82-24-05: 82-24-05 DETROIT DIESEL ALLISON: Amendment 39-4498. Applies to all Detroit Diesel Allison (DDA) Model 250 series engines equipped with Bendix fuel control assemblies and power turbine governor assemblies containing or suspected of containing P/N 2526146 bushing assemblies with a nylon ball bearing separator.
NOTE: Assemblies listed in the appendix to this AD have steel ball bearing separators.
Compliance required, as indicated, unless already accomplished.
To prevent possible engine power loss, autoacceleration, overspeeding, or power turbine governor instability/malfunctioning caused by failure of P/N 2526146 bushing assemblies with a nylon ball bearing separator installed in Bendix fuel control assemblies and power turbine governor assemblies, accomplish the following:
(a) Before further flight, remove from service affected Bendix fuel control assembly and power turbine governor assembly that exhibit one or more of the following symptoms that cannot be corrected by following the maintenance procedures in the appropriate DDA Operations and Maintenance Manual and, where applicable, install assemblies that have steel ball bearing separators:
Fuel Control Assembly Symptoms
N1 fluctuation
Autoacceleration or overspeed
Inability to obtain maximum power or N1 limiting
Inability to adjust/set idle speed or excessive flight idle
Power Turbine Governor Symptoms
Governor instability
Excessive droop which cannot be cured by correct control system rigging
NOTE: Above symptoms manifested by fuel control assemblies or power turbine governor assemblies which incorporate steel ball bearing separators should be corrected using appropriate DDA Operations and Maintenance Manual procedures.
(b) Inspect in accordance with Paragraph (c) affected Bendix fuel control assemblies and power turbine governor assemblies within the hours time in service specified in the following schedule or before October 16, 1983, whichever occurs first:
Time in Service (Hours) of Fuel Control or Power Turbine Governor Since New or Last Overhaul
Inspect Within The Following Time (Hours) In Service
Less than 300
100
300 or more and less than 600
50
600 or more and less than 900
150
900 or more and less than 1200
200
More than 1200
250
(c) Inspect in accordance with the applicable DDA Commercial Engine Alert Bulletin, or later FAA- approved revision, listed below to determine whether the P/N 2526146 bushing assembly with a nylon ball bearing separator is installed:
Engine Model
Bulletin No., dated October 15, 1982
250-C18
CEB-A-229
250-C20, -C20B, -C20F, -C20J
CEB-A-1206
250-B15G
CEB-A-99
250-B17, -B17B, -B17C
CEB-A-1166
250-C28B, -28C
CEB-A-73-2026
250-C30, -C30P, -C30S
CEB-A-73-3021
(d) If a bushing assembly containing a nylon ball bearing separator is identified during inspection required by Paragraph (c), replace the bushing assembly with a serviceable assembly having a steel ball bearing separator. Reidentify serviceable fuel control assemblies or power turbine governor assemblies, after inspection, in accordance with the applicable DDA service bulletin.
(e) Special flight permits may be issued in accordance with FARs 21.197 and 21.199 to operate aircraft to a base where compliance with this AD can be accomplished.
(f) Upon request of an operator, the Manager, Chicago Aircraft Certification Office, FAA, Central Region, may adjust the compliance time specified in this AD provided such requests are made through an FAA maintenance inspector, and the request contains substantiating data to justify the request for that operator.
(g) Upon request of the operator, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Chicago Aircraft Certification Office, FAA, Central Region.
This amendment becomes effective November 26, 1982.
AD 82-24-05 APPENDIX
All Bendix fuel control assemblies andpower turbine governor assemblies installed in DDA Model 250 series engines are suspected of containing nylon ball bearing separators, except the following assemblies all of which have steel ball bearing separators:
1. Units identified by the letter "K" marked on the fuel control assemblies or power turbine governor assemblies identification plate in the "less issues" (LI) block.
2. The following fuel control assemblies and power turbine governor assemblies which have acceptable New Hampshire Ball Bearing (NHBB) bushing assemblies and are NOT marked with letter "K."
Model
Bendix Part No.
DDA Part No.
DDA Model
Unit Serial No.
