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98-17-04: This amendment adopts a new airworthiness directive (AD) that is applicable to Hartzell Propeller Inc. HC-E4A-3(A,I,J) series propellers. This action requires a one-time inspection of the propeller blade counterweight clamps for thread damage in the bolt holes, and, if necessary, replacement with serviceable parts. This amendment is prompted by a report of a counterweight clamp bolt hole thread failure that resulted in the separation of the counterweight and the separation of a blade following impact with the counterweight. The actions specified in this AD are intended to prevent propeller blade counterweight clamp bolt hole thread failure, which can result in counterweight and propeller blade separation, and possible damage to the aircraft.
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2012-26-04: We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 757-200, -200PF, and -200CB series airplanes powered by Rolls-Royce engines. That AD currently requires repetitive inspections of the shim installation between the drag brace fitting vertical flange and bulkhead, and repair if necessary; for certain airplanes, an inspection for cracking of the four critical fastener holes in the horizontal flange, and repair if necessary; and, for airplanes without conclusive records of previous inspections, performing the existing actions. This new AD reduces the repetitive inspection interval; adds repetitive detailed inspections for cracking of the bulkhead, and repair if necessary; allows an extension of the repetitive intervals for certain airplanes by also doing repetitive ultrasonic inspections for cracking of the bulkhead, and repair if necessary; and provides an option for a high frequency eddy current inspection for cracking of the critical fastener holes, and repair if necessary. This action also adds a terminating action for certain repetitive inspections. This AD was prompted by reports of loose fasteners and cracks at the joint common to the aft torque bulkhead and strut-to-diagonal brace fitting, and one report of such damage occurring less than 3,000 flight cycles after the last inspection. We are issuing this AD to detect and correct cracks, loose and broken bolts, and shim migration in the joint between the aft torque bulkhead and the strut-to-diagonal brace fitting, which could result in damage to the strut and consequent separation of the strut and engine from the airplane.
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98-17-08: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires repetitive inspections to detect any discrepancy in the sealwire of the fireguards of the engine fire shut-off system, and repair, if necessary. 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 inadvertent closure of the fire shut-off valves due to ineffective or absent sealwires, which could result in in-flight engine shutdown.
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2008-18-02: The FAA is superseding an existing airworthiness directive (AD), which applies to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes. That AD currently requires repetitive tests for free movement of the capsule/bearing of the nose landing gear (NLG), and related investigative and corrective actions. This new AD requires a modified test for free movement of the capsule/bearing of the NLG at reduced repeat intervals, and replacement of the NLG assembly with a modified assembly. This AD results from additional reports of the NLG failing to extend fully on an airplane that had been inspected in accordance with AD 2004-14-07. We are issuing this AD to prevent failure of the NLG to extend fully, which could result in reduced controllability of the airplane during landing.
DATES: This AD becomes effective March 27, 2009.
The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of March 27, 2009.
On August 13, 2004 (69 FR 41413, July 9, 2004), the Director of the Federal Register approved the incorporation by reference of BAE Systems (Operations) Limited Alert Service Bulletin J41-A32-082, Revision 1, dated February 20, 2004.
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95-24-05 R1: 95-24-05 R1 MCCAULEY ACCESSORY DIVISION, THE CESSNA AIRCRAFT COMPANY: Amendment 39-9566. Docket 94-ANE-47. Revises AD 95-24-05, Amendment 39-9437.
Applicability: McCauley Accessory Division, The Cessna Aircraft Company, Model C35, C72, C74, C75, C80, C86, C87, C92, and C93 series propellers, incorporating the following Hub Models:
D3AF32C35-( ) D3AF32C80-( ) 3AF34C92-( )
3AF32C72-( ) 3AF34C86-( ) 3AF32C93-( )
3AF34C74-( ) 3AF32C87-( )
3AF32C75-( ) D3AF32C87-( )
The parentheses used in the above list indicate the presence or absence of an additional letter(s) which vary the basic propeller hub model designation. These letter(s) define minor changes that do not affect interchangeability or eligibility, and therefore, this airworthiness directive (AD) still applies regardless of whether these letters are present or absent on the propeller hub model designation.
