AD 98-24-08

This amendment adopts a new airworthiness directive (AD) that applies to all Burkhart Grob Luft-und Raumfahrt (Grob) Models G115, G115A, G115B, G115C, G115C2, G115D, and G115D2 airplanes. This AD requires inspecting the area of the elevator trim tab hinges for cracks and a secure fit, and repairing any elevator trim tab hinges with cracks or where a proper secure fit is not found. 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 structural damage of the trim tab hinges caused by cracks, which could result in trim tab failure with consequent loss of control of the airplane.

Final rule.

98-24-08 BURKHART GROB LUFT-UND RAUMFAHRT: Amendment 39-10894; Docket No. 98-CE-68-AD.

Applicability: Models G115, G115A, G115B, G115C, G115C2, G115D, and G115D2 airplanes, all serial numbers, 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 structural damage of the trim tab hinges caused by cracks, which could result in trim tab failure with consequent loss of control of the airplane, accomplish the following:

(a) Within the next 50 hours time-in-service (TIS) after the effective date of this AD, inspect the area of the elevator trim tab hinges for cracks and a secure fit. Accomplish this inspection in accordance with the Action section of Grob Service Bulletin No. 1078-75, dated May 15, 1998.

(b) Prior to further flight, repair any elevator trim tab hinges with cracks or where a proper secure fit is not found. Accomplish these repairs in accordance with the Procedure section of Grob Installation Instructions No. 1078-75, dated May 15, 1998.

(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 locationwhere 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, 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 2: 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 Grob Service Bulletin 1078-75, dated May 15, 1998, should be directed to Burkhart Grob Luft-und Raumfahrt, D-8939 Mattsies, Federal Republic of Germany. 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.(f) The inspection required by this AD shall be done in accordance with Grob Service Bulletin 1078-75, dated May 15, 1998. The repair required by this AD shall be done in accordance with Grob Installation Instructions No. 1078-75, dated May 15, 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 Burkhart Grob Luft-und Raumfahrt, D-8939 Mattsies, 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 of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC.

NOTE 3: The subject of this AD is addressed in German AD 1998-299, dated June 4, 1998.

(g) This amendment becomes effective on December 28, 1998.

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 all Grob Models G115, G115A, G115B, G115C, G115C2, G115D, and G115D2 airplanes was published in the Federal Register as a notice of proposed rulemaking (NPRM) on September 11, 1998 (63 FR 48653). The NPRM proposed to require inspecting the area of the elevator trim tab hinges for cracks and a secure fit, and repairing any elevator trim tab hinges with cracks or where a proper secure fit is not found. Accomplishment of the proposed inspection would be required in accordance with Grob Service Bulletin 1078-75, dated May 15, 1998. Accomplishment of the proposed repairs, if necessary, would be required in accordance with Grob Installation Instructions No. 1078-75, dated May 15, 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 26 airplanes in the U.S. registry will be affected by the inspection, that it will take approximately 1 workhour per airplane to accomplish the inspection, and that the average labor rate is approximately $60 an hour. Based on these figures, the total cost impact of the inspection on U.S. operators is estimated to be $1,560, or $60 per airplane.

If any of the affected airplanes have trim tab hinges that are found cracked or where a proper secure fit was not found, the repair will take approximately 5 workhours per airplane at an average labor rate of $60 per hour. Parts will cost approximately $25 per airplane. Based on these figures, the cost to repair any trim tab hinges found cracked, or where a proper secure fit was not found, will be approximately $325 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 preparation of a Federalism Assessment.

For the reasons discussed above, Icertify 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: