2009-26-02 Empresa Brasileira de Aeronautica S.A. (EMBRAER): Amendment 39-16137. Docket No. FAA-2007-0083; Directorate Identifier 2006-NM-266-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective January 19, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to EMBRAER Model EMB-135BJ, -135ER, -135KE, -135KL, -135LR, -145, -145ER, -145MR, -145LR, -145XR, -145MP, and - 145EP airplanes, certificated in any category, except airplanes having serial numbers 14500921, 14500928, 14500932, 14500949, 14500958, 14500971, 14500973 and up, which will have in-factory modification incorporated.
Subject
(d) Air Transport Association of America Code 30: Ice and Rain Protection.
Reason
(e) The mandatory continuing airworthiness information (MCAI) states:
It has been found the occurrence of engine anti-ice system valve failure, where the valve spring seat has broken and obstructed the anti-ice system venturi tube. Aircraft dispatch with that failure may be allowed by the operator Minimum Equipment List (MEL), [if] the engine anti-ice system valve [is] locked in the OPEN position. However, there is no readily available means to make sure the anti- ice system tubing is free of debris, allowing unrestricted hot airflow to the piccolo tube on the engine inlet lip. Therefore, should the aircraft encounter icing conditions, ice may accrete in the engine inlet lip and be ingested through the air inlet, resulting in possible engine damage and flame-out.
The required actions include an inspection to determine the part number of the engine anti-icing system valves; repetitive inspections of certain engine anti-icing system valves and tubes to detect damage, and replacement of the valves if damage is found; and eventual replacement of certain anti-icing system valves.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) PART I--Within 500 flight hours or 3 months after the effective date of this AD, whichever occurs first, carry out a general visual inspection of both LH (left-hand) and RH (right-hand) engine anti-ice system valves to determine their P/N (part number).
(i) For engine anti-ice system valves with P/N C146009-2: No further action is required by paragraph (f)(1) of this AD.
(ii) For engine anti-ice system valves with P/N C146009-3: Before further flight, remove the valve and carry out a detailed inspection regarding its integrity; and carry out a special detailed inspection for an obstruction in the corresponding engine anti-ice system tubes; according to the detailed instructions and procedures described in Embraer Service Bulletin 145-30-0049, dated June 28, 2006, or Revision 01, dated October 19, 2006; or Embraer Service Bulletin 145LEG-30-0016, dated June 28, 2006, or Revision 01, dated February 5, 2007; as applicable.
(A) If the valve is damaged or the tube is obstructed, before further flight: Replace the valve with a serviceable or new valve bearing P/N C146009-2, C146009-3, or C146009-4; or remove all obstructions; as applicable; in accordance with the Accomplishment Instructions of Embraer Service Bulletin 145-30-0049, dated June 28, 2006, or Revision 01, dated October 19, 2006; or Embraer Service Bulletin 145LEG-30-0016, dated June 28, 2006, or Revision 01, dated February 5, 2007; as applicable.
(B) If the valve is not damaged or the tube is not obstructed, re-install the valve or install a serviceable or new valve bearing P/N C146009-2, C146009-3, or C146009-4; or re-install the tube; in accordance with the Accomplishment Instructions of Embraer Service Bulletin 145-30-0049, dated June 28, 2006, or Revision 01, dated October 19, 2006; or Embraer Service Bulletin 145LEG-30-0016, dated June 28, 2006, or Revision 01, dated February 5, 2007; as applicable.
(iii) For engine anti-ice system valves with P/N C146009-4: No further action is required by paragraph (f)(1) of this AD. In this case, paragraphs (f)(2), (f)(3), (f)(4), (f)(7), and (f)(8) of this AD are not applicable. However, paragraphs (f)(5) and (f)(6) of this AD must be accomplished.
