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55-14-01: 55-14-01 BELL: Applies to Model 47G Helicopters Below Serial Number 1317.
Compliance required as soon as possible, but no later than September 15, 1955.
In order to provide additional support for the No. 1 bearing hangar, P/N 47-664-148-15, and the forward cross tube of the tail boom, P/N 47-267-088-1, it is mandatory that the support bracket installation be completed in accordance with Bell Drawing 47-267-402-1.
(Bell's Mandatory Service Bulletin No. 99, dated April 29, 1955, covers this same subject and outlines the details for the installation.)
NOTE: This does not eliminate the need for the mandatory daily preflight inspection for cracks in the No. 1 bearing hangar area called for in Bell's Maintenance and Overhaul Manual.
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74-25-02: 74-25-02 TED R. SMITH & ASSOCIATES, INC.: Amendment 39-2029. Applies to Aerostar Models 600/601/601P airplanes certificated in all categories with electrical attitude and directional gyros and 70 amp alternators installed either by the manufacturer or by incorporating STC SA2336WE or STC SA2367WE, as provided below.
Compliance required within the next 30 days after the effective date of this AD, unless already accomplished.
To prevent the possible overloading of the remaining alternator system after failure of either one of the dual alternator systems, accomplish the following:
(1) Amend, in pertinent part, the Electrical System Load Limitations Section of the FAA-approved Airplane Flight Manual for those airplanes affected, as follows:
"Electrical System Load Limitations
Aircraft with electrical attitude and directional gyros installed and equipped with 70 amp alternators: Do not exceed 55 amps continuous electrical load during IFR conditions.
NOTE.To determine actual alternator load, total the left and right amp readings. Do not read main position for actual alternator load."
(2) Install a placard in the cockpit, and add to the placard list in the AFM Limitations Section which provides: "Do not exceed 55 amps continuous electrical load during IFR conditions."
(3) This airworthiness directive must remain with the Airplane Flight Manual until replaced by an FAA-approved AFM revision issued by Ted R. Smith & Associates, Inc. providing the limitations of this A.D.
(4) The limitations described in (1), above, and placard installed per (2), above, may be removed upon the installation of an alternate electrical warning system approved by the Chief, Aircraft Engineering Division, FAA Western Region.
This amendment becomes effective December 4, 1974.
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75-17-33: 75-17-33 SIKORSKY: Amendment 39-2327 as amended by Amendment 39-2462. Applies to S-61L, S-61N, and S-61NM helicopters certificated in all categories equipped with sliding baggage door S6120-72601-1, including helicopters equipped with S6120-72615-1 and S6120-72615-2 track and fitting assemblies, or S6120-72615-5 and S6120-72615-2 track and fitting assemblies with S6120-72605-1 and S6120-72605-2 track assemblies or 61200-72539-041 and 61200-72539-042 track assemblies.
Compliance required on or before November 3, 1975, unless already accomplished.
(a) To prevent the loss of the baggage door in flight and possible damage to the helicopter rotors, accomplish the following:
Install baggage door retainers, P/N 61200-72538-101 and 61200-72538-102 or equivalent FAA approved parts in accordance with Sikorsky Service Bulletin No. 61B20-11B dated June 27, 1975 or later FAA approved revisions.
(b) To prevent door misalignment, which may contribute to door disengagement, accomplishthe following:
Install upper track stops, P/N S6120-72629-1 with angle P/N S6120-72629-3 and plate P/N S6120-72629-4 or equivalent FAA approved parts in accordance with Sikorsky Service Bulletin S61B20-11B dated June 27, 1975 or later FAA approved revision.
(c) To prevent possible loss of bearing cage, which may contribute to door disengagement, accomplish the following:
Install track end stops, P/N 61200-72381-101, 61200-72381-102, 61200-72381-103, 61200-72381-104, S6120-72618-8 and S6120-72618-10 stops or equivalent FAA approved parts in accordance with Sikorsky Service Bulletin No. 61B20-20 dated August 15, 1975 or later FAA approved revisions.
Include Sikorsky telegram SST6120CC036.1, dated October 2, 1975, as part of Sikorsky Service Bulletin No. S61B20-20.
(d) The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Sikorsky Aircraft, Stratford, Connecticut 06602. These documents may also be examined at the Office of Regional Counsel, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803 and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the New England Region Headquarters, Burlington, Massachusetts.
Amendment 39-2327 became effective August 20, 1975.
This amendment 39-2462 becomes effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated October 3, 1975.