These propellers are installed on but not limited to the following aircraft:
Beech 58, 58A, 95-C55, -C55A, -D55, -D55A, -E55, -E55A.
British Aerospace B-206 Series 2.
Cessna 310K, 310L, 310N, 310P, 310Q, 310R, T310P, T310Q, T310R, 320D, 320E, 320F, 335, 340, 340A, 401, 401A, 401B, 402, 402A, 402B, 402C, 411, 411A, 414, 414A, 421, 421A, 421B.
Colemill Executive 600 (Conversion of Cessna 310I, 310J, 310K, 310L, 310N).
RAM Conversion of Cessna 340.
NOTE 1: The above is not an exhaustive list of aircraft which may contain the affected McCauley Model C35, C72, C74, C75, C80, C86, C87, C92, and C93 series propellers, incorporating Models D3AF32C35, 3AF32C72, 3AF34C74, 3AF32C75, D3AF32C80, 3AF34C86, 3AF32C87, D3AF32C87, 3AF34C92, and 3AF32C93 propeller hubs because of installation approvals made by Supplemental Type Certificate or Federal Aviation Administration (FAA) Form 337 "Major Repair and Alteration," etc. It is the responsibility of the owner, operator and person returning the aircraft to service to determine if an aircraft has an affected propeller.
NOTE 2: This AD applies to each propeller 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 propellers 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 (g) 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 propeller from the applicability of this AD.
Compliance: Required as indicated, unless accomplished previously.
To prevent propeller blade separation due to a cracked propeller hub, which could result in separation of the engine from the aircraft and subsequent loss of aircraft control, accomplish the following:
(a) Within the next 25 hours time in service (TIS) after December 18, 1995 (the effective date of AD 95-24-05), unless already accomplished within the last 35 hours TIS, and thereafter at intervals not to exceed 60 hours TIS, perform a visual inspection for cracks and, if crack indications are found or suspected, confirm cracks by a dye penetrant inspection on propeller hubs in accordance with McCauley Accessory Division, The Cessna Aircraft Company, Service Bulletin (SB) No. 200C, dated January 20, 1994. Any propeller hubs found cracked during this inspection are to be permanently retired from service and replaced with a serviceable hub modified in accordance with paragraph (c) of this AD, or with an equivalent initial production propeller which has incorporated a hub containing oil with red dye.
(b) For affectedpropellers identified with the change letter "R" following the hub model designation and having an oil-fill plug in the side of the hub, compliance is required only with paragraphs (d) and (f) of this AD.
(c) Perform a one-time eddy current inspection and modify serviceable propeller hubs in accordance with the following schedule and requirements:
Propeller Time-In-Service (TIS) Compliance Required
on the effective date of
this AD.
Greater than 900 hours or 59 calendar Within the next 300 hours or at the next
months since last overhaul/penetrant annual inspection or by December 31, 1996,
inspection or installed new, or prior TIS whichever occurs first.
unknown.
Less than or equal to both 900 hours Prior to the accumulation of 1,200 hours
and 59 calendar months since last or 60 calendar months since last
overhaul/penetrant inspection or overhaul/penetrant inspection or installed
installed new. new, whichever occurs first.
(1) Perform a one-time eddy currentinspection for cracks in the threaded areas of the propeller hubs in accordance with McCauley Accessory Division, The Cessna Aircraft Company, Service Letter (SL) No. 1993-11A, dated June 20, 1995.
(2) Any propeller hubs found cracked during the eddy current inspection are to be permanently retired from service and replaced with a serviceable hub modified in accordance with paragraph (c) of this AD, or with an equivalent initial production propeller which has incorporated a hub containing oil with red dye.
