Airworthiness Directive · Amendment 39-15797 · Wings
BAE Systems (Operations) Limited (Jetstream) Model 4101 Airplanes
This AD applies to BAE Systems (Operations) Limited Model Jetstream 4101 airplanes, certificated in any category; constructor's numbers 41004 through 41096 inclusive and 41102 through 41104 inclusive.
The FAA is superseding an existing airworthiness directive (AD) that applies to certain British Aerospace (Jetstream) Model 4100 series airplanes. The existing AD currently requires an eddy current conductivity test to measure the conductivity of the upper splice plate of the wing, and related investigative and corrective actions if necessary. This AD revises the applicability to include additional airplanes. This AD results from reports of exfoliation corrosion of the upper splice plate of the wing. We are issuing this AD to detect and correct such corrosion, which could result in reduced structural integrity of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
For airplanes with constructor's numbers 41004 through 41096 inclusive: Within 6 months after September 23, 1998 (the effective date of AD 98-17-12), perform an eddy current conductivity test to measure the conductivity of the upper splice plate of the wing, in accordance with British Aerospace Regional Aircraft Service Bulletin J41-57-019, Revision 1, dated November 26, 1997. If the conductivity measurement is greater than or equal to 35.0% of the International Aluminum and Copper Standards (IACS), no further action is required by this AD.
(h) During the inspection required by paragraph (g) of this AD, if the conductivity measurement is less than 35.0% of the IACS: Prior to further flight, use a borescope to perform a detailed visual inspection to detect corrosion along the full length of the upper splice plate of the wing, in accordance with British Aerospace Regional Aircraft Service Bulletin J41-57-020, dated March 20, 1997; or BAE Systems (Operations) Limited Service Bulletin J41-57-020, Revision 1, dated July 3, 2006. Thereafter, repeat the inspection at intervals not to exceed 1 year.
(1) During any inspection required by paragraph (g) of this AD, if any corrosion is detected that is within the allowable limits specified in British Aerospace Regional Aircraft Service Bulletin J41-57-020, dated March 20, 1997; or BAE Systems (Operations) Limited Service Bulletin J41-57-020, Revision 1, dated July 3, 2006: Accomplish the actions required by paragraphs (h)(1)(i) and (h)(1)(ii) of this AD, at the times specified in those paragraphs.
(i) Prior to further flight, repair the upper splice plate of the wing in accordance with Appendix 2 of British Aerospace Regional Aircraft Service Bulletin J41-57-020, dated March 20, 1997; or BAE Systems (Operations) Limited Service Bulletin J41-57-020, Revision 1, dated July 3, 2006. And
(ii) Within 3 years after the detection of corrosion, replace the upper splice plate of the wing with a new upper splice plate in accordance with the applicable service bulletin identified in Table 1 of this AD. Such replacement constitutes terminating action for the requirements of this AD.
| Service bulletin | Revision level | Date |
|---|---|---|
| British Aerospace Regional Aircraft Service Bulletin J41-57-020 | Original | March 20, 1997. |
| BAE Systems (Operations) Limited Service Bulletin J41-57-020 | 1 | July 3, 2006. |
| British Aerospace Regional Aircraft Service Bulletin J41-57-021 | Original | May 7, 1998. |
| BAE Systems (Operations) Limited Service Bulletin J41-57-021 | 4 | January 16, 2003. |
(2) During any inspection required by paragraph (h) of this AD, if any corrosion is detected that is outside the allowable limits specified in British Aerospace Regional Aircraft Service Bulletin J41-57-020, dated March 20, 1997; or BAE Systems (Operations) Limited Service Bulletin J41-57-020, Revision 1, dated July 3, 2006: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate.
(i) Replacement of the upper splice plate is also acceptable for compliance with the requirements of paragraph (h)(1)(ii) of this AD, if done before the effective date of this AD in accordance with any service bulletin identified in Table 2 of this AD.
| BAE Systems (operations) limited service bulletin | Revision level | Date |
|---|---|---|
| J41-57-021 | 1 | May 26, 2000. |
| J41-57-021 | 2 | November 2, 2001. |
| J41-57-021 | 3 | August 9, 2002. |
(j) For airplanes with construction numbers 41102 through 41104 inclusive: Do the actions specified in paragraph (g) of this AD within 6 months after the effective date of this AD, in accordance with British Aerospace Regional Aircraft Service Bulletin J41-57-019, Revision 1, dated November 26, 1997. And do all applicable actions at the applicable times as specified in paragraph (h) of this AD.
