Airworthiness Directive · Amendment 39-17652 · Landing gear
Embraer S.A. Airplanes
Superseded. A later AD replaced this one: AD 2014-19-01. Comply with the one in force.
This AD applies to Embraer S.A. Models EMB-505 airplanes, all serial numbers, that are:
(1) Equipped with a part number (P/N) DAP00097-01 or P/N DAP00097-02 brake assembly; and
(2) certificated in any category.
We are adopting a new airworthiness directive (AD) for Embraer S.A. Model EMB-505 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracking in the stator pressure plate of the brake assembly, which may lead to loss of brake parts on the runway and reduced brake capability with possible runway excursion. We are issuing this AD to require actions to address the unsafe condition on these products.
Unless already done, do the following actions in paragraphs (f)(1) through (f)(9) of this AD, including all subparagraphs.
(1) If the number of cycles is unknown, calculate the compliance times of cycles in this AD by using hours time-in-service (TIS). Multiply the number of hours TIS on the brake assembly by.71 to come up with the number of cycles. For the purposes of this AD some examples are below:
(i) 500 hours TIS equates to 355 cycles; and
(ii) 12 hours equates to 9 cycles.
(2) Do a general visual inspection (GVI) for cracks in the stator pressure plate on both the left hand (LH) and right hand (RH) brake assemblies following the Accomplishment Instructions in Embraer Phenom Alert Service Bulletin No. 505-32-A011, dated September 13, 2013. Use the compliance times in paragraphs (f)(2)(i) and (f)(2)(ii):
(i) For brake assemblies with 300 flight cycles or less since new or since the last overhaul: Before or upon accumulating 150 flight cycles or within the next 30 flight cycles, whichever occurs later, and repetitively thereafter at intervals not to exceed 60 flight cycles or the next tire change, whichever occurs first.
(ii) For brake assemblies with more than 300 flight cycles since new or since the last overhaul: Within the next 10 flight cycles and repetitively thereafter at intervals not to exceed 60 flight cycles or the next tire change, whichever occurs first.
(3) If no cracks are found during any of the inspections required in paragraph (f)(2) of this AD, continue the repetitive inspection intervals required in paragraph (f)(2) of this AD, including all subparagraphs.
(4) If during any of the inspections required in paragraph (f)(2) of this AD, including all subparagraphs, any crack is found in the stator pressure plate, before further flight, do a detailed inspection (DET) following the Accomplishment Instructions in Embraer Phenom Alert Service Bulletin No. 505-32-A011, dated September 13, 2013.
(5) If no cracks beyond the acceptable limits are found during the DET required in paragraph (f)(4) of this AD, continue the repetitive inspection intervals required in paragraph (f)(2) in this AD, including all subparagraphs.
(6) If cracks that exceed the acceptable limits are found during the DET required in paragraph (f)(4) of this AD, before further flight, repair the brake assembly following Appendix 2 of Embraer Phenom Alert Service Bulletin No. 505-32-A011, dated September 13, 2013; or replace the brake assembly with a brake assembly that has been inspected and found free of cracks that exceed the acceptable limits following the Accomplish Instructions of Embraer Phenom Alert Service Bulletin No. 505-32-A011, dated September 13, 2013. After repair or replacement of the brake assembly, the brake assembly is subject to the inspections required in paragraphs (f)(2), including all subparagraphs, of this AD.
Note 1 to paragraph (f)(6) of this AD: Appendix 2 of Embraer Phenom Alert Service Bulletin No. 505-32-A011, dated September 13, 2013, includes Meggitt Aircraft Braking System Service Bulletin No. SB-32-1625, dated September 13, 2013.
(7) For the purposes of this AD, a GVI is a visual examination of an interior or exterior area, installation or assembly, to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance, unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or drop-light. It may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.
(8) For the purposes of this AD, a DET is an intensive examination of a specific item, installation or assembly, to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate access procedures may be required.
(9) After the effective the date of this AD, do not install on any airplane a brake assembly P/N DAP00097-01 or P/N DAP00097-02 unless it is inspected per the requirements of this AD and continues to be crack free or the cracks do not exceed the allowable limits.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