(3) Modify affected propeller hubs to contain oil with red dye, in accordance with McCauley Accessory Division, The Cessna Aircraft Company, SL No. 1993-11A, dated June 20, 1995. Completion of this modification of the hub to contain oil with red dye constitutes terminating action to the repetitive inspections required by paragraph (a) of this AD.
NOTE: The modification of the propeller hub assembly to contain oil with a red dye provides an "on-condition" (in-service)means of early crack detection of the propeller assembly and also improves lubrication and corrosion protection. The oil will add approximately 4.0 lbs. to the weight of the propeller assembly.
(4) Previous compliance with McCauley Accessory Division SL 1993-11, dated September 15, 1993, also constitutes compliance with paragraphs (a) and (c) of this AD.
(5) Install Decal-Warning "Oil Filled", part number B-6493, in accordance with McCauley Accessory Division, The Cessna Aircraft Company, SL No. 1993-11A, dated June 20, 1995, Figure F-9.
(d) If leakage of oil containing red dye is detected in service (whether during flight or while on the ground), determine, prior to further flight, the source of leakage in accordance with the procedures specified in Section A-7 of McCauley SL No. 1993-11A, dated June 20, 1995. Remove from service, prior to further flight, propeller assemblies that exhibit cracks and replace with a serviceable unit, modified in accordance with paragraph(c) of this AD, or with an equivalent initial production propeller that has incorporated a hub containing oil with red dye. Oil-filled propellers are identified with the change letter "R" following the Hub Model Designation and have an oil-fill plug in the side of the hub.
(e) The "calendar month" compliance times stated in this AD allow the performance of the required action up to the last day of the month in which compliance is required. For example, a required eddy current inspection and modification 60 calendar months from last overhaul/penetrant inspection that was performed on December 15, 1991, would allow the eddy current inspection and modification to be performed no later than December 31, 1996.
(f) Report in writing any cracks found during the accomplishment of paragraphs (a), (c) or (d) of this AD to the Manager, Chicago Aircraft Certification Office, FAA, Small Airplane Directorate, 2300 East Devon Avenue, Room 232, Des Plaines, IL 60018; telephone (847) 294-7134, fax (847) 294-7834, within 10 days of the inspection. Information collection requirements contained in the regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (P.L. 96-511) and has been assigned OMB Control Number 2120-0056.
(g) 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, Chicago Aircraft Certification Office. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Chicago Aircraft Certification Office.
NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Chicago Aircraft Certification Office.
(h) 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 aircraft to a location where the requirements of this AD can be accomplished.
(i) The inspections and modification required by this AD shall be done in accordance with the following McCauley Accessory Division, The Cessna Aircraft Company, service documents:
Document No. Pages Date
SB 200C 1-4 January 20, 1994
Total pages: 4.
SL 1993-11A
Cover Page 1 June 20, 1995
Section A 1-4 June 20, 1995
Section B 1 June 20, 1995
Section C 1 June 20, 1995
Section D 1-7 June 20, 1995
Section E 1-10 June 20, 1995
Section F 1-15 June 20, 1995
Section G 1 June 20, 1995
Section H 1-4 June 20, 1995
Section I 1-4 June 20, 1995
Total pages: 48.
This incorporation by reference was approved by the Director of the Federal Register as of December 18, 1995, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from McCauley Accessory Division, The Cessna Aircraft Company, 3535 McCauley Dr., Vandalia, OH 45377-0430; telephone (513) 890-5246, fax (513) 890-6001. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(j) This amendment becomes effective on April 12, 1996.
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70-25-06: 70-25-06 ROLLS-ROYCE DART: Amdt. 39-1119. Applies to Rolls-Royce Dart Models 542-4, 542-4K, 542-10, 542-10J, and 542-10K engines.
Compliance is required as indicated, unless already accomplished.
