Results
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.
65-13-03: 65-13-03 FAIRCHILD: Amdt. 39-85 Part 39 Federal Register June 18, 1965. Applies to Model F-27 Aircraft Serial Numbers 1 through 95. Compliance required within the next 50 hours' time in service after the effective date of this AD unless already accomplished. To prevent further malfunctions of the actuator shaft to flap gear box connecting shaft universal joints resulting in an asymmetric flap condition, accomplish the following: Modify the actuator shaft to flap gear box connecting shaft universal joints in accordance with Fairchild Service Bulletin No. 27-35, dated June 15, 1962, or later FAA-approved revision, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This directive effective July 18, 1965.
91-05-03: 91-05-03 DORNIER: Amendment 39-6902. Docket No. 90-CE-49-AD. Applicability: Models Do228-100, Do228-101, Do228-200, Do228-201, Do228-202, and Do228-212 airplanes (serial numbers as indicated in the body of the AD), certificated in any category. Compliance: Required within the next 300 hours time-in-service after the effective date of this AD, unless already accomplished. To assure the electrical bonding integrity of the affected airplanes, accomplish the following: (a) For serial numbers (S/N) 7000 through 7168 and S/N 8000 through 8190 airplanes, replace the 4 mm2 cross-sectional area bonding straps between the horizontal stabilizer and the elevator with 6 mm2 cross-sectional area bonding straps in accordance with the instructions in Dornier Service Bulletin (SB) No. SB-228-106, Revision 1, dated December 11, 1989. (b) For S/N 7000 through 7168, S/N 8000 through 8175, and S/N 8177 airplanes, visually inspect the wing front spar area around electrical connectors 56VP, 57VP, 58VP and 59VP (electrical connectors 23QXa, 24QXa if option IK04 is installed) for corrosion in accordance with the instructions in Dornier SB No. SB-228-152, Revision 1, dated February 19, 1990. If corrosion is found, prior to further flight, remove the corrosion and treat the affected area in accordance with the instructions in Dornier SB No. SB-228-152, "Accomplishment Instruction" paragraph 2.2. (c) For S/N 7000 through 7168 and S/N 8000 through 8179 airplanes, install an additional grounding strap between the wing rear spar and the fuselage in accordance with the instructions in Dornier SB No. SB-228-162, dated February 19, 1990. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished. (e) An alternate method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager,Brussels Aircraft Certification Staff, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. (f) All persons affected by this directive may obtain copies of the documents referred to herein upon request to Dornier Luftfahrt GmbH, Product Support, P.O. Box 3, D-8031 Wessling, Federal Republic of Germany; Telephone (498153)-300; Facsimile (498153)-30.29.85; or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-6902, AD 91-05-03) becomes effective on March 25, 1991.
80-07-03: 80-07-03 CESSNA: Amendment 39-3723. Applies to the following Model R172K airplanes certificated in all categories: (Serial Numbers R1722000 through R1723204, R1723206 through R1723211, R1723213, R1723214, R1723216 through R1723220, R1723222 through R1723226, R1723228 through R1723238, R1723240 through R1723246, R1723248 through R1723258, R1723260 through R1723272, R1723274 through R1723312, R1723314, R1723316 through R1723319, R1723321 through R1723329, R1723331 through R1723351, R1723353 through R1723362 airplanes). COMPLIANCE: Required as indicated unless already accomplished. To preclude failure of the engine oil pressure pump drive shaft and resulting oil pressure loss caused by an improperly installed tachometer shaft connector, within the next 10 hours' time- in-service after the effective date of this AD, accomplish the following in accordance with the applicable Cessna Service Manual: A) Remove Cessna P/N 0550297-1 tachometer drive adapter assembly from the engine accessory case. B) Using a five-eighths inch crow foot wrench, measure the breakaway torque of Cessna P/N 0550296-1 tachometer drive connector. NOTE: Refer to Advisory Circular AC65-9A, Airframe & Powerplant Mechanics General Handbook, or Torque Wrench Manufacturers Instructions for formula for use of torque wrench with extensions. C) If the breakaway torque is at least 200 inch-pounds and not over 350 inch- pounds, retorque the Cessna P/N 0550296-1 tachometer drive connector to 280 to 300 inch- pounds. Reinstall the tachometer drive adapter assembly and make the prescribed entry in the aircraft maintenance record indicating compliance with this AD. D) If the breakaway torque is less than 200 inch-pounds or greater than 350 inch- pounds, prior to further flight, accomplish either of the following: 1. Replace the Teledyne Continental Motors P/N 634010 Oil Pump Drive Gear and P/N MS35756-1 Woodruff Key with a new Oil Pump Drive Gear and Woodruff Key of the same part number. (Refer to Teledyne Continental Motors Overhaul Manual for I0-360 Series Aircraft Engines for procedures.) 2. Perform a magnetic particle inspection of the Teledyne Continental Motors P/N 634010 Oil Pump Drive Gear in accordance with Section VI of the Teledyne Continental Motors Overhaul Manual for I0-360 Series Aircraft Engines. Give particular attention to the Woodruff Key slot and threaded area. If the oil pump drive gear is found cracked, replace with a new part of the same part number. Whether the oil pump drive gear is cracked or not, replace the P/N MS35756-1 Woodruff Key with a new part of the same part number. (Refer to Teledyne Continental Motors Overhaul Manual for I0-360 Series Aircraft Engines for procedures.) E) Install the Cessna P/N 0550296-1 tachometer drive connector and torque to 280 to 300 inch-pounds. Reinstall the tachometer drive adapter assembly and make the prescribed entry in the aircraft maintenance record indicatingcompliance with this AD. F) Airplanes may be flown in accordance with FAR 21.197 to a location where the maintenance required by this AD may be performed. G) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing District Office, Federal Aviation Admin., Rm 238, Terminal Bldg. No. 2299, Mid-Continent Airport, Wichita, KS 67209. This amendment becomes effective on March 31, 1980, to all persons except those to whom it has already been made effective by an airmail letter from the FAA dated March 13, 1980.
2006-01-11: The FAA adopts a new airworthiness directive (AD) for all The Cessna Aircraft Company (Cessna) Models 208 and 208B airplanes. This AD requires you to install the pilot assist handle (part number (P/N) SK208-146-2) (or FAA-approved equivalent part number) and deicing boots on the cargo pod and landing gear fairings (part number (P/N) AK208-6C) (or FAA-approved equivalent part number); and make changes to the Pilot's Operating Handbook (POH) and FAA-approved Airplane Flight Manual (AFM). This AD results from reports of several accidents involving the affected airplanes during operations in flight and in ground icing conditions. We are issuing this AD to provide a safe method to detect ice, snow, frost, or slush adhering to the upper wing (a critical surface) prior to takeoff; and to reduce drag in-flight by shedding ice on the cargo pod and landing gear fairings. Ice adhering to the upper wing surface, cargo pod, or landing gear fairings could result in a reduction in airplane performance with the consequences that the airplane cannot perform a safe takeoff or climb.
85-14-05: 85-14-05 SHORT BROTHERS LTD: Amendment 39-5088. Applies to Model SD3-30 airplanes as listed in Short Brothers Service Bulletin SD3-25-37, dated June 1984, certificated in any category. Compliance is required within 90 days after the effective date of this AD, unless previously accomplished. To assure proper operation of the crew seat harness, accomplish the following: A. Install the improved crew seat harness torsion spring assembly in accordance with Short Brothers Ltd. Service Bulletin SD3-25-37, dated June 1984. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. 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 inspections and/or modifications required by this AD. This amendment becomes effective August 12, 1985.