Airworthiness Directive · Amendment 39-17969 · Landing gear
Embraer S.A. Airplanes
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 superseding an airworthiness directive (AD) 2013-22-20 for Embraer S.A. Model EMB-505 airplanes. 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 cracks beyond acceptable limits in the carbon discs of the left hand (LH) and right hand (RH) brake assemblies. 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)(14) of this AD, including all subparagraphs.
(1) If the number of flight cycles is unknown, calculate the compliance times for flight cycles in this AD by multiplying the number of hours time-in-service (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 flight cycles; and
(ii) 12 hours equates to 9 flight cycles.
(2) Do a general visual inspection (GVI) for cracks in the stator pressure plate on both the LH and RH brake assemblies following Part 1 of the Accomplishment Instructions in Embraer Phenom Service Bulletin No. 505-32-0011, Revision 01, dated March 31, 2014. Use the compliance times in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD:
(i) For brake assemblies with 300 flight cycles or less since new or since the last overhaul: Before or upon accumulating 150 flight cycles after October 22, 2014 (the effective date of this AD) or within the next 30 flight cycles after October 22, 2014 (the effective date of this AD), 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 after October 22, 2014 (the effective date of this AD), 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 any crack is found in the stator pressure plate during any of the inspections required in paragraph (f)(2) of this AD, before further flight, do a detailed inspection (DET) following Part 1 of the Accomplishment Instructions in Embraer Phenom Service Bulletin No. 505-32-0011, Revision 01, dated March 31, 2014.
(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) of 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 Service Bulletin No. 505-32-0011, Revision 01, dated March 31, 2014; 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 Accomplishment Instructions of Embraer Phenom Service Bulletin No. 505-32-0011, Revision 01, dated March 31, 2014.
Note 1 to paragraph (f)(6) of this AD: Appendix 2 of Embraer Phenom Service Bulletin No. 505-32-0011, Revision 01, dated March 31, 2014, consists of Meggitt Aircraft Braking System Service Bulletin No. SB-32-1625, Revision A, dated October 17, 2013. This service bulletin is incorporated as pages 27 through 40 of Embraer Phenom Service Bulletin No. 505-32-0011, Revision 01, dated March 31, 2014.
(7) At the next tire change or 30 days after October 22, 2014 (the effective date of this AD), whichever occurs later, do a DET for cracks on the external visible surface of the thrust stator, double stator, and rotors following Part 2 of the Accomplishment Instructions in Embraer Phenom Service Bulletin No. 505-32-0011, Revision 01, dated March 31, 2014.
(8) If no crack is detected or if any crack within the acceptable limits shown in Figure 4 Detail G of Embraer Phenom Service Bulletin No. 505-32-0011, Revision 01, dated March 31, 2014, is detected in the inspection required in paragraph (f)(7) of this AD, repeat the inspection required by paragraph (f)(7) of this AD at each tire change or at each maintenance action that requires wheel removal, whichever occurs first.
(9) If any crack within the acceptable limits shown in Figure 4 Detail H of Embraer Phenom Service Bulletin No. 505-32-0011, Revision 01, dated March 31, 2014, is detected in the inspection required in paragraph (f)(7) of this AD, the affected brake assembly must be replaced within 40 flight cycles.
(10) If any crack beyond the acceptable limits shown in Figure 4 Detail H of Embraer Phenom Service Bulletin No. 505-32-0011, Revision 01, dated March 31, 2014, is detected, the affected brake assembly must be replaced before the next flight.
(11) After any repair or replacement of the brake assembly, the brake assembly P/N DAP00097-01 or P/N DAP00097-02 is subject to the inspections required in paragraphs (f)(2) through (f)(10), including all subparagraphs as applicable, of this AD.
(12) 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.
(13) 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.
(14) As of November 8, 2013 (the effective the date of AD 2013-22-20) and to October 22, 2014 (the effective 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 AD 2013-22-20 and continues to be crack free or the cracks do not exceed the allowable limits; and as of October 22, 2014 (the effective 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.
This AD provides credit for the inspections required in paragraphs (f)(2) and (f)(6) of this AD, if those actions were performed before October 22, 2014 (the effective date of this AD), using Embraer Alert Service Bulletin (ASB) 505-32-A011, original issue, dated September 13, 2013; Embraer Alert Service Bulletin (ASB) 505-32-A011, Revision 01, dated November 01, 2013; Embraer Alert Service Bulletin (ASB) 505-32-A011, Revision 02, dated December 19, 2013; or Embraer Phenom Service Bulletin No. 505-32-0011, original issue, dated February 11, 2014.
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