To prevent cracking and subsequent failure of the engine propeller shaft and damage to the coarse pitch oil line due to material inclusions in that part of the shaft between the annulus gear support diaphragms, accomplish the following:
(a) For all airplanes with Rolls-Royce Dart Models 542-4, 542-4K, 542-10, 542-10J, and 542-10K engines installed except those having engine propeller shafts installed which have been supplied by Rolls-Royce with "CU" marked on the front end of the shaft, or in which each engine propeller shaft has been overhauled (including ultrasonic inspection for cracks and material inclusions) in accordance with Rolls-Royce Dart Overhaul Manual O-DA.10-AC and identified with "CU" marked on the front end of the shaft, and which are not listed in paragraph(g) of this AD, within the Next 50 hours' time in service after the effective date of this AD, install the following placard in clear view of the pilot and as close to the R.P.M. indicators as practicable: "In the event of abnormal, short duration R.P.M. increase (500-600 R.P.M.) accompanied by a drop in TGT and torque pressure at a fixed power setting, immediately feather affected propeller per AFM feathering instructions."
(b) For engines which have been feathered in accordance with the placard in paragraph (a), overhaul the engine propeller shaft (including ultrasonic inspection) in accordance with Rolls-Royce Dart Overhaul Manual O- DA.10AC to determine whether material inclusions or cracks exist in that part of the engine propeller shaft between the annulus gear support diaphragms, and whether the propeller coarse pitch oil line has been damaged. If material inclusions or cracks in the propeller shaft or damage to the propeller coarse pitch oil line are found, before furtherflight replace the cracked propeller shaft and damaged propeller coarse pitch oil line with an approved serviceable part of the same part number.
(c) For all engines having propeller shafts with 1200 or more hours' time in service on the effective date of this AD, within the next 450 hours' time in service and thereafter at intervals not to exceed 1200 hours' time in service since the last inspection, inspect each engine propeller shaft (including ultrasonic inspection) in accordance with Rolls-Royce Dart Aero Engine Alert Service Bulletin Number Da 72-367, dated September 17, 1969, or later ARB-approved issue or an FAA-approved equivalent. If material inclusions or cracks are detected during any inspection, before further flight replace the engine propeller shaft with an approved serviceable part of the same part number.
(d) For all engines having propeller shafts with less than 1200 hours' time in service on the effective date of this AD, within a total of 1650 hours' time in service, and thereafter at intervals not to exceed 1200 hours' time in service since the last inspection, inspect each engine propeller shaft (including ultrasonic inspection) in accordance with Rolls-Royce Dart Aero Engine Alert Service Bulletin Number Da 72-367, dated September 17, 1969, or later ARB-approved issue or an FAA-approved equivalent. If material inclusions or cracks are detected during any inspection, before further flight replace the engine propeller shaft with an approved serviceable part of the same part number.
(e) For Rolls-Royce Dart Models 542-4 and 542-4K engines installed in Convair airplanes, the repetitive inspections required by paragraphs (c) and (d) may be discontinued when propeller shafts are installed which have been supplied by Rolls-Royce with "CU" marked on the front end of the shaft, or which have been overhauled (including ultrasonic inspection for cracks and material inclusions) in accordance with Rolls-Royce Dart Overhaul Manual O-DA.10-AC and identified with "CU" marked on the front end of the shaft.
(f) For all engines with propeller shafts installed bearing the serial numbers listed in paragraph (g), the placard required by paragraph (a) may not be removed until an FAA-approved inspection method has been developed to insure that the shafts are free from defects.
(g) For Rolls-Royce Dart Models 542-4 and 542-4K engine with propeller shafts installed bearing the serial numbers listed below and which are not installed in Convair airplanes and for all Rolls-Royce Models 542- 10, 542-10J and 542-10K engines with propeller shafts installed bearing the serial numbers listed below, the repetitive inspection required by paragraphs (c) and (d) may not be discontinued until an FAA-approved inspection method has been developed to insure that the shafts are free from defects:
INSPECTION OF DART PROPELLER SHAFTS IN INSTALLED ENGINES -
SHAFTS FROM TOP THREE INGOT POSITION
Shaft Serial No.
