Airworthiness directives: und Raumfahrt,

[Federal Register: September 11, 1998 (Volume 63, Number 176)]

[Proposed Rules]

[Page 48653-48655]

From the Federal Register Online via GPO Access [wais.access.gpo.gov]

[DOCID:fr11se98-30]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-CE-68-AD]

RIN 2120-AA64

Airworthiness Directives; Burkhart Grob Luft-und Raumfahrt Models G115, G115A, G115B, G115C, G115C2, G115D, and G115D2 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

SUMMARY: This document proposes to adopt a new airworthiness directive (AD) that would apply to all Burkhart Grob Luft-und Raumfahrt (Grob) Models G115, G115A, G115B, G115C, G115C2, G115D, and G115D2 airplanes. The proposed AD would 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. The proposed AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by the proposed 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.

DATES: Comments must be received on or before October 15, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), Central Region, Office of the Regional Counsel, Attention: Rules Docket No. 98-CE-68-

[[Page 48654]]

AD, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. Comments may be inspected at this location between 8 a.m. and 4 p.m., Monday through Friday, holidays excepted.

Service information that applies to the proposed AD may be obtained from Burkhart Grob Luft-und Raumfahrt, D-8939 Mattsies, Federal Republic of Germany. This information also may be examined at the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr. Karl M. Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 1201 Walnut, suite 900, Kansas City, Missouri 64106; telephone: (816) 426-6932; facsimile: (816) 426-2169.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to participate in the making of the proposed rule by submitting such written data, views, or arguments as they may desire. Communications should identify the Rules Docket number and be submitted in triplicate to the address specified above. All communications received on or before the closing date for comments, specified above, will be considered before taking action on the proposed rule. The proposals contained in this notice may be changed in light of the comments received.

Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the proposed rule. All comments submitted will be available, both before and after the closing date for comments, in the Rules Docket for examination by interested persons. A report that summarizes each FAA-public contact concerned with the substance of this proposal will be filedin the Rules Docket.

Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this notice must submit a self-addressed, stamped postcard on which the following statement is made: ``Comments to Docket No. 98-CE-68-AD.'' The postcard will be date stamped and returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this NPRM by submitting a request to the FAA, Central Region, Office of the Regional Counsel, Attention: Rules Docket No. 98-CE-68-AD, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.

Discussion

The Luftfahrt-Bundesamt (LBA), which is the airworthiness authority for Germany, recently notified the FAA that an unsafe condition may exist on all Grob Models G115, G115A, G115B, G115C, G115C2, G115D, and G115D2 airplanes. The LBA reports incidents of cracks found in the area of the trim tab hinges on the affected airplanes. The LBA states that the cracks could be forming due to the trim tab end touching the upper elevator shell at full deflection. This would indicate a loose or non- secure fit of the trim tab hinges.

This condition, if not detected and corrected, could result in trim tab failure with consequent loss of control of the airplane.

Relevant Service Information

Grob has issued Service Bulletin 1078-75, dated May 15, 1998, which specifies procedures for inspecting the area of the elevator trim tab hinges for cracks and a secure fit. Included with this service bulletin are Installation Instructions No. 1078-75, dated May 15, 1998, which specify procedures for repairing any elevator trim tab hinges with cracks or where a proper secure fit is not found.

The LBA of Germany classified this service bulletin as mandatory and issued German AD 1998-299, dated June 4, 1998, in order to assure the continued airworthiness of these airplanes in Germany.

The FAA's Determination

These airplane models are manufactured in Germany and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the LBA of Germany has kept the FAA informed of the situation described above.

The FAA has examined the findings of the LBA; reviewed all available information, including the service information referenced above; and determined that AD action is necessary for products of this type design that are certificated for operation in the United States.

Explanation of the Provisions of the Proposed AD

Since an unsafe condition has been identified that is likely to exist or develop in other Grob Models G115, G115A, G115B, G115C, G115C2, G115D, and G115D2 airplanes of the same type design registered in the United States, the FAA is proposing AD action. The proposed AD would 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 in accordance with Grob Service Bulletin 1078-75, dated May 15, 1998. Accomplishment of the proposed repairs, if necessary, would be accomplished in accordance with Grob Installation Instructions No. 1078-75, dated May 15, 1998.

Cost Impact

The FAA estimates that 26 airplanes in the U.S. registry would be affected by the proposed inspection, that it would take approximately 1 workhour per airplane to accomplish the proposed inspection, and that the average labor rate is approximately $60 an hour. Based on these figures, the total cost impact of the proposed inspection on U.S. operators is estimated to be $1,560, or $60 per airplane.

If any of the affected airplanes would have trim tab hinges that were found cracked or where a proper secure fit was not found, the proposed repair would take approximately 5 workhours per airplane at an average labor rate of $60 per hour. Parts would 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, would be approximately $325 per airplane.

Regulatory Impact

The regulations proposed herein would 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 proposal would 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) if promulgated, 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 draft regulatory evaluation prepared for this action has been placed in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the

[[Page 48655]]

location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 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.

    Sec. 39.13 [Amended]

  2. Section 39.13 is amended by adding a new airworthiness directive (AD) to read as follows:

    Burkhart Grob Luft-und Raumfahrt: Docket No. 98-CE-68-AD.

    Applicability: Model 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 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, 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.

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

    Issued in Kansas City, Missouri, on September 3, 1998. Michael Gallagher, Manager, Small Airplane Directorate, Aircraft Certification Service.

    [FR Doc. 98-24383Filed9-10-98; 8:45 am]

    BILLING CODE 4910-13-P

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