- Effective
- December 31, 1996
- Published
- November 26, 1996 · 61 FR 60018–60019
- Models
- ATR72-101, ATR72-102, ATR72-201, ATR72-202, ATR72-211, ATR72-212, ATR72-212A
- Data sheet
- TCDSA53EU
- Registered aircraft
- 32 matched by model
- Product
- Aircraft · Large airplane
- Amendment
- 39-9836
- Docket
- 96-NM-140-AD
- Issued as
- Final rule
Unofficial copy of the text in the FAA’s Dynamic Regulatory System. 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 | 116 KB | 79ab3f4a…0263e35 | 96-29989.pdf on govinfo.gov |
| FAA DRS HTML | 41 KB | 32e5062c…a1202f2 | FAA DRS (API key needed) |
| Federal Register text | 9 KB | fe42c396…41c5c9d | 96-29989.txt on federalregister.gov |
On this page
Summary
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR72 series airplanes, that requires modification of the pitch uncoupling mechanism of both elevators. This amendment is prompted by reports of fatigue cracking of the pitch uncoupling mechanism and the torque tube of the elevator. Failure of the pitch uncoupling mechanism due to fatigue cracking could result in the uncommanded uncoupling of the elevators. The actions specified by this AD are intended to prevent such fatigue cracking and subsequent uncommanded uncoupling of the elevators, which could result in reduced controllability of the airplane.
The airworthiness directive
96-24-12 AEROSPATIALE: Amendment 39-9836. Docket 96-NM-140-AD.
Applicability: Model ATR72-101, -102, -201, -202, -211, and -212 series airplanes on which Modification 4495 or Aerospatiale Service Bulletin ATR 72-27-1044 has not been accomplished; certificated in any category.
NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
Compliance: Required as indicated, unless accomplished previously.
To prevent uncoupling of the elevators due to failure of the elevator coupling mechanism and resultant reduced controllability of the airplane, accomplish the following:
(a) Prior to the accumulation of 12,000 total landings, or within 1,000 landings after the effective date of this AD, whichever occurs later: Modify the elevator uncoupling mechanism in accordance with Aerospatiale Service Bulletin ATR72-27-1044, dated March 5, 1996.
(b) As of the effective date of this AD, no person shall install a pitch uncoupling mechanism of the elevator, having the following part numbers, on any airplane:
S2738194100800 S2738194102895 S2738194102200 S2738194102400 S2738194102800 S2738194103200
(c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113.
NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113.
(d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.
(e) The modification shall be done in accordance with Aerospatiale Service Bulletin ATR72-27-1044, dated March 5, 1996. 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. 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.
(f) This amendment becomes effective on December 31, 1996.
Rule preamble
The FAA’s background, reasoning and cost estimate, published with the AD.
Supplementary information
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 Aerospatiale Model ATR72 series airplanes was published in the Federal Register on August 19, 1996 (61 FR 42825). That action proposed to require modification of the elevator uncoupling mechanism.
Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were submitted in response to the proposal or the FAA's determination of the cost to the public.
Conclusion The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.
Cost Impact The FAA estimates that 51 Aerospatiale Model ATR72 series airplanes of U.S. registry will be affected by this AD, that it will take approximately 55 work hours per airplane to accomplish the required actions, and that the average labor rate is $60 per work hour.The required parts will be provided by the manufacturer at no cost to the operator. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $168,300, or $3,300 per airplane.
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.
Regulatory Impact The regulations adopted herein will not have substantial direct effects 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, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.
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."
List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment 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: PART 39 - AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority:49 U.S.C. 106(g), 40113, 44701. 39.13 - [Amended] 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 · 32
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1991 | 3 |
|---|---|
| 1993 | 1 |
| 1994 | 1 |
| 2012 | 1 |
| 2013 | 1 |
| 2021 | 3 |
| 2022 | 2 |
| 2023 | 5 |
| 2026 | 1 |
14 with no year recorded