Shaft Serial No.
Shaft Serial No.
Shaft Serial No.
Shaft Serial No.
Shaft Serial No.
Shaft Serial No.
HA.275
HD. 86
HE.111
HJ.135
HM.267
HR.536
HS. 8
HA.277
HD. 88
HE.115
HJ.138
HM.272
HR.547
HS. 11
HA.281
HD. 94
HE.121
HJ.143
HM.288
HR.551
HS. 13
HD. 95
HE.129
HJ.151
HM.289
HR.552
HS. 14
HB. 25
HD. 97
HE.135
HJ.153
HM.294
HR.553
HS. 16
HB. 29
HD.103
HE.139
HJ.157
HM.436
HR.580
HS. 24
HB. 30
HD.105
HE.141
HJ.165
HR.581
HS. 25
HD.107
HE.142
HJ.167
HR.315
HR.583
HS. 28
HC.846
HD.110
HE.143
HJ.168
HR.319
HR.592
HS. 29
HC.847
HD.117
HJ.173
HR.326
HR.595
HS. 30
HC.849
HD.119
HG.562
HJ.176
HR.337
HR.596
HS.129
HC.854
HD.373
HG.563
HJ.178
HR.345
HR.597
HS.131
HC.856
HD.376
HG.570
HJ.180
HR.346
HR.600
HS.139
HC.857
HD.377
HG.571
HJ.189
HR.439
HR.601
HS.140
HC.858
HD.391
HG.572
HJ.190
HR.442
HR.780
HS.142
HC.861HD.392
HJ.196
HR.447
HR.781
HS.149
HC.862
HD.394
HH.699
HJ.197
HR.448
HR.789
HS.150
HD.399
HH.700
HJ.199
HR.511
HR.980
HS.153
HD. 60
HD.401
HH.714
HJ.201
HR.513
HR.981
HS.156
HD. 61
HD.404
HH.715
HJ.207
HR.520
HR.989
HD. 62
HD.413
HH.716
HJ.212
HR.527
HR.993
HD. 67
HD.414
HH.717
HJ.218
HR.528
HR.995
HD. 69
HD.421
HH.719
HJ.219
HR.529
HD. 71
HD.425
HH.720
HJ.223
HR.532
HS. 1
HD. 73
HD.427
HH.721
HR.533
HS. 5
HD. 74
HM.266
HR.535
HS. 7
INSPECTION OF DART PROPELLER SHAFTS IN INSTALLED ENGINES -
SHAFTS FROM UNRECORDED INGOT POSITIONS
Shaft Serial No.
Shaft Serial No.
Shaft Serial No.
Shaft Serial No.
Shaft Serial No.
Shaft Serial No.
Shaft Serial No.
