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2016-06-10: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by a report of fuel leaking onto the hot exhaust portion of an engine as a result of an unintended leak path from the leading edge through the pylon. This AD requires installing new seal dams in the inboard and outboard corners of the aft pylon frame on the left and right engines, including an inspection for damage of the outboard blade seal and applicable corrective actions. We are issuing this AD to prevent fuel leaking from an unintended drain path from the leading edge through either the left or right pylon and onto the hot engine parts or brakes, which could lead to a major ground fire.
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2016-06-06: We are adopting a new airworthiness directive (AD) for certain Quest Aircraft Design, LLC Model KODIAK 100 airplanes. This AD was prompted by a report of limited control yoke movement of the elevator control system due to cushion edging jammed in the elevator control anti-rotation guide slot. This AD requires repetitively inspecting the elevator control system cushion edging for proper condition; replacing the cushion edging; and at a specified time terminating the repetitive inspections by installing wear pads on the elevator bearing assemblies. We are issuing this AD to correct the unsafe condition on these products.
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2000-26-10: This amendment adopts a new airworthiness directive (AD), applicable to all BAe Systems (Operations) Limited Model ATP airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This amendment is prompted by issuance of a revision to the airworthiness limitations of the British Aerospace ATP Aircraft Maintenance Manual, which specifies new inspections and compliance times for inspection and replacement action. The actions specified by this AD are intended to ensure that fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
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53-17-01: 53-17-01 MOONEY: Applies to All Model M-18 Series Aircraft.
Compliance required by October 15, 1953.
To prevent possible fouling of controls and the control stick by foreign objects install canvas boot P/N 22-7 around control stick and secure to floor boards. These boots are available from Mooney Aircraft, Inc., Box 72, Kerrville, Texas.
(Mooney Service Bulletin No. 11 covers this same subject.)
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2016-06-04: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. This AD was prompted by reports of cracking at certain fastener locations in the window corners of the window belt area. This AD requires repetitive high frequency eddy current (HFEC) inspections for fatigue cracking in certain fastener locations in the window corners of the window belt area, and related investigative and corrective actions if necessary. This AD also provides an optional preventive modification that terminates the inspections at the modified location. We are issuing this AD to detect and correct fatigue cracking around fastener locations that could cause multiple window corner skin cracks, which could result in rapid decompression and loss of structural integrity of the airplane.
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2016-05-13: We are adopting a new airworthiness directive (AD) for certain Pratt & Whitney Canada Corp. (P&WC) PT6A-60AG, -65AG, -67AF, and -67AG turboprop engines. This AD requires removing Woodward fuel control units (FCUs) and installing an FCU that is eligible for installation. This AD was prompted by incidents of corrosion and perforation of the two-ply Cu-Be bellows in Woodward FCUs. We are issuing this AD to prevent failure of the Woodward FCU and engine, in-flight shutdown, and loss of control of the airplane.
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2000-26-08: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace (Jetstream) Model 4101 airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This amendment is prompted by issuance of a revision to the airworthiness limitations of the British Aerospace J41 Aircraft Maintenance Manual. The actions specified by this AD are intended to ensure that fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
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78-06-02: 78-06-02 MCCAULEY PROPELLERS: Amendment 39-3159 as amended by Amendment 39-3233. Applies to the following three bladed full feathering constant speed Model 3FF32C501 propellers installed on but not limited to the Cessna Model 421C and 404 aircraft:
Affected Propeller Serial Numbers
769303
769304
769571
769572
769573
769574
769575
769576
769577
769578
769579
769580
769581
769582
769583
769584
769585
769586
769587
769588
769589
769590
770176
770177
770178
770179
770601
770602
770603
770604
770605
770606
770607
770643
770644
770645
770646
770647
770648
770649
770650
770651
770652
770653
770654
771239
771291
771318
771319
771320
771321
771322
771323
771324
771325
771326
771327
771328
771329
771330
771331
771332
771333
771334
771335
771491
771492
771493
771495
771496
771497
771498
771499
771500
771534
771535
771536
771537
771538
771539
771540
771734
771735
771736
771737
771738
771739
771740
771741
771742
771743
771744
771745
771746
771747
771748
771839
771840
771841
771843
771848
772212
772213
772335
772336
772337
772338
772339
772340
772341
772342
772343
772344
772345
772346
772347
772348
772349
772396
772397
772398
772399
772400
772401
772429
772430
772432
772433
772434
772435
772436
772437
772438
772439
772440
772952
772953
772958
772959
772960
772961
772994
772995
772996
772997
772998
772999
773000
773047
773048
773049
773050
773051
773052
773053
773054
773055
773056
773057
773058
773059
773060
773061
773062
773066
773184
773185
773186
773187
773188
773189
773190
773191
773348
773349
773350
773351
773352
773353
773356
773358
773359
773360
773361
773573
773574
773575
773896
773897
773898
773899
773903
773966
773969
773970
773971
773973
773974
774113
774116
774122
774124
774175
774178
774180
774181
NOTE: Serialnumbers are stamped on the side of the propeller hub. These propellers are equipped with Model 90UMB-0 blades.
Compliance required before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a Federal Aviation Administration Certificate Propeller Repair Station.
To prevent possible blade pitch control failures, accomplish the following:
(a) Replace blade actuating pin screws, P/N A-1635-104 (cadmium plated), with new screws, P/N A-1635-108 (black oxide) in accordance with McCauley Service Bulletin No. 131 dated January 20, 1978, and Service Manual No. 751201 or later Federal Aviation Administration approved revisions.
(b) Replacement of the above parts must be accomplished by a Federal Aviation Administration Certificated Propeller Repair Station, since it is considered a major repair.
(c) When the affected propellers are approved for return to service, compliance with this airworthiness directive shall be noted in the Aircraft's Records.
The manufacturer's specifications and procedures identified in this directive are incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by the directive who have not already received these documents from the manufacturer, may obtain copies upon request to McCauley Accessory Division, Cessna Aircraft Company, Box 7, Roosevelt Station, Dayton, Ohio 45417. These documents may also be examined at the Great Lakes Regional Office, 2300 East Devon Avenue, Des Plaines, Illinois 60018, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this airworthiness directive which includes incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and the Great Lakes Region.
Amendment 39-3101 became effective March 22, 1978.
This amendment 39-3233 becomes effective on June 7, 1978.
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2000-26-15: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires deactivation of the map light assemblies; or modification and reidentification of the insulation blankets adjacent to certain map light assemblies, if applicable, a general visual inspection to detect damage of the Captain, First Officer, and Right Observer map light assemblies, and follow-on actions. This amendment is prompted by the FAA's determination that certain airplanes equipped with reading light assemblies in the crew rest area are subject to the identified unsafe condition. For certain airplanes, this amendment requires deactivation of the reading light assemblies, or an inspection to detect damage of the reading light assemblies, and follow-on or corrective actions, as applicable. The actions specified in this AD are intended to detect any broken light bulb housing, which could expose the power contactor. An exposed power contactor could cause the Captain, First Officer, or Right Observer map light or reading light in the crew rest area to short or overheat, which could result in smoke or fire in the cockpit.
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2000-25-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires inspections to detect cracking of the front spar web of the wing, and corrective action, if necessary. The actions specified by this AD are necessary to detect and correct fatigue cracking of the front spar web, which could result in fuel leaking onto an engine and a consequent fire. This action is intended to address the identified unsafe condition.
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