61-23-01: 61-23-01 BRANTLY: Amdt. 364 Part 507 Federal Register November 3, 1961. Applies to All Model B-2 Helicopters Equipped With B2-248-53 or B2-248-53A Outboard Main Rotor Blades.
Compliance required as indicated.
As the result of bond separation between the skin and foam filler on the inboard end of the B2-248-53 and -53A main rotor blades and cracks around the root fitting in both the upper and lower skins the following inspections are required:
(a) Within the next 10 hours' time in service unless already accomplished within the last 15 hours' time in service and at the expiration of each 25 hours' time in service thereafter, inspect the upper and lower skins of the inboard end of the B2-248-53 and -53A blades as follows:
(1) Inspect for bond separation by feel or sound tests. If the skin is separated from the foam filler a sponginess will be felt or a dullness in tone will be heard when tapped with a coin. Blades with voids exceeding 12 inches in length shallbe replaced prior to further flight.
(2) Inspect for cracks between rivets in the skins with a 5-power or greater magnifying glass. If any cracks are found around two or more rivets the blade must be replaced prior to further flight.
(b) When blades are replaced they must be replaced with either B2-248-53M or B2- 248-101 blades. Brantly Service Letter No. 31A must be complied with when B2-248-101 blades are installed.
(c) In addition to the inspection interval specified in (a), the inspection required in (a)(1) also must be made prior to each flight after the initial inspection.
(d) (1) The inspections required in (a) shall be made by a person as authorized by CAR 18.11.
(2) The inspections required in (c) and appropriate log book entries thereon are hereby authorized to be made by the pilot.
(Brantly Service Letter No. 28A applies to this same subject.)
This directive effective November 4, 1961.
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2021-06-04: The FAA is adopting a new airworthiness directive (AD) for all Gulfstream Aerospace Corporation (Gulfstream) Model GV airplanes. This AD was prompted by notification of corrosion present in floor beam support links. This AD requires inspecting the right butt line 6 floor beam inboard support links and bushings for corrosion. The FAA is issuing this AD to address the unsafe condition on these products.
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2020-15-17: The FAA is adopting a new airworthiness directive (AD) for certain Sikorsky Aircraft Corporation Model S-76C helicopters. This AD was prompted by reports of inaccurate main gear box (MGB) indications in flight. This AD requires updating the remote data acquisition unit (RDAU) software and re-identifying the RDAU and, for certain helicopters, updating the software of the display unit (DU) and re- identifying the DU. The FAA is issuing this AD to address the unsafe condition on these products.
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2007-03-11: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD requires inspecting for discrepancies of the activation mechanism of certain chemical oxygen generators, and corrective action if necessary. This AD results from several incidents, on certain airplane models, of incorrect installation of the release pin into the safety pin hole of the activation mechanism of the chemical oxygen generator; this resulted in failure to activate the chemical oxygen generator when required. A separate incident occurred on a different airplane model during deployment of the cabin oxygen system, which resulted in failure of the release pin to activate the oxygen generator at a flight attendant station. We are issuing this AD to prevent failure of the activation mechanism of the chemical oxygen generator, which could result in the unavailability of supplemental oxygen and possible incapacitation of passengers and cabin crew during an in-flight decompression.
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80-16-04: 80-16-04 AIRESEARCH MANUFACTURING COMPANY OF ARIZONA: Amendment 39-3862. Applies to AiResearch TFE-731-2, -3, -3R engines manufactured prior to May 1980.
Compliance required as indicated, unless already accomplished.
To prevent separation of tie rod and potential massive engine failure, accomplish the following:
(a) Within 150 operating hours after the effective date of this AD, unless previously accomplished, compliance is required with Paragraph (c) for the following TFE-731 engines:
Model
Serial Numbers
TFE-731-2-1C
73142, 73159, 73215, 73240, 73293, 73345, 73348 thru 73361
TFE-731-2-2B
74145, 74153, 74159, 74161, 74175, 74201, 74218, 74271, 74284, 74328, 74329, 74331, 74332 thru 74336, 74339, 74341, 74342, 74344, 74348 thru 74351, 74355, 74356, 74358 thru 74362, 74375, 74431, 74448, 74821
TFE-731-3-1E
75138, 75143, 75177, 75179, 75183 thru 75186, 75190, 75191, 75192, 75214
TFE-731-3-1C
76108
TFE-731-3-1G
77166, 77167, 77174, 77176, 77177
TFE-731-3-1F/-1K
78115, 78130, 78131, 78132, 78134, 78137, 78138, 78139, 78145, 78146
TFE-731-3-1H
80107, 80118, 80121, 80176
TFE-731-2-2J
81101, 81102, 81104
(b) For all TFE-731-2, -3, -3R engines manufactured prior to May 1980, and not listed in Paragraph (a), compliance with Paragraph (c) is required at, or prior to, the next major periodic inspection (as defined in AiResearch Service Bulletin TFE-731-72-3105 or -3106), unless previously accomplished.