(2) PART II--Within 1,500 flight hours or 9 months after the effective date of this AD, whichever occurs first, and thereafter at intervals that do not exceed 1,000 flight hours or 6 months, whichever occurs first, carry out a detailed inspection for damage of both LH and RH engine anti-ice system valves bearing P/N C146009- 2 or C146009-3; and a special detailed inspection for obstruction of the corresponding engine anti-ice system tubes; according to the detailed instructions and procedures described in Embraer Service Bulletin 145-30-0049, dated June 28, 2006, or Revision 01, dated October 19, 2006; or Embraer Service Bulletin 145LEG-30-0016, dated June 28, 2006, or Revision 01, dated February 5, 2007; as applicable; and accomplish paragraphs (f)(2)(i) and (f)(2)(ii) of this AD, as applicable.
(i) If the valve is damaged or the tube is obstructed, before further flight: Replace the valve with a serviceable or new valve bearing P/N C146009-2, C146009-3, or C146009-4; or remove all obstructions; as applicable; in accordance with the Accomplishment Instructions of Embraer Service Bulletin 145-30-0049, dated June 28, 2006, or Revision 01, dated October 19, 2006; or Embraer Service Bulletin 145LEG-30-0016, dated June 28, 2006, or Revision 01, dated February 5, 2007; as applicable.
(ii) If the valve is not damaged, or the tube is not obstructed, before further flight: Re-install the valve or install a serviceable or new valve bearing P/N C146009-2 C146009-3, or C146009-4; or re- install the tube; as applicable; in accordance with the Accomplishment Instructions of Embraer Service Bulletin 145-30-0049, dated June 28, 2006, or Revision 01, dated October 19, 2006; or Embraer Service Bulletin 145LEG-30-0016, dated June 28, 2006, or Revision 01, dated February 5, 2007; as applicable.
(3) PART III--Any engine anti-ice system valve with P/N C146009- 2 or C146009-3 that will be installed as a replacement, as provided for in paragraphs (f)(1) and (f)(2) of this AD, must undergo a detailed inspection for its integrity before installation, according to the detailed instructions and procedures described in Embraer Service Bulletin 145-30-0049, dated June 28, 2006, or Revision 01, dated October 19, 2006; or Embraer Service Bulletin 145LEG-30-0016, dated June 28, 2006, or Revision 01, dated February 5, 2007; as applicable; and additionally adhere to paragraphs (f)(3)(i) and (f)(3)(ii) of this AD, as applicable.
(i) If the valve is damaged, replace it with a serviceable or new valve bearing P/N C146009-2, C146009-3, or C146009-4; in accordance with the Accomplishment Instructions of Embraer Service Bulletin 145-30-0049, dated June 28, 2006, or Revision 01, dated October 19, 2006; or Embraer Service Bulletin 145LEG-30-0016, dated June 28, 2006, or Revision 01, dated February 5, 2007; as applicable.
(ii) If the valve is not damaged, installation is permitted.
(4) PART IV--Any engine anti-ice system tubes that will be installed on the airplane as a replacement, as provided for in paragraphs (f)(1) and (f)(2) of this AD, must undergo a special detailed inspection before installation, and all obstructions removed, according to the detailed instructions and procedures described in Embraer Service Bulletin 145-30-0049, dated June 28, 2006, or Revision 01, dated October 19, 2006; or Embraer Service Bulletin 145LEG-30-0016, dated June 28, 2006, or Revision 01, dated February 5, 2007; as applicable.
(5) PART V--If any engine anti-ice system valve with P/N C146009-4 has been found during the inspection required by paragraph (f)(1) of this AD, do paragraphs (f)(5)(i) or (f)(5)(ii) of this AD, as applicable, within 500 flight hours or 6 months after the effective date of this AD, whichever occurs first.
(i) If the valve was installed according to the detailed instructions and procedures described in Embraer Service Bulletin 145-30-0044, Revision 01, dated June 26, 2006, Revision 02, dated September 25, 2006, Revision 03, dated December 12, 2006, or Revision 04, dated May 14, 2008; or Embraer Service Bulletin 145LEG- 30-0018, Revision 02, dated December 12, 2006, or Revision 03, dated May 14, 2008; as applicable: No further action is required by this AD.
