Airworthiness Directive · Amendment 39-16795 · Wings
328 Support Services GmbH (Type Certificate Previously Held by AvCraft Aerospace GmbH; Fairchild Dornier GmbH; Dornier Luftfahrt GmbH) Model 328-100 and -300 Airplanes
This AD applies to 328 Support Services GmbH (Type Certificate previously held by AvCraft Aerospace GmbH; Fairchild Dornier GmbH; Dornier Luftfahrt GmbH) Model 328-100 and -300 airplanes; all serial numbers; certificated in any category.
We are superseding an existing airworthiness directive (AD) that applies to the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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:
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Within 10 flight cycles, or 10 flight hours, or 7 days, whichever occurs first after June 3, 2008 (the effective date of AD 2008-10-51 (73 FR 30752, May 29, 2008)): Accomplish a detailed visual inspection of both the left-hand (LH) and right-hand (RH) lower wing panel inboard and outboard of flap lever arm 1 (rib 5) for cracks, in accordance with the Accomplishment Instructions of Dornier Alert Service Bulletin ASB-328J-57-015 or ASB-328-57-037, both Revision 1, both dated May 8, 2008, as applicable; or 328 Support Services Alert Service Bulletin ASB-328J-57-015 or ASB-328-57-037, both Revision 2, both dated May 20, 2008, as applicable. After the effective date of this AD, use only 328 Support Services Alert Service Bulletin ASB-328J-57-015 or ASB-328-57-037, both Revision 2, both dated May 20, 2008, as applicable. If no crack is detected, repeat the detailed visual inspection thereafter at intervals not to exceed 50 flight hours. If any crack is detected, before further flight, do an eddy current inspection, in accordance with Dornier Alert Service Bulletin ASB-328J-57-015 or ASB-328-57-037, both Revision 1, both dated May 8, 2008, as applicable; or 328 Support Services Alert Service Bulletin ASB-328J-57-015 or ASB-328-57-037, both Revision 2, both dated May 20, 2008, as applicable.
Except as required by paragraph (g) of this AD, within 400 flight hours or 3 months after June 3, 2008, whichever occurs first: Accomplish an eddy current inspection for cracking of both the LH and RH lower wing panel in the vicinity of rib 3 and inboard and outboard of flap lever arm 1 (rib 5), in accordance with the Accomplishment Instructions of Dornier Alert Service Bulletin ASB-328J-57-015 or ASB-328-57-037, both Revision 1, both dated May 8, 2008, as applicable; or 328 Support Services Alert Service Bulletin ASB-328J-57-015 or ASB-328-57-037, both Revision 2, both dated May 20, 2008, as applicable. After the effective date of this AD, use only 328 Support Services Alert Service Bulletin ASB-328J-57-015 or ASB-328-57-037, both Revision 2, both dated May 20, 2008, as applicable. Accomplishment of the eddy current inspection terminates the detailed visual inspection required by paragraph (g) of this AD.
(i) Within 1,500 flight cycles after the most recent eddy current inspection done in accordance with the applicable service bulletin listed in table 1 of this AD, or within 60 days after the effective date of this AD, whichever occurs later, do an eddy current inspection for cracking of the lower wing panel (outside) around the flap lever arm 1 (rib 5), in accordance with the Accomplishment Instructions of 328 Support Services Alert Service Bulletin ASB-328-57-037 (for Model 328-100 airplanes) or ASB-328J-57-015 (for Model 328-300 airplanes), both Revision 2, both dated May 20, 2008. Repeat the inspection thereafter at intervals not to exceed 1,500 flight cycles, except as provided by paragraph (k) of this AD.
| Service Bulletin | Revision | Date |
|---|---|---|
| Dornier Alert Service Bulletin ASB-328-57-037 | 1 | May 8, 2008. |
| Dornier Alert Service Bulletin ASB-328J-57-015 | 1 | May 8, 2008. |
| 328 Support Services Alert Service Bulletin ASB-328-57-037 | 2 | May 20, 2008. |
| 328 Support Services Alert Service Bulletin ASB-328J-57-015 | 2 | May 20, 2008. |
Within 24 months after the effective date of this AD, do an eddy current inspection for cracking of the lower wing panel (outside) around the flap lever arm 1 (rib 5). If no cracking is found, within 24 months after the effective date of this AD, modify the lower wing panel by doing a cold expansion of the CAMLOC holes and installing new attachment material from rib 9 LH to rib 9 RH. Do all actions required by this paragraph in accordance with the Accomplishment Instructions of 328 Support Services Service Bulletin SB-328-57-481 (for Model 328-100 airplanes) or SB-328J-57-230 (for Model 328-300 airplanes), both Revision 1, both dated October 15, 2009.
(k) After the modification required by paragraph (j) is done, do the eddy current inspection required by paragraph (i) of this AD at the applicable time specified in paragraph (k)(1) or (k)(2) of this AD. Repeat the inspections thereafter at the intervals specified in paragraph (i) of this AD.
(1) For Model 328-100 airplanes: Within 25,000 flight cycles after accomplishing the modification specified in paragraph (j) of this AD.
(2) For Model 328-300 airplanes: Within 20,000 flight cycles after accomplishing the modification specified in paragraph (j) of this AD.
If any cracking is found during any inspection required by this AD, before further flight contact 328 Support Services GmbH for repair instructions and do the repair using a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or European Aviation Safety Agency (EASA) (or its delegated agent).
Inspections accomplished before the effective date of this AD according to Dornier Alert Service Bulletin ASB-328-57-037 or Dornier Alert Service Bulletin ASB-328J-57-015, both Revision 1, both dated May 8, 2008, as applicable, are considered acceptable for compliance with the inspection requirements of paragraphs (i) and (j) of this AD.
At the applicable times specified in paragraphs (n)(1) and (n)(2) of this AD: Send 328 Support Services GmbH a report of findings (both positive and negative) found during each inspection required by paragraphs (g), (h), (i), and (j) of this AD. The report must include the inspection results, a description of any cracks found, the airplane serial number, and the number of landings and flight hours on the airplane. Send the report to 328 Support Services GmbH, Global Support Center, P.O. Box 1252, D-82231 Wessling, Federal Republic of Germany; Telephone +49 8153 88111 6666; fax +49 8153 88111 6565; e-mail: gsc.op@328support.de.
(1) For any inspection done on or after the effective date of this AD: Within 30 days after the inspection.
(2) For any inspection done before the effective date of this AD: Within 30 days after the effective date of this AD.
Note 1: This AD differs from the MCAI and/or service information as follows: EASA Airworthiness Directive 2009-0194R1, dated March 10, 2011, corrected March 22, 2011, gives credit for eddy current inspections conducted in accordance with the maintenance review board tasks. We are not giving credit for those inspections.
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.
