Airworthiness Directive · Amendment 39-13783 · Bombardier Model DHC-8-311 Airplanes
Bombardier Model DHC-8-311 Airplanes
This AD applies to Model DHC-8-311 airplanes, serial numbers 202 through 298 inclusive, certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-311 airplanes. This AD requires reviewing the airplane maintenance records to determine if you did the most recent bonding integrity inspection according to a certain revision of the Maintenance Program Support Manual (PSM), and doing related investigative and corrective actions if necessary. This AD is prompted by the discovery that a certain revision of the PSM omits several fuselage skin panels from a list of skin panels that must be inspected. We are issuing this AD to prevent disbonding of the subject skin panels, which could reduce the load-carrying capacity of the skin panels and 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.
Within 14 days after the effective date of this AD, review the airplane maintenance records or maintenance logbook to determine if the most recent bonding integrity inspection of the fuselage skin panels was done according to Bombardier Maintenance Program Support Manual (PSM) 1-83-7A, Revision 6, dated January 30, 2001.
(1) If it can conclusively be determined that the most recent bonding integrity inspection of the fuselage skin panels was done according to PSM 1-83-7A, Revision 5, dated April 30, 1999; or Revision 7, dated August 15, 2001: This AD requires no further action.
(2) If the most recent bonding integrity inspection of the fuselage skin panels was done according to PSM 1-83-7A, Revision 6, dated January 30, 2001, or if it cannot be conclusively determined what revision of PSM 1-83-7A was used: At the applicable compliance time specified in paragraph (f)(2)(i) or (f)(2)(ii) of this AD, do a resonance frequency inspection of the fuselage skin panels listed in Table 1 of this AD, according to a method approved by either the Manager, New York Aircraft Certification Office (ACO), FAA; or Transport Canada Civil Aviation (TCCA) (or its delegated agent). PSM 1-83-7A, Revision 7, dated August 15, 2001, is one approved method.
(i) If no disbonding was found during any previous bonding integrity inspection: Within 1,000 flight hours or 6 months after the effective date of this AD, whichever is first.
(ii) If any disbonding was found during any previous bonding integrity inspection: Within 6 weeks after the effective date of this AD.
| Engineering drawing | Skin panel description | PSM 1-83-7A figure sheet |
|---|---|---|
| 85330204 | Skin, Right Side, Bottom | Figure 4/(Sheet 2). |
| 85330201 | Skin, Right Side | Figure 4/(Sheet 5). |
| 85330180 | Skin, Right Side, Top | Figure 4/(Sheet 6). |
| 85330181 | Skin, Left Side, Top | Figure 4/(Sheet 7). |
| 85330106 | Skin, Left Side, Bottom | Figure 4/(Sheet 14). |
| 85330105 | Skin, Left Side | Figure 4/(Sheet 15). |
| 85330101 | Skin, Left Side, Bottom | Figure 4/(Sheet 16). |
| 85330033 | Skin, Bottom | Figure 4/(Sheet 17). |
| 85330032 | Skin, Right Side, Lower | Figure 4/(Sheet 18). |
| 85330032 | Skin, Right Side, Lower with Service Door | Figure 4/(Sheet 19). |
| 85330031 | Skin, Left Side, Lower | Figure 4/(Sheet 20). |
| 85332750 | Skin, Bottom, Center | Figure 4/(Sheet 25). |
| 85332750 | Skin, Bottom, Center | Figure 4/(Sheet 26). |
If any disbonding is found during the resonance frequency inspection required by paragraph (f) of this AD: Before further flight, repair per a method approved by the Manager, New York ACO; or TCCA (or its delegated agent).
As of the effective date of this AD, no person may use PSM 1-83-7A, Revision 6, dated January 30, 2001, to inspect for disbonding of fuselage skin panels on any airplane having any serial number 202 through 298 inclusive.