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70-02-02: 70-02-02 PRATT & WHITNEY: Amdt. 39-922 as amended by Amendment 39-969. Applies to all JT8D series turbofan engines which incorporate the following serial number sixth stage compressor rotor disc:
1V5825
1V5969
1V6073
1V6371
1V5826
1V5970
1V6083
1V6375
1V5828
1V5976
1V6093
1V6394
1V5831
1V5977
1V6094
1V6398
1V6096
1V5980
1V5832
1V5833
1V5981
1V6097
1V6663
1V5835
1V5982
1V5851
1V5987
1V6101
2T8050
1V5857
1V5992
1V6103
1V5859
1V6106
7S6324
1V5860
1V6000
1V6112
1V5862
1V6003
1V6113
7S6409
1V5863
1V6005
1V6115
7S6449
1V5864
1V6006
1V6117
1V5871
1V6007
1V6132
8T7257
1V5875
1V6008
1V6148
1V5878
1V6010
1V6151
8T7335
1V5882
1V6013
1V6152
1V5885
1V6016
1V6158
8T7450
V5890
1V6020
1V6162
8T7462
1V5896
1V6022
1V6164
8T7470
1V6027
1V6171
8T7474
1V5904
1V6028
1V6172
8T7487
1V591
1V6031
1V6175
8T7489
1V5916
1V6032
1V6182
8T7490
1V59201V6034
1V6194
8T7491
1V5923
1V6036
1V5935
1V6043
1V6209
8T7513
1V5938
1V6046
1V6222
8T7517
1V5943
1V6047
1V6240
8T7520
1V5945
1V6050
1V6247
8T7524
1V5948
1V6054
1V6251
8T7544
1V5952
1V6056
1V6260
8T7552
1V5954
1V6057
1V6273
8T7562
1V5956
1V6058
1V6274
8T7569
1V5957
8T7567
1V6068
1V5964
1V6072
1V6350
8T7570
8T7572
8T7636
8T7681
8T7695
8T7588
8T7638
8T7686
8T7696
8T7589
8T7655
8T7688
8T7699
8T7597
8T7657
8T7689
8T7669
8T7690
8T7704
8T7621
8T7679
8T7692
8T7708
Compliance required as indicated.
To preclude sixth stage compressor rotor disc failures as the result of abnormal processing of the edge radius in the base of the blade slots, accomplish the following:
a. For engines incorporating any of the previously listed sixth stage compressor rotor discs:
1. With 1700 hours' or more in service since new within the next 600 hours in service after the effective date ofthis AD replace the suspect sixth stage compressor rotor disc with a new, used or reworked disc, approved by Chief, Engineering & Manufacturing Branch, Eastern Region, New York.
2. With 1700 hours' or less in service since new prior to the accumulation of 2300 hours' in service replace the suspect sixth stage compressor rotor disc with a new, used or reworked disc approved by Chief, Engineering & Manufacturing Branch, Eastern Region, New York.
b. 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.
Amendment 39-922 effective February 16, 1970.
This amendment (39-969) is effective April 15, 1970.
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2011-11-08: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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:
There have been several findings of cracking at the firtrees of LP Turbine discs. Fatigue crack initiation and subsequent crack propagation at the firtree may result in multiple LP Turbine blade release. The latter may potentially be beyond the containment capabilities of the engine casings. Thus, cracking at the firtrees of LP Turbine discs constitutes a potentially unsafe condition.
We are issuing this AD to detect cracks in the low-pressure (LP) turbine stage 1, 2, and 3 discs, which could result in an uncontained release of LP turbine blades and damage to the airplane.
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2011-07-06: 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:
* * * There have recently been several in-service occurrences that
have highlighted the inability of the existing [wing anti-ice] system to detect a low-heat condition in the wing leading edge at all times, with the potential consequence of unannunciated asymmetric ice build-up on the wing. * * *
[[Page 18025]]
Such a condition, in combination with maneuvers close to stick shaker activation, could possibly result in reduced controllability of the aircraft.
* * * * *
We are issuing this AD to require actions to correct the unsafe condition on these products.
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73-12-02: 73-12-02 DOWTY ROTOL: Amdt. 39-1653. Applies to Dowty Rotol Propellers, type (c)R186/4-30-4/16 which have not been modified in accordance with Modification No. (c) VP.2388 (Rev. 3). These propellers are installed on, but not necessarily limited to, Armstrong Whitworth Argosy Type A.W. 650 Series 101 airplanes.
