- Effective
- April 3, 1998
- Published
- February 27, 1998 · 63 FR 9926–9928
- Models
- TB 10, TB 200, TB9
- Data sheet
- TCDSA51EU
- Registered aircraft
- 65 matched by model
- Product
- Aircraft · Small airplane
- Amendment
- 39-10358
- Docket
- 95-CE-70-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 | 126 KB | 99767fa4…ad64f9b | 98-4243.pdf on govinfo.gov |
| FAA DRS HTML | 59 KB | d438e8bf…704dd71 | FAA DRS (API key needed) |
| Federal Register text | 15 KB | 59fcc004…3d5f6ef | 98-4243.txt on federalregister.gov |
On this page
Summary
This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA - Groupe AEROSPATIALE (Socata) Models TB9, TB10, and TB200 airplanes. This AD requires inspecting the main landing gear (MLG) support ribs for cracks, replacing MLG support ribs that have cracks beyond a certain level, and incorporating a certain MLG support rib reinforcement kit. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent MLG failure caused by cracks in the support ribs, which could result in loss of control of the airplane during landing operations.
The airworthiness directive
98-04-47 SOCATA - GROUPE AEROSPATIALE: Amendment 39-10358; Docket No. 95-CE-70-AD.
Applicability: Models TB9, TB10, and TB200 airplanes, serial numbers 1 through 9999, certificated in any category.
NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been 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 (d) 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 in the body of this AD, unless already accomplished.
To prevent main landing gear (MLG) failure caused by cracks in the support ribs, which could result in loss of control of the airplane during landing operations, accomplish the following:
NOTE 2: The compliance times of this AD are presented in landings instead of hours time-in-service (TIS). If the number of landings is unknown, hours TIS may be used by multiplying the number of hours TIS by 1.5.
NOTE 3: The paragraph structure of this AD is as follows:
Level 1: (a), (b), (c), etc.
Level 2: (1), (2), (3), etc.
Level 3: (i), (ii), (iii), etc.
Level 2 and Level 3 structures are designations of the Level 1 paragraph they immediately follow.
(a) For TB9, serial numbers (S/N) 1 through 1442 and 1444 through 1574; and TB10, S/N 1 through 803; 805; 806; 809 through 815; 820; 821; and 822, airplanes that are not equipped with either wing rib reinforcement kit No. OPT10910800 (TB9 and TB10 airplanes) or do not have reinforced ribs (TB10 airplanes), part number (P/N) TB10 11008001 and P/N TB10 11008002, accomplish the following:
(1) Upon accumulating 1,500 landings on the MLG support ribs or within the next 75 landings after the effective date of this AD, whichever occurs later, inspect the MLG support ribs for cracks at all four locations (two per wing) in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Socata Service Bulletin No. SB 10-085, Amdt. 2, dated April 1996.
(2) If any cracks are found that are out of the tolerances specified in the maintenance manual, prior to further flight, replace the ribs with reinforced ribs, P/N TB10 11008001 and P/N TB10 11008002. Accomplish the replacement in accordance with the maintenance manual.
(3) If any cracks are found that are within the tolerances specified in the maintenance manual, prior to further flight, incorporate wing rib reinforcement kit No. OPT10 910800 in accordance with the maintenance manual.
(4) If no cracks are found, upon accumulating 3,000 landings on the MLG support ribs or within the next 100 landings after the effective date of this AD, whichever occurs later, incorporate wing rib reinforcement kit No. OPT10 910800 in accordance with the maintenance manual.
(b) For Models TB10 and TB200 airplanes, S/N 804; 807; 808; 816 through 819; 823 through 1701; 1707 through 1733; and 1737 to 1761, accomplish the following:
(1) Upon accumulating 6,000 landings on the MLG support ribs or within the next 75 landings after the effective date of this AD, whichever occurs later, inspect the MLG support ribs for cracks at all four locations (two per wing) in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Socata Service Bulletin No. SB 10-085, Amdt. 2, dated April 1996.
(2) At the applicable compliance time presented below, incorporate wing rib reinforcement kit No. OPT10 920100 in accordance with the Technical Instruction of Modification, OPT10 9201-57, Reinforcement of the Main Landing Gear Support Ribs, which incorporates the following pages:
Pages Revision Level Date 1 and 2 Amendment 1 April 1996 3 through 27 Original Issue November 1995
(i) Prior to further flight if any cracks are found.