(c) Determine the serial number identification of the tie rod, P/N 3070065-1, installed in engines covered under Paragraphs (a) or (b). This determination can be made by reference to engine build records or by disassembly of the engine sufficient to gain access to the aft end of the tie rod. All tie rods of the following listed serial numbers must be removed from service and replaced with like serviceable parts:
6P11723
6P11747
6P11771
6P11795
6P21154
6P11724
6P11748
6P11772
6P11796
6P21155
6P11725
6P11749
6P11773
6P11797
6P21156
6P11726
6P11750
6P11774
6P11798
6P21157
6P11727
6P11751
6P11775
6P11799
6P21158
6P11728
6P11752
6P11776
6P11800
6P21159
6P11729
6P11753
6P11777
6P11801
6P21160
6P11730
6P11754
6P11778
6P11802
6P21162
6P11731
6P11755
6P11779
6P11803
6P21163
6P11732
6P11756
6P11780
6P11804
6P21164
6P11733
6P11757
6P11781
6P11805
6P21165
6P11734
6P11758
6P11782
6P11806
6P21166
6P11735
6P11759
6P11783
6P11807
6P21167
6P11736
6P11760
6P11784
6P11808
6P21168
6P11737
6P11761
6P11785
6P11809
6P21169
6P11738
6P11762
6P11786
6P11810
6P21170
6P11739
6P11763
6P11787
6P11811
6P21171
6P11740
6P11764
6P11788
6P11812
6P21172
6P11741
6P11765
6P11789
6P11813
6P21173
6P11742
6P11766
6P11790
6P11814
6P21174
6P11743
6P11767
6P11791
6P11815
6P21175
6P11744
6P11768
6P11792
6P11816
7P11849
6P11745
6P11769
6P11793
6P11817
7P11850
6P11746
6P11770
6P11794
6P11818(d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD.
(e) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region.
This amendment becomes effective August 7, 1980.
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2021-05-20: The FAA is superseding Airworthiness Directive (AD) 2018-16- 02, which applied to all Airbus SAS Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114, and -115 airplanes; Model A320-211, - 212, -214, and -216 airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes. AD 2018-16-02 required modifying and re-identifying the 3-lug aft engine mount assemblies. This AD continues to require modifying and re-identifying the 3-lug aft engine mount assemblies, and also requires modifying and re-identifying the 4-lug aft engine mount assemblies; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a report of a production quality deficiency on the inner retainer installed on link assemblies of the aft engine mount, which could result in failure of the retainer. The FAA is issuing this AD to address the unsafe condition on these products.
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2007-03-03: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires repetitive inspections to detect cracks in the vertical beam webs of the body station (BS) 178 bulkhead, and corrective actions if necessary. This AD also requires a terminating modification for the repetitive inspections. This AD results from reports of numerous cracks in the vertical beam webs. We are issuing this AD to prevent fatigue cracks in certain vertical beam webs, which could result in loss of structural integrity of the BS 178 bulkhead, and consequently could impair the operation of the control cables for the elevators, speed brakes, and landing gear, or could cause the loss of cabin pressure.
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2021-02-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model EC 155B and EC155B1 helicopters. This AD was prompted by a report that non-destructive tests of the main gearbox (MGB) housing may have been evaluated incorrectly during production. This AD requires replacing affected MGBs with serviceable MGBs, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
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2007-03-01: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757 airplanes. This AD requires inspecting certain power feeder wire bundles for damage, inspecting the support clamps for these wire bundles to determine whether the clamps are properly installed, and performing corrective actions if necessary. This AD results from a report that a power feeder wire bundle chafed against the number six auxiliary slat track, causing electrical wires in the bundle to arc, which damaged both the auxiliary slat track and power feeder wires. We are issuing this AD to prevent arcing that could be a possible ignition source for leaked flammable fluids, which could result in a fire. Arcing could also result in a loss of power from the generator connected to the power feeder wire bundle, and consequent loss of systems, which could reduce controllability of the airplane.
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2007-02-19: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-605R airplanes and Model A310-308, -324, and -325 airplanes. This AD requires modifying the Bruce floor plan electrical emergency path marking system (FPEEPMS) and, for certain airplanes, modifying the automatic switching of the emergency lighting system. This AD results from a report that in the case of vertical separation of the fuselage forward of door 1, the FPEEPMS and the exit signs do not turn on. We are issuing this AD to prevent inadequate lighting and marking of the escape path, which could delay or impede the flightcrew and passengers when exiting the airplane during an emergency landing.
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