- Effective
- October 12, 2004
- Published
- September 7, 2004 · 69 FR 53999–54000
- Issued
- August 25, 2004
- Model
- DHC-8-311
- Data sheet
- TCDSA13NM
- Registered aircraft
- 3 matched by model
- Product
- Aircraft · Large airplane
- Amendment
- 39-13783
- Docket
- FAA-2004-18563
- Project
- 2002-NM-98-AD
- Issued as
- Final rule
Unofficial copy from the Federal Register XML, document 04-20204. Only the govinfo PDF is the legal edition. DRS record last changed May 30, 2024.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
| File | Size | SHA-256 | Original |
|---|---|---|---|
| Official PDF | 147 KB | 0c7230c7…6de4e8b | 04-20204.pdf on govinfo.gov |
| Federal Register XML | 17 KB | 7a66f752…3125cc4 | 04-20204.xml on federalregister.gov |
| FAA DRS HTML attachment | 48 KB | ab652420…cf0f0c1 | FAA DRS (API key needed) |
| FAA DRS PDF | 30 KB | bc07491c…fbe7a79 | FAA DRS (API key needed) |
On this page
Summary
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.
The airworthiness directive
2004-18-05 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment 39-13783. Docket No. FAA-2004-18563; Directorate Identifier 2002-NM-98-AD.
(a) Effective Date
PDF page 1(a) This airworthiness directive (AD) becomes effective October 12, 2004.
(b) Affected ADs
PDF page 1(b) None.
(c) Applicability
PDF page 2(c) This AD applies to Model DHC-8-311 airplanes, serial numbers 202 through 298 inclusive, certificated in any category.
(d) Unsafe Condition
PDF page 2(d) This AD was prompted by the discovery that a certain revision of the Maintenance Program Support Manual (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.
(e) Compliance
PDF page 2(e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
(f) Review of Maintenance Records
PDF page 2(f) 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). |
(g) Repair
PDF page 2(g) 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).
(h) Limitation on Future Inspections
PDF page 2(h) 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.
(i) Alternative Methods of Compliance (AMOCs)
PDF page 2(i) The Manager, New York ACO, has the authority to approve AMOCs for this AD, if an AMOC is requested in accordance with the procedures found in 14 CFR 39.19.
(j) Related Information
PDF page 2(j) Canadian airworthiness directive CF-2002-08, dated January 25, 2002, also addresses the subject of this AD.
Rule preamble
The FAA’s background, reasoning and cost estimate, published with the AD.
DatesPage 1
This AD becomes effective October 12, 2004.
AddressesPage 1
You can examine the contents of this AD docket on the Internet at http://dms.dot.gov, or at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW, room PL-401, on the plaza level of the Nassif Building, Washington, DC.
For further information contactPage 1
Technical information: Jon Hjelm, Aerospace Engineer, Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Westbury, New York 11590; telephone (516) 228-7323; fax (516) 794-5531.
Plain language information: Marcia Walters, marcia.walters@faa.gov.
The AD docket contains the proposed AD, comments, and any final disposition. You can examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647-5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section.
Supplementary informationPage 1
The FAA proposed to amend 14 CFR Part 39 with an AD for certain Bombardier Model DHC-8-311 airplanes. The proposed AD was published in the Federal Register on July 8, 2004 (69 FR 41213), to require 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.
CommentsPage 1
We provided the public the opportunity to participate in the development of this AD. No comments have been submitted on the proposed AD or on the determination of the cost to the public.
ConclusionPage 1
We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed.
Costs of CompliancePage 1
This AD will affect about 8 airplanes of U.S. registry. The records review will take about 1 work hour per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the proposed AD for U.S. operators is $520, or $65 per airplane.
Regulatory findingsPage 1
We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a “significant regulatory action” under Executive Order 12866;
(2) Is not a “significant rule” under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to comply with this AD. See the ADDRESSES section for a location to examine the regulatory evaluation.
Adoption of the amendmentPage 1
Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:
1. The authority citation for part 39 continues to read as follows:
2. The FAA amends § 39.13 by adding the following new airworthiness directive:
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 3
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.