating action to the applications of sealant. We are issuing this AD to prevent an in-flight double generator failure, which could result in reduced control of the airplane.
76-06-02: 76-06-02 BELL: Amendment 39-2554. Applies to Model 205A-1 helicopters, Serial Numbers 30001 through 30196, certified in all categories. Compliance required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. (a) Gain access to the engine fire extinguisher discharge cartridge, P/N 13083-45, mounted on the fire extinguisher agent container, as necessary, to determine if the legend "1272" is stamped on one of the hexagonal flats on the cartridge body. If this legend is found, proceed as follows: (1) Disconnect the circuit breaker for the fire extinguisher system circuit. (2) Disconnect aircraft wiring from the fire extinguisher discharge wiring. (3) Using a short length of wire (safety wire is suitable), connect the actuation pin to the ground stud. (4) Identify the 1 1/4" hexagonal nut into which the cartridge is threaded. Use an appropriate wrench to prevent this nut from turning and remove the cartridge from the nut. Leave the wire specified in item (3) attached on the cartridge terminals to prevent inadvertent detonation by static electricity. (5) Attach a connecting wire as described in step (3) above to a suitable replacement cartridge and install the cartridge into the 1 1/4" hexagonal nut from which the defective cartridge was removed. (6) Tighten the new cartridge to 90-100 inch pounds and lockwire to the 1 1/4" hexagonal nut. (7) Remove the pin-to-stud connecting wire and reconnect aircraft wiring. Close the circuit breaker. (b) If initial inspection of the cartridge reveals that the cartridge is not from the lot marked "1272," no further action is required to comply with this AD. Completion of Steps 1, 2, and 4 of Bell Helicopter Service Bulletin No. 205-75-7, dated November 5, 1975, or later approved revision, will satisfy the requirements of this AD. Equivalent methods of compliance with this airworthiness directive must be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76106. This amendment becomes effective April 26, 1976.
98-25-13: This amendment adopts a new airworthiness directive (AD) that is applicable to McCauley Propeller Systems (formerly McCauley Accessory Division, The Cessna Aircraft Company) Models 2A36C23/84B-0 and 2A36C82/84B-2 propellers. This action supersedes priority letter AD 89-26-08 that currently requires penetrant inspections for cracks in the propeller blade threaded retention area, and modifying the propeller hub to a red dye filled configuration. This action adds an explanatory note to better define the AD applicability and makes minor adjustments to compliance section language to reflect current AD practice. This amendment is prompted by reports of confusion from operators as to if the AD is applicable to their particular model propeller. The actions specified by this AD are intended to prevent possible cracks in the propeller blade threaded retention area from progressing to blade separation, which can result in loss of aircraft control.
75-14-01: 75-14-01 MESSERSCHMITT BOELKOW BLOHM Gmbh.: Amendment 39-2245 as amended by Amendment 39-2277. Applies to Messerschmitt Boelkow Blohm (MBB) Model BO-105 helicopters certificated in all categories. Compliance is required as indicated. To prevent failure in service accomplish the following: (a) Before further flight, remove flexible hose assemblies having any of the following MBB or ESPA part numbers that have blue fittings marked MS24590. Replace with flexible hose assemblies of the same MBB or ESPA part number that have silver or metal colored fittings marked 12 LN 29813. MBB PART NUMBER ESPA PART NUMBER 105 - 61795 40848 - 1290 105 - 61796 40561 - 1185 105 - 61797 40561 - 820 105 - 61798 40560 - 440 105 - 62163 40558 - 415 105 - 62165 40558 - 500 105 - 61793 40561 - 355 105 - 62161 40561 - 960 105 - 62162 40561 - 1010 105 - 62169 40848 - 820 105 - 62168 40848 - 775 105 - 61792 40562 -330 -0 105 - 61791 40562 - 1125 105 - 62166 40849 - 810 105 - 62167 40849 - 865 105 - 61799 40560 - 600 105 - 61343 40848 - 250 105 - 61344 40848 - 890 105 - 90897 40556 - 350 (Replaces 105-90898) (b) Before further flight, except that the aircraft may be flown in accordance with FAR Sec.21.197 and 21.199 to a base where the work can be performed, remove flexible hose assemblies, MBB part numbers 105-61797, -61798, and -61799 that have the marking "HN-10" behind the part/drawing number or that have "ESPA HN-10" marked on the hose surface. Replace with serviceable assemblies of the same part number that do not carry the designation "HN-10" or "ESPA HN-10". (c) Before further flight, except that the aircraft may be flown in accordance with FAR Sec. 21.197 and 21.199 to a base where the work can be performed, inspect flexible hose assemblies having the following part/drawing numbers that carry the designation "HN-10" or "ESPA HN-10",for cracks in the area where the hose extrudes from the fitting. Remove and replace in accordance with the following schedule: 105 - 61795 105 - 62162 (or D133 - 1580) 105 - 61793 105 - 62169 (or D133 - 1585) 105 - 61343 (or D133 - 1577) 105 - 61344 (or D133 - 1578) (1) If cracks are found, or prior to reaching the hose assembly service life limit if no cracks are found, remove the assembly and replace with a serviceable assembly of the same part number that does not carry designation "HN-10" or "ESPA HN-10". (2) If no cracks are found, the hose assembly may be continued in service until reaching the service life limit of 100 hours total time in service provided the assembly is reinspected at intervals not to exceed 25 hours time in service or two calendar weeks, whichever occurs first. (Messerschmitt Boelkow Blohm BO-105 Alert Bulletins 10, 11, and 12 and Service Bulletin 60-14 cover this same subject.) Amendment 39-2245 was effective upon publication in the Federal Register. This Amendment is effective upon publication in the Federal Register as to all persons except those persons, to whom it was made immediately effective by the telegram dated June 25, 1975, which contained this amendment.
90-08-03: 90-08-03 FOKKER: Amendment 39-6559. Docket No. 89-NM-238-AD. Applicability: Model F-27 series airplanes, 10102 through 10684, 10686, 10687, and 10689 through 10692, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural capability of the wing due to fatigue cracks, accomplish the following: A. Perform a one-time X-ray inspection of the top skin Stringers 5 and 6 at Wing Stations 11260, 11860, 12660, and 13460, in accordance with Fokker Service Bulletin F27/57-65, dated October 4, 1989; or Revision 1, dated December 1, 1989, following the schedule below: 1. For airplanes that have accumulated less than 40,000 landings as of the effective date of this AD, inspect prior to the accumulation of 30,000 landings or within 180 days after the effective date of this AD, whichever occurs later. 2. For airplanes that have accumulated 40,000 landings or more but less than 50,000 landings asof the effective date of this AD, inspect within 90 days after the effective date of this AD. 3. For airplanes that have accumulated 50,000 landings or more as of the effective date of this AD, inspect within 30 days after the effective date of this AD. B. If cracks are found, repair prior to further flight, in accordance with Part 2 of the Accomplishment Instructions of Fokker Service Bulletin F27/57-65, dated October 4, 1989; or Revision 1, dated December 1, 1989. 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 will either concur or comment 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 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 Fokker Aircraft USA, Inc., 1199 N. Fairfax Street, Alexandria, Virginia 22314. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6559, AD 90-08-03) becomes effective on May 4, 1990.