(ii) If the valve was installed according to detailed instructions and procedures other than those specified in paragraph (f)(5)(i) of this AD: Carry out a special detailed inspection in the corresponding engine anti-ice system tubes, and repair all damage and remove all obstructions; according to the detailed instructions and procedures described in Embraer Service Bulletin 145-30-0049, dated June 28, 2006, or Revision 01, dated October 19, 2006; or Embraer Service Bulletin 145LEG-30-0016, dated June 28, 2006, or Revision 01, dated February 5, 2007; as applicable. After doing the actions specified in paragraph (f)(5)(ii) of this AD, no further action is required by this AD.
(6) PART VI--Before aircraft dispatch with one or two engine anti-ice system valves inoperative (Master Minimum Equipment List (MMEL) 30-21-01), carry out a detailed inspection for damage of the affected engine anti-ice system valves; and a special detailed inspection for obstruction of the corresponding engine anti-ice system tubes; and replace all damaged valves and remove all obstructions before further flight. Do all actions according to the detailed instructions and procedures described in Embraer Service Bulletin 145-30-0049, dated June 28, 2006, or Revision 01, dated October 19, 2006; or Embraer Service Bulletin 145LEG-30-0016, dated
June 28, 2006, or Revision 01, dated February 5, 2007; as applicable; by accomplishing paragraph (f)(2) of this AD, unless the condition specified in paragraph (f)(6)(i) or (f)(6)(ii) of this AD has been met.
(i) Valves with P/N C146009-4 have been previously installed accordingto the detailed instructions and procedures described in Embraer Service Bulletin 145-30-0044, dated October 31, 2005; Embraer Service Bulletin 145LEG-30-0018, dated June 26, 2006; or Embraer Service Bulletin 145LEG-30-0018, Revision 01, dated September 25, 2006; as applicable; and additionally, paragraph (f)(5)(ii) of this AD has been accomplished.
(ii) Valves with P/N C146009-4 have been previously installed according to the detailed instructions and procedures described in Embraer Service Bulletin 145-30-0044, Revision 01, dated June 26, 2006, Revision 02, dated September 25, 2006, Revision 03, dated December 12, 2006, or Revision 04, dated May 14, 2008; or Embraer Service Bulletin 145LEG-30-0018, Revision 02, dated December 12, 2006, or Revision 03, dated May 14, 2008; as applicable.
(7) PART VII--Within 1,000 flight hours or 10 months after the effective date of this AD, whichever occurs first, install engine anti-ice system valves bearing P/N C146009-4 in the LH and RH engine positions, replacing P/N C146009-3, according to the detailed instructions and procedures described in Embraer Service Bulletin 145-30-0044, Revision 01, dated June 26, 2006, Revision 02, dated September 25, 2006, Revision 03, dated December 12, 2006, or Revision 04, dated May 14, 2008; or Embraer Service Bulletin 145LEG- 30-0018, Revision 02, dated December 12, 2006, or Revision 03, dated May 14, 2008; as applicable.
(8) PART VIII--Within 1,000 flight hours or 10 months after the effective date of this AD, whichever occurs first, install engine anti-ice system valves bearing P/N C146009-4 in the LH and RH engine positions, replacing P/N C146009-2, according to the detailed instructions and procedures described in Embraer Service Bulletin 145-30-0044, Revision 01, dated June 26, 2006; Revision 02, dated September 25, 2006, Revision 03, dated December 12, 2006, or Revision 04, dated May 14, 2008; or Embraer Service Bulletin 145LEG- 30-0018, Revision 02, dated December 12, 2006, or Revision 03, dated May 14, 2008; as applicable.
