AD 2009-23-08

Required as indicated, unless accomplished previously.

For Model ERJ 170-100 LR, -100 STD, -100 SE, -100 SU, -200 LR, -200 STD, and -200 SU airplanes; and ERJ 190-100 STD, -100 LR, and -100 IGW airplanes: As of 24 hours after May 7, 2007 (the effective date of AD 2007-06-53), before each flight after closing the cargo doors, verify that the forward and aft cargo doors are closed flush with the fuselage skin, and that all 4 latched and locked indicators at the bottom of each door are green. Persons qualified to do this verification are mechanics and flightcrew members. If it cannot be verified that both doors are closed flush with the fuselage skin, and that all 4 latched and locked indicators at the bottom of each door are green, repair before further flight. Repeat the verification before every flight until accomplishment of the actions required by paragraph (h) of this AD.

For Model ERJ 170-100 LR, -100 STD, -100 SE, -100 SU, -200 LR, -200 STD, and -200 SU airplanes; and ERJ 190-100 STD, -100 LR, and -100 IGW airplanes: Within 10 days after May 7, 2007, do the actions specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD, in accordance with the Accomplishment Instructions of Embraer Alert Service Bulletin 170-52-A036 (for Model ERJ 170 airplanes) or 190-52-A018 (for Model ERJ 190 airplanes), both dated March 12, 2007; or Revision 01, both dated March 23, 2007; as applicable. As of the effective date of this AD, use Revision 01 of Embraer Alert Service Bulletin 170-52-A036 or 190-52-A018.

(1) Remove the roller fitting cover plate on the forward and aft cargo door frames.

(2) Perform a detailed inspection of the forward and aft cargo doors to detect signs of interference between the lock handle and the aft edge liner assembly. Then rework the aft edge liner assembly at the applicable time specified in paragraph (h)(2)(i) or (h)(2)(ii) of this AD.

(i) If any sign of interference is detected: Rework the assembly before further flight.

(ii) If no sign of interference is detected: Rework the assembly within 150 flight cycles after the inspection.

(3) Perform a detailed inspection for signs of damage of the lateral roller fitting on the forward and aft cargo door frames at the fuselage. If any damage is found, replace the lateral roller fitting before further flight with a new roller fitting having the same part number, in accordance with Embraer Alert Service Bulletin 170-52-A036 or 190-52-A018, as applicable.

(4) Actions done before May 7, 2007, in accordance with Embraer Alert Service Bulletin 170-52-A036 or 190-52-A018, both dated March 12, 2007, are acceptable for compliance with the corresponding requirements of this AD.

Note 1: 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 2: Embraer Alert Service Bulletins 170-52-A036 and 190-52-A018 refer to Embraer Service Bulletins 170-50-0006 and 190-50-0006, respectively, as additional sources of guidance for the rework and roller fitting cover plate removal. Embraer Alert Service Bulletins 170-50-0006 and 190-50-0006 are currently at Revision 01, dated March 13, 2007.

(i) For Model ERJ 170-100 LR, -100 STD, -100 SE, -100 SU, -200 LR, -200 STD, and -200 SU airplanes; and ERJ 190-100 STD, -100 LR, and -100 IGW airplanes: Repeat the inspection specified in paragraph (h)(3) of this AD at intervals not to exceed 150 flight cycles until the terminating action specified in paragraph (k)(3) of this AD has been accomplished.

For Model ERJ 170-100 LR, -100 STD, -100 SE, -100 SU, -200 LR, -200 STD, and -200 SU airplanes; and ERJ 190-100 STD, -100 LR, and -100 IGW airplanes: As of May 7, 2007, no person may install a roller fitting cover plate on the forward and aft cargo door frames on any airplane.

Unless already done, do the following actions.

(1) For Model ERJ 190-200 LR, -200 STD, and -200 IGW airplanes: As of 24 hours after the effective date of this AD, before each flight after closing the cargo doors, verify that the forward and aft cargo doors are closed flush with the fuselage skin, and that all 4 latched and locked indicators at the bottom of each door are green. Persons qualified to do this verification are mechanics and flightcrew members. If it cannot be verified that both doors are closed flush with the fuselage skin, and that all 4 latched and locked indicators at the bottom of each door are green, repair before further flight. Repeat the verification before every flight until accomplishment of the actions required by paragraph (k)(2) of this AD.

