- Effective
- December 28, 1998
- Published
- November 23, 1998 · 63 FR 64603–64605
- Models
- EA-300, EA-300L, EA-300S
- Data sheet
- TCDSA67EU
- Registered aircraft
- 193 matched by model
- Product
- Aircraft · Small airplane
- Amendment
- 39-10893
- Docket
- 98-CE-53-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 | 125 KB | b2d87ee4…3e316a8 | 98-31013.pdf on govinfo.gov |
| FAA DRS HTML | 54 KB | a9b2821d…56caaa4 | FAA DRS (API key needed) |
| Federal Register text | 13 KB | 4d02f4a2…84b20cb | 98-31013.txt on federalregister.gov |
On this page
Summary
This amendment adopts a new airworthiness directive (AD) that applies to certain EXTRA Flugzeugbau GmbH (EXTRA) Models EA-300, EA-300S, and EA-300L airplanes. This AD requires repetitively inspecting the rudder pedal for proper alignment, the safety control stop for wear and proper clearance, the rudder cables for elongation, and the rudder pedal footrest for cracks. This AD also requires correcting or replacing any discrepant part, as applicable. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent failure of the rudder pedal footrest caused by overloading the rudder pedal safety control stop, which could result in loss of directional control of the airplane.
The airworthiness directive
98-24-07 EXTRA FLUGZEUGBAU GMBH: Amendment 39-10893; Docket No. 98-CE-53-AD.
Applicability: The following models and serial numbers, certificated in any category:
Model Serial Number EA-300 all serial numbers, if factory equipped or retrofitted with the electric actuated rudder pedal adjustment that was produced prior to November 1995. EA-300S 001 through 028 EA-300L 001 through 015
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 (f) 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 follows:
1. Inspections specified in this AD are required within the next 50 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 50 hours TIS.
2. Replacements or other follow-on corrective actions specified in this AD are required prior to further flight after the inspection when the discrepancy was found.
To prevent failure of the rudder pedal footrest caused by overloading the rudder pedal safety control stop, which could result in loss of directional control of the airplane, accomplish the following:
(a) Inspect the rudder pedal alignment in accordance with Figure 1 and Figure 2 and the Instructions Part I.1 section of EXTRA Service Bulletin No. 300-3-95, Issue: B, dated May 12, 1998. If not aligned,prior to further flight, accomplish one of the following, as applicable, in accordance with the service bulletin:
(1) Re-rig the rudder cables to attain proper alignment; or
(2) Replace the rudder cables if alignment cannot be attained.
(b) For all airplanes equipped at manufacture with a safety control stop (See NOTE 2 of this AD), inspect the safety control stop for wear (rubbing, scrapes, etc.) in accordance with the Instructions Part I.2 section of EXTRA Service Bulletin No. 300-3-95, Issue: B, dated May 12, 1998. If the safety control stop is worn, prior to further flight, replace the safety control stop and accomplish one of the following, as applicable, in accordance with the service bulletin:
(1) Re-rig the rudder cable if elongation of the cable is not evident; or
(2) Replace the rudder cable if elongation of the cable is evident.
NOTE 2: The Model EA-300/S airplanes, serial numbers 001 through 011, were not factory equipped with a safetycontrol stop.
(c) Inspect the footrest flange in the area of the safety wire hole for cracks in accordance with the Instructions Part I.3 section of EXTRA Service Bulletin No. 300-3-95, Issue: B, dated May 12, 1998. If cracks are found, prior to further flight, replace the rudder pedal in accordance with the applicable maintenance manual or instructions obtained from the Small Airplane Directorate at the address specified in paragraph (f) of this AD.
(d) For all airplanes equipped at manufacture with a safety control stop (See NOTE 2 of this AD), inspect the safety control stop clearance in accordance with the Instructions Part I.4 and Instructions Part II section of EXTRA Service Bulletin No. 300-3-95, Issue: B, dated May 12, 1998. If the clearance does not meet the minimum specified clearance, prior to further flight, accomplish one of the following, as applicable, in accordance with the service bulletin:
(1) Adjust the foot rest to meet the required clearance ifelongation of the cable is not evident; or
(2) Replace the rudder cable if elongation of the cable is evident.
(e) 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.
(f) 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 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Small Airplane Directorate.
(g) Questions or technical information related toEXTRA Service Bulletin No. 300-3-95, Issue: B, dated May 12, 1998, should be directed to EXTRA Flugzeugbau GmbH, Flugplatz Dinslaken, D-46569 Hunxe, Federal Republic of Germany; telephone: (0 28 58) 91 37-00; facsimile: (0 28 58) 91 37-30. 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 64106.
(h) The inspections, modifications, or replacements required by this AD shall be done in accordance with EXTRA Service Bulletin No. 300-3-95, Issue: B, dated May 12, 1998. 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 EXTRA Flugzeugbau GmbH, Flugplatz Dinslaken, D-46569 Hunxe, Federal Republic of Germany. 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 ofthe Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC.
NOTE 4: The subject of this AD is addressed in German AD No. 95-443 EXTRA, dated November 29, 1995.
(i) This amendment becomes effective on December 28, 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 EXTRA Models EA-300, EA-300S, and EA-300L airplanes was published in the Federal Register as a notice of proposed rulemaking (NPRM) on September 17, 1998 (63 FR 49675). The NPRM proposed to require repetitively inspecting the rudder pedal for proper alignment, the safety control stop for wear and proper clearance, the rudder cable for proper alignment, and the rudder pedal footrest for cracks. The NPRM also proposed to require correcting or replacing any discrepant part, as applicable. Accomplishment of the proposed actions as specified in the NPRM would be required in accordance with EXTRA Service Bulletin No. 300-3-95, Issue: B, dated May 12, 1998.
The NPRM was the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany.
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 15 airplanes in the U.S. registry will be affected by this AD, that it will take approximately 4 workhours per airplane to accomplish the inspections, and that the average labor rate is approximately $60 an hour. Based on these figures, the total cost impact of this AD on U.S. operators is estimated to be $3,600, or $240 per airplane. These figures do not take into account any corrective action that will be necessary after accomplishing the inspections.
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 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 · 193
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1989 | 3 |
|---|---|
| 1990 | 2 |
| 1991 | 4 |
| 1992 | 1 |
| 1993 | 5 |
| 1994 | 6 |
| 1995 | 9 |
| 1996 | 11 |
| 1997 | 10 |
| 1998 | 15 |
| 1999 | 10 |
| 2000 | 12 |
| 2001 | 7 |
| 2002 | 9 |
| 2003 | 4 |
| 2004 | 8 |
| 2005 | 10 |
| 2006 | 11 |
| 2007 | 14 |
| 2008 | 3 |
| 2009 | 5 |
| 2010 | 1 |
| 2012 | 1 |
| 2014 | 1 |
| 2015 | 1 |
30 with no year recorded
By model
Aircraft
NTSB investigations that cite this AD · 1
Their narratives or probable cause name AD 98-24-07, often to say whether the aircraft complied with it.