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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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2022-24-06: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-710A1-10, BR700-710A2-20, and BR700-710C4-11 model turbofan engines. This AD was prompted by reports of cracks on certain low-pressure compressor (LPC) rotor (fan) disks. This AD requires initial and repetitive visual inspections of certain LPC rotor fan disks and, depending on the results of the inspections, replacement of any LPC rotor fan disk with cracks detected. This AD also allows modification of the engine in accordance with RRD service information as a terminating action to these inspections, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
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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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93-09-03: 93-09-03 DASSAULT AVIATION: Amendment 39-8570. Docket 92-NM-242-AD.
Applicability: Model Mystere-Falcon 900 series airplanes; serial numbers 1 through 9, inclusive; and 11 through 20, inclusive; certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To prevent reduced structural integrity of the windshield support structure and potential loss of the windshield, accomplish the following:
(a) For airplane serial number 1: Prior to the accumulation of 3,750 total landings, or within 6 months after the effective date of this AD, whichever occurs later, modify the windshield support structure-to-aft window frame attachment at frame 4 on the right-hand and left-hand sides, in accordance with Dassault Aviation F900-91 Service Bulletin F900-53-12 and Appendix 1 to that service bulletin, both dated July 8, 1992.
(b) For airplanes having serial numbers 2 through 9, inclusive, and 11 through 20, inclusive: Modify the windshield support structure-to-aft window frame attachment at frame 4 on the right-hand and left-hand sides, in accordance with Dassault Aviation F900-91 Service Bulletin F900-53-12 and Appendix 1 to that service bulletin, both dated July 8, 1992; and at the later of the times specified in paragraphs (b)(1) and (b)(2) of this AD.
(1) Prior to the accumulation of 3,750 total landings, or within 6 years since date of manufacture, whichever occurs first.
(2) Within 6 months after the effective date of this AD.
(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, Standardization Branch, ANM-113, 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, Standardization Branch, ANM-113.
NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113.
(d) 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.
(e) The modification shall be done in accordance with Dassault Aviation F900-91 Service Bulletin F900-53-12, dated July 8, 1992 and Appendix 1 to that service bulletin F900-53-12, both dated July 8, 1992. (NOTE: Appendix 1 contains pages 101 through 106.) 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 Falcon Jet Corporation, Customer Support Department, Teterboro Airport, Teterboro, New Jersey 07608. 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.
(f) This amendment becomes effective on June 9, 1993.
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2000-25-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that requires repetitive inspections to detect fatigue cracking of the longeron splice fittings at stringer 11 on the left and right sides at body station 2598, and various follow-on actions. The actions specified by this AD are necessary to detect and correct fatigue cracking of the longeron splice fittings and subsequent damage to adjacent structure. Such damage could result in the inability of the structure to carry horizontal stabilizer flight loads, and consequent reduced controllability of the horizontal stabilizer. This action is intended to address the identified unsafe condition
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80-12-09: 80-12-09 GOVERNMENT AIRCRAFT FACTORIES (GAF): Amendment 39-3796. Applies to Models N22B (Serial Nos. N22B-5 and up) and N24A (Serial Nos. N24A-42 and up), certificated in all categories.
Compliance required as indicated. To prevent possible failure of rudder trim tab control, accomplish the following:
(a) Within the next 25 hours time in service after the effective date of the AD, unless already accomplished, visually inspect the rudder skin for loose rivets, and cracked intercostal flanges, and the rudder trim tab control rod for chafing, in accordance with GAF Nomad Alert Service Bulletin No. ANMD-55-11 (hereinafter referred to as the Service Bulletin) dated January 29, 1980, Part I and Part II, or an FAA-approved equivalent.
(1) If no cracks are found as a result of the inspection required by paragraph (a) of this AD, within the next 100 hours time in service after the effective date of this AD, unless already accomplished, perform the following modificationin accordance with Part III of the Service Bulletin:
(i) Replace rudder intercostal between W.L. 140.55 and W.L. 165.95 with an improved type or strengthen existing intercostal flanges.
(ii) Rework lower rudder intercostal lightening hole and angle to prevent chafing of rudder trim tab control rod.
(iii) Cut inspection hole in lower rib.
(2) If loose rivets or cracked flanges are found, before further flight, accomplish the modifications required by sub-paragraph (1)(i), (ii) and (iii) of this paragraph.
(b) Aircraft may be flown in accordance with FAR 21.197 and FAR 21.199 to a location where the modification can be performed.
(c) For purposes of complying with this AD, an FAA-approved equivalent must be approved by the Chief, Engineering and Manufacturing District Office, FAA, Pacific-Asia Region, Honolulu, Hawaii.
NOTE: All persons affected by this directive who have not already received the Service Bulletin from the manufacturer, may obtain copies upon request to the Government Aircraft Factories, 226 Lorimer Street, Port Melbourne 3207 Vic., Australia. These documents may also be examined at the FAA, Engineering and Manufacturing District Office, 300 Ala Moana Blvd., Room 7321, Honolulu, Hawaii 96850, or Rules Docket, Room 916, FAA, 800 Independence Avenue, S.W., Washington, D.C. 20591.
This amendment becomes effective June 23, 1980.
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2000-25-02: This amendment supersedes Airworthiness Directive (AD) 98-05-04, which currently requires you to repetitively inspect the front and rear wood spars for damage (including installing any as-needed inspection holes) and repair or replace any damaged wood spar on certain American Champion Aircraft Corporation (ACAC) Model 8GCBC airplanes. Damage is defined as cracks, compression cracks, longitudinal cracks through the bolt holes or nail holes, or loose or missing nails. This AD retains the actions of AD 98-05-04 for the ACAC Model 8GCBC airplanes; extends the actions to all ACAC 7, 8, and 11 series airplanes (except the inspections are not repetitive for certain 7 and 11 series airplanes); incorporates alternative methods of accomplishing the actions; and requires reporting any damage found. This AD is the result of a review of the service history of the affected airplanes that incorporate wood wing spars where damage was found in this area and consideration of all public comments received. The actions specified by this AD are intended to detect and repair or replace damaged wood wing spars. Continued operation with such damage could progress to in-flight structural failure of the wing with consequent loss of control of the airplane
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