Compliance is required as indicated.
To prevent cracking of the propeller hub front wall, accomplish the following:
Within the next 200 hours' time in service after the effective date of this AD, or prior to the accumulation of 8,000 hours total time in service, whichever occurs later, strengthen the propeller hub and hub driving center by incorporating Modification No. (c) VP.2388, Revision 3, in accordance with Dowty Rotol Service Bulletin No. 61-604 (Rev. 2) dated November 24, 1971, or an FAA-approved equivalent.
This amendment becomes effective July 1, 1973.
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73-16-02: 73-16-02 CESSNA: Amendment 39-1697 as amended by Amendment 39-1807. Applies to:
1) Paragraphs A and C of the AD are applicable to Model 188 series airplanes (Serial Numbers 188-0001 through 18801348), except those that have a centerline pulley installed in lieu of fair-leads per Cessna Service Letters SE72-1 or SE73-33. Service Letter SE72-1 dated January 14, 1972, is applicable to Serial Numbers 188-0001 through 18800707. Service Letter SE73-33, Item #1, dated November 5, 1973, is applicable to Serial Numbers 18800708 through 18801348.
2) Paragraphs B, C and D of the AD are applicable to Model 188 (Serial Numbers 188-0001 through 18800707) Series airplanes.
Compliance: Required as indicated, unless already accomplished.
To insure integrity of the aileron control cables, within the next 25 hours' time in service after the effective date of this AD and thereafter at 100 hour intervals time in service, accomplish Paragraphs A, B, and C and accomplish Paragraph Das indicated:
A) Inspect those portions of the aileron control cables that move in the area of the fair-leads near B.L. 20 (aft of the rear spar) for frayed or broken cable strands.
B) 1. To perform the inspections required by Paragraph B) 2.(a), identify those portions of the aileron control cables that move around the pulleys and:
(a) disconnect either end of each aileron cable to provide sufficient slack to conduct the inspections, or
(b) remove the aileron cables per manufacturer's instructions to conduct the inspections.
2. Inspect those portions of the aileron cables that move around the pulleys as follows:
(a) Rotate the cable so that the cable tends to untwist and simultaneously simulate the curvature of the cable over the pulley and check for fraying and broken outer and inner cable strands.
C) Prior to further flight replace aileron control cables showing fraying or broken strands that are discovered during any inspections required by this AD.
D) Upon accumulation of 500 hours' time in service and at 500 hour intervals thereafter, replace all aileron control cables.
Amendment 39-1697 became effective August 7, 1973.
This Amendment 39-1807 becomes effective April 9, 1974.
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2011-10-14: We are superseding an existing airworthiness directive (AD) that applies to 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:
On two occurrences on Myst[egrave]re-Falcon 50 aeroplanes in service, it was detected that two pipes of the emergency brake system 2 located near the nose landing gear bearing were swapped.
The swapping of these two pipes implies that when the Left Hand (LH) brake pedal is depressed, the Right Hand (RH) brake unit is activated, and conversely, when the RH brake pedal is depressed, the LH brake unit is actuated. This constitutes an unsafe condition, which may go unnoticed as the condition is latent until the emergency brake system 2 is used. This condition, if not corrected, could ultimately lead to a runway excursion of the aeroplane.
* * * * *
We are issuing this AD to require actions to correct the unsafe condition on these products.
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70-05-02: 70-05-02 BRITISH AIRCRAFT CORPORATION: Amdt. 39-946. Applies to Viscount Models 744, 745D, and 810 series airplanes.
Compliance is required as indicated, unless already accomplished.
To prevent burn-through of aluminum piping, accomplish the following:
(a) For Viscount Models 744 and 745D airplanes, within the next 600 hours' time in service after the effective date of this AD replace the aluminum engine breather pipes located between the firewall and drains collector box with stainless steel pipes in accordance with British Aircraft Corporation Bulletin for Modification No. D.3226, dated March 17, 1969, or later ARB- approved issue or an FAA-approved equivalent.
(b) For Viscount Model 810 series airplanes, within the next 600 hours' time in service after the effective date of this AD, replace the aluminum engine breather pipes located between the firewall and drains collector box and the engine accessory gearbox aluminum breather pipe which connects into the engine breather piping, with stainless steel pipes in accordance with British Aircraft Corporation Bulletin for Modification No. FG.2102, dated March 17, 1969, or later ARB-approved issue or an FAA-approved equivalent.
This amendment becomes effective March 23, 1970.
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