HA. 28
HA.961
HC.577
HD.840
HH.670
HJ.957
HM.398
HA. 29
HA.962
HC.578
HD.841
HH.671
HJ.958
HM.399
HA. 30
HA.963
HC.579
HD.842
HH.672
HM.400
HA. 31
HA.964
HC.580
HD.843
HH.673
HM.355
HM.401
HA. 32
HC.581
HD.844
HH.674
HM.356
HM.402
HA. 37
HB. 35
HC.582
HD.845
HH.675
HM.357
HM.403
HA. 70
HB. 36
HC.850
HD.846
HH.676
HM.358
HM.404
HA. 71
HB. 37
HC.852
HD.847
HH.677
HM.359
HM.405
HA. 72
HB. 38
HC.853
HD.848
HH.678
HM.360
HM.406
HA. 73
HB. 39
HC.855
HD.849
HH.679
HM.361
HM.407
HA. 74
HB. 40
HC.859
HD.850
HH.680
HM.362
HM.408
HA. 75
HB. 41
HC.996
HD.851
HH.681
HM.363
HM.409
HA. 76
HB.975
HD.852
HH.682
HM.364
HM.410
HA. 77
HB.976
HD.807
HH.683
HM.365
HM.411
HA. 78
HB.977
HD.808
HH.638
HH.684
HM.366
HM.412
HA. 79
HB.978
HD.809
HH.639
HH.685
HM.367
HM.413
HA. 80
HB.979
HD.810
HH.640
HH.686
HM.368
HM.414
HA. 81
HB.980
HD.811
HH.641
HH.687
HM.369
HM.415
HA. 82
HB.981
HD.812
HH.642
HH.688
HM.370
HM.416
HA. 83
HB.982
HD.813
HH.643
HH.689
HM.371
HM.417
HA. 84
HD.814
HH.644
HH.690
HM.372
HM.418
HA. 85
HC.539
HD.815
HH.645
HH.691
HM.373
HM.419
HA. 86
HC.540
HD.816
HH.646
HH.692
HM.374
HM.420
HA. 87
HC.541
HD.817
HH.647
HH.693
HM.375
HM.421
HA. 88
HC.542
HD.818
HH.648
HH.694
HM.376
HM.422
HA. 89
HC.543
HD.819
HH.649
HH.798
HM.377
HM.423
HA. 90
HC.544
HD.820
HH.650
HH.799
HM.378
HM.424
HA. 91
HC.545
HD.821
HH.651
HH.800
HM.379
HM.425
HA. 92
HC.546
HD.822
HH.652
HH.801
HM.380
HM.426
HA. 93
HC.547
HD.823
HH.653
HH.802
HM.381
HM.427
HA. 94
HC.548
HD.824
HH.654
HH.803
HM.382
HM.428
HA. 95
HC.549
HD.825
HH.655
HH.804
HM.383
HM.429
HA. 96
HC.550
HD.826
HH.656
HM.384
HM.430
HA. 97
HC.558
HD.827
HH.657
HJ.944
HM.385
HM.431
HA.592
HC.559
HD.828
HH.658
HJ.945
HM.386
HM.432
HA.595
HC.560
HD.829
HH.659
HJ.946
HM.387
HM.433
HA.690
HC.561
HD.830
HH.660
HJ.947
HM.388
HM.434
HA.952
HC.562
HD.831
HH.661
HJ.948
HM.389
HM.435
HA.953
HC.563
HD.832
HH.662
HJ.949
HM.390
HA.954
HC.564
HD.833
HH.663
HJ.950
HM.391
HR.355
HA.955
HC.565
HD.834
HH.664
HJ.951
HM.392
HA.956
HC.566
HD.835
HH.665
HJ.952
HM.393
HA.957
HC.567
HD.836
HH.666
HJ.953
HM.394
HA.958
HC.568
HD.837
HH.667
HJ.954
HM.395
HA.959
HC.569
HD.838
HH.668
HJ.955
HM.396
HA.960
HC.576
HD.839
HH.669
HJ.956
HM.397
These numbers are listed in Appendices A and B of Rolls-Royce Dart Aero Engine Service Bulletin No. Da 72-367, Revision 2, dated February 18, 1970.
This supersedes Amendment 39-913, 35 F.R. 145, AD 70-2-3 as amended by Amendment 39-1056, 35 F.R. 12270.
This amendment becomes effective December 7, 1970.
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91-25-11: 91-25-11 EMBRAER (EMPRESA BRASILEIRA de AERONAUTICA, S.A.): Amendment 39-8167. Docket No. 91-CE-92-AD.
Applicability: EMB-110 Series airplanes (all serial numbers), certificated in any category.
Compliance: Required within the next 10 hours time-in-service after receipt of this AD, unless already accomplished.