(9) PART IX--The installation of engine anti-ice system valves bearing P/N C146009-4 according to the detailed instructions and procedures described in Embraer Service Bulletin 145-30-0044, Revision 01, dated June 26, 2006, Revision 02, dated September 25, 2006, Revision 03, dated December 12, 2006; or Revision 04, dated May 14, 2008; or Embraer Service Bulletin 145LEG-30-0018, Revision 02, dated December 12, 2006, or Revision 03, dated May 14, 2008; as applicable; constitutes terminating action for this AD.
Note 1: For the purposes of this AD, a general visual inspection 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 ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and 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.''
Note 2: For the purposes of this AD, a detailed inspection 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 mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.''
Note 3: For the purposes of this AD, a special detailed inspection is: ``An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. The examination is likely to make extensive use of specialized inspection techniques and/or equipment. Intricate cleaning and substantial access or disassembly procedure may be required.''
FAA AD Differences
Note 4: This AD differs from the MCAI and/or service information as follows (we have coordinated these differences with Agencia Nacional de Aviacao Civil (ANAC)):
(1) ``Part V'' of the MCAI specifies a compliance time of within ``1,500 flight hours or 9 months.'' However, paragraph (f)(5) of this AD requires compliance ``within 500 flight hours or 6 months'' for the corresponding action.
(2) ``Part VII'' of the MCAI specifies a compliance time of ``within 2,500 flight hours or 12 months.'' However, paragraph (f)(7) of this AD requires compliance ``within 1,000 flight hours or 10 months'' for the corresponding action.
(3) ``Part VIII'' of the MCAI specifies a compliance time of ``within 6,000 flight hours or 30 months.'' However, paragraph (f)(8) of this AD requires compliance ``within 1,000 flight hours or 10 months'' for the corresponding action.
Other FAA AD Provisions(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, ANM- 116, International Branch, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1405; fax (425) 227-1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office.
(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120-0056.
Related Information
(h) Refer to Brazilian Airworthiness Directive 2006-09-03R1, effective January 4, 2007; and the service bulletins listed in Table 1 of this AD; for related information.
Table 1--Related Service Bulletins
Embraer Service Bulletin
Revision
Dated
145-30-0044
01
June 26, 2006
145-30-0044
02
September 25, 2006
145-30-0044
03
December 12, 2006
145-30-0044
04
May 14, 2008
145-30-0049
Original
June 28, 2006
145-30-0049
01
October 19, 2006
145LEG-30-0016
Original
June 28, 2006
145LEG-30-0016
01
February 5, 2007
145LEG-30-0018
02
December 12, 2006
145LEG-30-0018
03
May 14, 2008
Material Incorporated by Reference
(i) You must use the applicable service information contained in Table 2 of this AD to do the actions required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact Empresa Brasileira de Aeronautica S.A. (EMBRAER), Technical Publications Section (PC 060), Av. Brigadeiro Faria Lima, 2170-- Putim--12227-901 Sao Jose dos Campos--SP--BRASIL; telephone: +55 12 3927-5852 or +55 12 3309-0732; fax: +55 12 3927-7546; e-mail: distrib@embraer.com.br; Internet: http://www.flyembraer.com.
(3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For informationon the availability of this material at the FAA, call 425-227-1221 or 425-227-1152.
(4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http:// www.archives.gov/federal_register/code_of_federal_regulations/ ibr_locations.html.
Table 2--Material Incorporated by Reference
Embraer Service Bulletin
Revision
Dated
145LEG-30-0016
Original
June 28, 2006
145LEG-30-0016
01
February 5, 2007
145LEG-30-0018
02
December 12, 2006
145LEG-30-0018
03
May 14, 2008
145-30-0044
01
June 26, 2006
145-30-0044
02
September 25, 2006
145-30-0044
03
December 12, 2006
145-30-0044
04
May 14, 2008
145-30-0049
Original
June 28, 2006
145-30-0049
01
October 19, 2006