Fuel Control Assemblies:
DP-N2
2524644-18
23001794
250-C20B/F/J
336103 and subsequent
DP-P2
2524654-15
23001796
250-B17B/C
336036 and subsequent
DP-T3
2524738-20
23001797
250-C28B/C
334078 and subsequent
DP-V1
2524854-1
23004537
250-C30P
336051 and subsequent
DP-V1
2524745-17
23001798
250-C30/S
334132 and subsequent
Power Turbine Governor Assemblies:
AL-AA1
2524667-8
23005492
250-C20/B/F
29288 and subsequent
AL-AA1
2524769-7
23005493
250-C20B/J
29367 and subsequent
AL-AC1
2524677-6
23005494
250-C28B/C
27511 and subsequent
AL-AD1
2524692-5
23006268
250-C30/P/S
28914 and subsequent
3. Fuel control assemblies and power turbine governor assemblies manufactured prior to November 7, 1979, provided that they have NOT been overhauled or have NOT had P/N 2526146 bushing assembly replaced since that date. The following listed fuel control assemblies and power turbine governor assemblies were manufactured prior to November 7, 1979:
Model
Bendix Part No.
Engine Model
All Serial Numbers Including and Prior To
Fuel Control Assemblies:
DP-D3
2524463
250-C18
323884
DP-D3
2524527
250-C18
326174
DP-M1
2524384
250-B15G
319258
DP-N1
2524552
250-C20
320894
DP-N2
2524644
250-C20B, C20F, C20J
327936
DP-P1
2524558
250-B17
319575
DP-P2
2524654
250-B17B
327892
DP-P2
2524661
250-B17B, B17C
317461
DP-T3
2524738
250-C28B, C28C
328100
DP-V1
2524745
250-C30, C30S
326387
Power Turbine Governor Assemblies:
AL-AA1
2524553
250-C20/B/F
18010
AL-AA1
2524667
250-C20/B/F
22797
AL-AA1
2524706
250-C20/B/J
20218
AL-AA1
2524769
250-C20/B/J
22921
AL-AC1
2524677
250-C28B, C28C
23097
AL-AD1
2524692
250-C30, C30P, C30S
21897
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79-04-05: 79-04-05 AVCO LYCOMING: Amendment 39-3418 as amended by Amendment 39-3570. Applies to all fuel injected Lycoming series engines equipped with the following Bendix Injector Models and Parts List Numbers:
Model
Parts List and Issue
Serial Numbers
RSA-5AB1
2524254-4
2524712-1
63758 thru 65862
63503 thru 66027
RSA-5AD1
2524054-4
62999 thru 66249
2524147-6
65988 thru 65997
2524171-4
64961 thru 65060
2524213-4
61032 thru 66290
2524291-4
63678 thru 65867
2524297-3
64428 thru 64432
2524307-3
64828 thru 66854
2524335-3
65721 thru 66920
2524359-3
62401 thru 65412
2524450-2
61392 thru 65987
2524550-1
64635 thru 65887
2524673-1
63643 thru 64265
2524682-1
65071 thru 65499
2524723-1
61928 thru 65231
2524469(B)
64915 thru 65338
RSA-10AD1
2524163-7
63742 thru 65720
2524175-3
63399 thru 66941
and to all Lycoming fuel injected engines irrespective of parts list number or serial number whose Bendix Injector Models RSA-5AD1, RSA-5AB1, and RSA-10AD1 have been overhauled by a Bendix Authorized Warrant Repair Station or by AVCO Lycoming between April 1, 1977, and August 14, 1978, and to all Lycoming fuel injected engines irrespective of parts list number or serial number, whose Bendix Models RSA-5AB1, RSA- 5AD1, and RSA-10AD1 fuel injectors have been overhauled after March 31, 1977, by repair stations other than the above in which the fuel diaphragm has been replaced with a new P/N 2529471 diaphragm assembly.
Compliance required within the next 10 hours in service after the effective date of this AD, unless previously accomplished.
To prevent an in-flight power loss due to the separation of the P/N 2529192 regulator diaphragm stem assembly, the P/N 2529471 regulator diaphragm assembly must be removed, inspected, and replaced if necessary, in accordance with the Accomplishment Instructions listed in Bendix Energy Controls Division Service Bulletin No. RS-57 Rev. 1 or FAAapproved equivalent.
Equivalent methods of compliance must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Eastern Region. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region may adjust the compliance time specified in this AD.
NOTE: AVCO Lycoming Service Bulletin No. 433A also pertains to this subject.
Amendment 39-3418 was effective February 26, 1979.
This Amendment 39-3570 is effective September 26, 1979.
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98-01-14: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-01-14, which was sent previously to all known U.S. owners and operators of Cessna Aircraft Company (Cessna) Model 182S airplanes. This AD requires replacing the left and right Aeroquip engine exhaust mufflers (P/N 71379-1254017-8) with an FAA-approved equivalent part. Reports of carbon monoxide gas entering the cabin heating system and the cabin of the Cessna Model 182S airplanes prompted this action. This condition, if not corrected, could result in passenger and pilot injury with consequent loss of control of the airplane.