(2) For Model ERJ 190-200 LR, -200 STD, and -200 IGW airplanes: Within 10 days after the effective date of this AD, do the actions specified in paragraphs (k)(2)(i), (k)(2)(ii), and (k)(2)(iii) of this AD, in accordance with the Accomplishment Instructions of Embraer Alert Service Bulletin 190-52-A018, Revision 01, dated March 23, 2007. Repeat the inspection specified in paragraph (k)(2)(iii) of this AD at intervals not to exceed 150 flight cycles until the terminating action specified in paragraph (k)(3) of this AD has been accomplished.

(i) Remove the roller fitting cover plate on the forward and aft cargo door frames.

(ii) Perform a detailed inspection of the forward and aft cargo doors to detect signs of interference between the lock handle and the aft edge liner assembly. Then rework the aft edge liner assembly at the applicable time specified in paragraph (k)(2)(ii)(A) or (k)(2)(ii)(B) of this AD.

(A) If any sign of interference is detected: Rework the assembly before further flight.

(B) If no sign of interference is detected: Rework the assembly within 150 flight cycles after the inspection.

(iii) Perform a detailed inspection for signs of damage of the lateral roller fitting on the forward and aft cargo door frames at the fuselage. If any damage is found, replace the lateral roller fitting before further flight with a new roller fitting having the same part number, in accordance with Embraer Alert Service Bulletin 190-52-A018, Revision 01, dated March 23, 2007.

(3) For all airplanes: Within 5,000 flight cycles after the effective date of this AD, do the actions specified in paragraphs (k)(3)(i) and (k)(3)(ii) of this AD on the forward and aft cargo doors. Accomplishing the actions in this paragraph terminates the repetitive inspections required by paragraphs (i) and (k)(2) of this AD.

(i) Relocate the cargo door closed indication sensor in accordance with the Accomplishment Instructions of Embraer Service Bulletin 170-52-0041, Revision 01, dated June 13, 2008; or 190-52-0023, Revision 02, dated March 11, 2008; as applicable.

(ii) Modify the cargo door lock handle mechanism and replace the forward and aft cargo door roller fittings having part number (P/N) 170-92569-401 and 170-85452-401 with new fittings having P/N 170-92569-403 and 170-85452-403, as applicable. Do the modification in accordance with the Accomplishment Instructions of Embraer Service Bulletins 170-52-0044, dated January 18, 2008; or 190-52-0027, dated March 20, 2008; as applicable.

(4) Actions done before the effective date of this AD in accordance with Embraer Service Bulletin 170-52-0041, dated September 6, 2007; or 190-52-0023, dated September 6, 2007, or Revision 01, dated December 6, 2007; as applicable; are acceptable for compliance with the corresponding requirements of this AD.

(5) Within 12 months after the effective date of this AD or 12 months after accomplishing the modification required by paragraph (k)(3) of this AD, whichever occurs later: Incorporate information into the maintenance program to include the operational (OPC) and functional (FNC) checks of the forward and aft cargo doors; in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Agência Nacional de Aviação Civil (or its delegated agent). Within 6,000 flight hours after doing the actions required by paragraph (k)(3) of this AD, do the OPC and FNC checks and repeat the checks thereafter at intervals not to exceed 6,000 flight hours.

Note 3: Guidance on the OPC and FNC checks specified in paragraph (k)(5) of this AD can be found in the document specified in Table 1 of this AD, as applicable:

Note 4: For the purposes of this AD, a functional check (FNC) is: “A quantitative check to determine if one or more functions of an item perform within specified limits.”

Note 5: For the purposes of this AD, an operational check (OPC) is: “A task to determine if an item is fulfilling its intended purpose. Since it is a failure finding task, it does not require quantitative tolerances.”

Note 6: This AD differs from the MCAI and/or service information as follows: Where the MCAI includes a compliance time of “after accomplishment of the modification” for revising the maintenance program for Model ERJ-170 airplanes, we have determined that a compliance time of “within 12 months after the effective date of the AD or within 12 months after accomplishment of the modification, whichever occurs later” is appropriate. This compliance time is equivalent to the compliance time required for Model ERJ-190 airplanes. The manufacturer and ANAC agree with this compliance time.