(ii) Upon accumulating 7,500 landings on the MLG support ribs or within the next 100 landings after the effective date of this AD, whichever occurs later, if no cracks are found.
(c) 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.
(d) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Small Airplane Directorate, FAA, 1201 Walnut, suite 900, Kansas City, Missouri 64106. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Small Airplane Directorate.
NOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Small Airplane Directorate.
(e) Questions or technical information related to the service information referenced in this AD should be directed to SOCATA - Groupe AEROSPATIALE, Socata Product Support, Aeroport Tarbes-Ossun-Lourdes, B P 930, 65009 Tarbes Cedex, France; telephone: 62.41.74.26; facsimile: 62.41.74.32; or the Product Support Manager, SOCATA - Groupe AEROSPATIALE, North Perry Airport, 7501 Pembroke Road, Pembroke Pines, Florida 33023; telephone: (954) 964-6877; facsimile: (954) 964-1668. This service information may be examined at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri.
(f) The inspections required by this AD shall be done in accordance with Socata Service Bulletin No. SB 10-085, Amdt. 2, dated April 1996. The modification required by this AD should be done in accordance with the Technical Instruction of Modification, OPT10 9201-57, Reinforcement of the Main Landing Gear Support Ribs, which incorporates the following pages:
Pages Revision Level Date 1 and 2 Amendment 1 April 1996 3 through 27 Original Issue November 1995
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 SOCATA - Groupe AEROSPATIALE, Socata Product Support, Aeroport Tarbes-Ossun-Lourdes, B P 930, 65009 Tarbes Cedex, France; or the Product Support Manager, SOCATA - Groupe AEROSPATIALE, North Perry Airport, 7501 Pembroke Road, Pembroke Pines, Florida 33023. Copies may be inspected at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC.
NOTE 5: The subject of this AD is addressed in French AD 94-265(A)R4, dated June 19, 1996.
(g) This amendment (39-10358) becomes effective on April 3, 1998.
Rule preamble
The FAA’s background, reasoning and cost estimate, published with the AD.
Supplementary information
Events Leading to the Issuance of This AD A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to certain Socata Models TB9, TB10, and TB200 airplanes was published in the Federal Register as a notice of proposed rulemaking (NPRM) on December 24, 1997 (62 FR 67300). The NPRM proposed to require inspecting the MLG support ribs for cracks, replacing any MLG support ribs that have cracks beyond a certain level, and incorporating a certain MLG support rib reinforcement kit if cracks beyond a certain level are not found. Accomplishment of the proposed action as specified in the NPRM would be in accordance with Socata Service Bulletin No. SB 10-085, Amdt. 2, dated April 1996. Accomplishment of the kit modifications, as applicable, would be in accordance with either the technical instructions included with the kit or the maintenance manual.
The NPRM was the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France.
Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposed rule or the FAA's determination of the cost to the public.
The FAA's Determination After careful review of all available information related to the subject presented above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed except for minor editorial corrections. The FAA has determined that these minor corrections will not change the meaning of the AD and will not add any additional burden upon the public than was already proposed.
Cost Impact The FAA estimates that 146 airplanes in the U.S. registry will be affected by this AD, that it will take approximately 1 workhour per airplane to accomplish the required inspection, and that the average labor rate is approximately $60 an hour. Based on these figures, the total cost impact of this inspection on U.S. operators is estimated to be $8,760, or $60 per airplane.
The required modification will take approximately 1 workhour to incorporate the applicable kits on each wing (total of 2 workhours), and the average labor rate is approximately $60 per hour. Parts cost approximately $1,200 per airplane ($300 per kit; 2 kits per wing X 2 wings per airplane). Based on these figures, the total cost impact of this modification on U.S. operators is estimated to be $192,720, or $1,320 per airplane.
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 preparationof 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 copy of the final evaluation prepared for this action is contained in the Rules Docket. A copy of it may be obtained by contacting 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 a new airworthiness directive (AD) to read as follows:
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 65
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1979 | 1 |
|---|---|
| 1983 | 1 |
| 1985 | 2 |
| 1986 | 7 |
| 1987 | 1 |
| 1988 | 1 |
| 1989 | 2 |
| 1991 | 3 |
| 1992 | 1 |
| 1994 | 1 |
| 1995 | 1 |
| 2000 | 1 |
| 2002 | 1 |
| 2003 | 2 |
40 with no year recorded