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2019-07-01: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FAN JET FALCON and FAN JET FALCON SERIES C, D, E, F, and G airplanes. This AD was prompted by a determination of the need for a revision to the airplane airworthiness limitations to introduce changes to the maintenance requirements and airworthiness limitations. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations and maintenance requirements. We are issuing this AD to address the unsafe condition on these products.
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2019-07-04: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 757 airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the inner skin of the lap splices, at the lower fastener row, is subject to scratch cracks that may interact with widespread fatigue damage (WFD). This AD requires a general visual inspection (GVI) of certain lap splice inspection areas for any repair common to the fuselage skin lap splice dual frequency eddy current (DFEC) inspection areas, repetitive DFEC inspections of certain lap splice inner skins for any crack, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
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59-06-04: 59-06-04 NAVION: Tusco Corporation (Navion) Applies to All Models.
Several failures of hydraulic actuating cylinders have occurred causing the loss of the use of the flaps and the landing gear to collapse.
To prevent further difficulties of this nature, the following items must be accomplished by May 1, 1959, and at each periodic inspection thereafter.
(1) Inspect the flap and landing gear actuating cylinders for cracks. If any cracks appear, the cylinder must be replaced.
(2) Determine, by means of a hydraulic gage, that the hydraulic system pressure relief valve is adjusted to 1125+25, -0 p.s.i. Excessive pressures could cause damage to the components of the system.
(3) Hydraulic fluid restrictors are required in the nose gear lines, Serial Numbers 1271 and subsequent, main gear lines, Serial Numbers 1790 and subsequent, and flap lines, all serial numbers.
(4) Inspect the linkage adjustments of the landing gear bungee springs and the flap stops anddetermine that they have been properly adjusted in accordance with appropriate service manuals.
(Tusco Corporation Service Letter No. 79 dated December 23, 1958, covers this same subject.)
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2019-06-09: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by reports that baby bassinet inserts installed on airplane stowages and partitions were found loose because a self-securing fixation device (Loctite) had not been applied. This AD requires repetitive tightness checks of the baby bassinet inserts installed on stowages and partitions and, depending on findings, accomplishment of applicable corrective actions, as specified in an European Aviation Safety Agency (EASA) AD, which is incorporated by reference. We are issuing this AD to address the unsafe condition on these products.
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2005-25-20: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A330-300, A340-200, and 340-300 series airplanes. The existing AD requires repetitive inspections to detect cracking of the fuselage skin in the area of the VHF2 antenna, and repair if necessary. The existing AD also provides for optional terminating action for the repetitive inspections. This new AD requires accomplishment of the previously optional terminating action, and revises the applicability by removing certain airplanes. This AD is prompted by the need to change the applicability of the existing AD and to mandate the formerly optional terminating action. We are issuing this AD to prevent cracking of the fuselage skin in the area of the VHF2 antenna, which could result in depressurization of the airplane.
DATES: Effective December 29, 2005.
The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of December 29, 2005.
The incorporation by reference of certain other publications, as listed in the regulations, was approved previously by the Director of the Federal Register as of April 12, 2000 (65 FR 12075, March 8, 2000).
We must receive comments on this AD by February 13, 2006.
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2005-25-15: The FAA is adopting a new airworthiness directive (AD) for certain Dassault Model Falcon 2000 airplanes equipped with CFE Company CFE738- 1-1B turbofan engines. This AD requires determining the serial number of the engines installed on the airplane, inspecting any affected engine to verify that a spherical bearing is installed on the attachment fitting of the engine mount, and corrective action if necessary. This AD results from a report of a missing spherical bearing on the attachment fitting of the front engine mount on an in-service airplane, and subsequent damage and abnormal fatigue of the attachment fitting. We are issuing this AD to prevent reduced structural integrity of the engine mount, which could result in possible separation of an engine from the airplane.
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2011-17-10: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
* * * [T]he Federal Aviation Administration (FAA) have published Special Federal Aviation Regulation (SFAR) 88, and the Joint Aviation Authorities (JAA) have published Interim Policy INT/POL/25/ 12. The review conducted by Fokker Services on the Fokker F28 type design in response to these regulations revealed that, on certain aeroplanes, an interrupted shield contact may exist or develop between the housing of an in-tank Fuel Quantity Indication (FQI) cable plug and the cable shield of the shielded FQI system cables in the main and collector fuel tanks which can, under certain conditions, form a spark gap.
This condition, if not detected and corrected, may create an ignition source in the tank vapour space, possibly resulting in a wing fuel tank explosion and consequent loss of the aeroplane.
* * * * *
We are issuing this AD to require actions to correct the unsafe condition on these products.
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