To prevent severe vibration, flutter, and loss of control of the airplane caused by incorrect installation of the rudder trim tab system, accomplish the following:
(a) Visually inspect the rudder trim tab system for correct assembly in accordance with the instructions in EMBRAER Service Bulletin (SB) No. 110-27-0091, dated December 5, 1991.
(1) If determined to be correctly installed in accordance with the criteria specified in EMBRAER SB No. 110-27-0091, return the airplane to service.
(2) If determined to be incorrectly installed in accordance with the criteria specified in EMBRAER SB No. 110-27-0091, reinstall the rudder trim tab system in accordance with the instructions in EMBRAER SB No. 110-27-0091.
(b) 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.
(c) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office.
(d) The inspection and possible reinstallation required by this AD shall be done in accordance with EMBRAER Service Bulletin (SB) No. 110-27-0091, dated December 5, 1991. 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 EMBRAER, P.O. Box 343-CE, 12.200 Sao Jose dos Campos, Sao Paulo, Brazil; or EMBRAER Aircraft Corporation, 276 SW 34th Street, Fort Lauderdale, Florida 33315. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC.
(e) This amendment (39-8167, AD 91-25-11) becomes effective on February 10, 1992, as to all persons except those persons to whom it was made immediately effective by priority letter AD 91-25-11, issued 12/6/91, which contained this amendment.
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2022-06-07: The FAA is superseding Airworthiness Directive (AD) 2016-09- 01, which applied to certain The Boeing Company Model 777-200 and -300 series airplanes. AD 2016-09-01 required repetitive inspections for cracking of the left- and right-side forward outer chords of the pivot bulkhead, and related investigative and corrective actions if necessary. AD 2016-09-01 also provided a modification of the pivot bulkhead, which terminated the repetitive inspections. This AD was prompted by reports of fatigue cracking of the forward outer chord of the station (STA) 2370 pivot bulkhead, and the determination that the compliance times need to be reduced, post-modification inspections must be done, and the inspections areas need to be expanded due to additional cracking found prior to the inspection times required by AD 2016-09-01. This AD retains certain requirements of AD 2016-09-01. This AD also requires doing repetitive detailed and high frequency eddy current (HFEC) inspections of the longeron fitting, and, for post- repair and post-modification inspections, the bulkhead assembly structure, for any cracking, and doing all applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
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2009-04-05: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 182Q and 182R airplanes that are equipped with Societe de Motorisations Aeronautiques (SMA) Aircraft Diesel Engine (ADE) Model SR305-230-1 or Model SR305-230 converted to Model SR305-230-1 installed under Supplemental Type Certificate (STC) SA03302AT. This AD requires you to remove the intercooler and the intercooler inlet and outlet hoses, install a reworked intercooler and new intercooler inlet and outlet hoses, inspect hoses and clamp torques, repetitively inspect installation of the intercooler outlet and inlet hose assemblies for any displacement or damage of clamps or hoses, and, if necessary, replace any damaged clamps or hoses. This AD results from a report of two instances of induction hose disconnection occurring while in service, resulting in a loss of turbo boost and a significant loss of engine power. We are issuing this AD to detect and correct improper intercooler outlet and intercooler inlet hose assembly installations, which could result in loss of turbo boost and a significant loss of engine power. This failure could lead to an inability to maintain constant altitude in flight.
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98-17-01: This amendment supersedes an existing airworthiness directive (AD), applicable to AlliedSignal Inc. TFE731 series turbofan engines, that currently requires the installation of a clamp assembly to support the rigid fuel tube. This action would require the installation of a clamp assembly to support the rigid fuel tube. This amendment requires installation of an improved flexible (flex) fuel tube. This amendment is prompted by reports of fuel leaks from a cracked fuel tube in engines that have already installed a clamp assembly in accordance with the current AD. The actions specified by this AD are intended to prevent cracking of the fuel tube and the subsequent leakage of fuel on or around electrical components, which can cause an engine fire.
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