- Effective
- May 11, 2004
- Published
- April 6, 2004 · 69 FR 17905–17906
- Issued
- March 25, 2004
- Models
- CN-235, CN-235-100, CN-235-200, CN-235-300
- Data sheet
- TCDSA21NM
- Registered aircraft
- 11 matched by model
- Product
- Aircraft · Large airplane
- Amendment
- 39-13560
- Docket
- 2002-NM-160-AD
- Issued as
- Final rule
Unofficial copy from the Federal Register XML, document 04-7353. 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 | 151 KB | 2ec03c43…f393c4e | 04-7353.pdf on govinfo.gov |
| Federal Register XML | 11 KB | 23677499…f9623f6 | 04-7353.xml on federalregister.gov |
| FAA DRS HTML attachment | 39 KB | fd49f5d8…2650319 | FAA DRS (API key needed) |
| FAA DRS PDF | 28 KB | d9b794c7…eeed1f0 | FAA DRS (API key needed) |
On this page
Summary
This amendment adopts a new airworthiness directive (AD), applicable to certain CASA Model C-235 series airplanes, that requires modification of the electrical wiring of the rudder trim control unit. This action is necessary to prevent the flight crew from being able to inhibit the aural warning for the landing gear up. If the flight crew of the next flight or possibly of the same flight is unaware that the aural warning had been disabled, they could inadvertently land the airplane with the landing gear not down and locked. This action is intended to address the identified unsafe condition.
The airworthiness directive
2004-07016 Construcciones Aeronauticas, S.A. (CASA): Amendment 39-13560. Docket 2002-NM-160-AD.
Applicability: Model C-235 series airplanes, serial numbers C-006, C-007, C-010, C-012, C-018, C-029, C-030, C-032, C-033, and C-042; certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To prevent the flight crew from being able to inhibit the aural warning for the landing gear up, and the possibility that the flight crew of the next flight or possibly of the same flight could inadvertently land the airplane with the landing gear not down and locked; accomplish the following:
(a) Modification
PDF page 1(a) Within 6 months after the effective date of this AD, modify the electrical wiring of the rudder trim control unit per the Accomplishment Instructions of CASA Service Bulletin SB-235-27-20, dated March 7, 2001.
(b) Alternative Methods of Compliance
PDF page 1(b) In accordance with 14 CFR 39.19, the Manager, International Branch, FAA, Transport Airplane Directorate, is authorized to approve alternative methods of compliance for this AD.
(c) Alternative Methods of Compliance
PDF page 1(c) In accordance with 14 CFR 39.19, the Manager, International Branch, FAA, Transport Airplane Directorate, is authorized to approve alternative methods of compliance for this AD.
(d) Incorporation by Reference
PDF page 2(d) The actions must be done in accordance with CASA Service Bulletin SB-235-27-20, dated March 7, 2001. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Construcciones Aeronauticas, S.A., Getafe, Madrid, Spain. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
Note 1:
The subject of this AD is addressed in Spanish airworthiness directive 02/02, dated April 30, 2002.
(e) Effective Date
PDF page 2(e) This amendment becomes effective on May 11, 2004.
Rule preamble
The FAA’s background, reasoning and cost estimate, published with the AD.
DatesPage 1
Effective May 11, 2004.
The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of May 11, 2004.
AddressesPage 1
The service information referenced in this AD may be obtained from Construcciones Aeronauticas, S.A., Getafe, Madrid, Spain. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
For further information contactPage 1
Dan Rodina, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2125; fax (425) 227-1149.
Supplementary informationPage 1
A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain CASA Model C-235 series airplanes was published in the Federal Register on February 6, 2004 (69 FR 5780). That action proposed to require modification of the electrical wiring of the rudder trim control unit.
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.
Cost impactPage 1
The FAA estimates that 1 airplane of U.S. registry will be affected by this AD, that it will take approximately 7 work hours per airplane to accomplish the required actions, and that the average labor rate is $65 per work hour. Required parts will cost approximately $40 per airplane. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $495.
The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions.
Regulatory impactPage 1
The regulations adopted herein 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. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132.
For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption ADDRESSES.
Adoption of the amendmentPage 1
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:
1. The authority citation for part 39 continues to read as follows:
2. Section 39.13 is amended 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 · 11
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1990 | 1 |
|---|---|
| 1991 | 1 |
| 1998 | 1 |
| 2002 | 1 |
| 2004 | 3 |
| 2007 | 2 |
| 2008 | 1 |
| 2009 | 1 |