AD 98-24-06

This amendment adopts a new airworthiness directive (AD) that applies to all Dornier-Werke G.m.b.H. (Dornier) Model Do 27 Q-6 airplanes. This AD requires repetitively inspecting the rivets that attach the forward stabilizer attach fitting to the airplane fuselage for looseness, and replacing any loose rivets. 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 the stabilizer from detaching at the forward stabilizer attach flanges because of loose rivets, which could result in reduced or loss of control of the airplane.

Final rule.

98-24-06 DORNIER-WERKE G.M.B.H.: Amendment 39-10892; Docket No. 97-CE-137-AD.

Applicability: Model Do 27 Q-6 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 the stabilizer from detaching at the forward stabilizer attach flanges because of loose rivets, which could result in reduced or loss of control of the airplane, accomplish the following:

(a) Within the next 3 calendar months after the effective date of this AD, and thereafter at intervals not to exceed 100 hours time-in-service (TIS), inspect the rivets that attach the forward stabilizer attach fitting to the airplane fuselage for looseness. Accomplish these inspections in accordance with the PROCEDURE section of Dornier Service Bulletin (SB) No. 1140-0000, Date of Issue: September 29, 1995.

(b) If loose rivets are found during any inspection required in paragraph (a) of this AD, prior to further flight, replace any loose rivets in accordance with the PROCEDURE section of Dornier SB No. 1140-0000, Date of Issue: September 29, 1995.

(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 initial or repetitive 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 Dornier Service Bulletin No. 1140-0000, Date of Issue: September 29, 1995, should be directed to Daimler-Benz Aerospace, Dornier, Product Support, P.O. Box 1103, D-82230 Wessling, Federal Republic of Germany; telephone: (08153) 300; facsimile: (08153) 302985. 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 and replacement required by this AD shall be done in accordance with Dornier Service Bulletin No. 1140-0000, Date of Issue: September 29, 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 Daimler-Benz Aerospace, Dornier, Product Support, P.O. Box 1103, D-82230 Wessling, 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 96-271 Daimler-Benz Aerospace/Dornier,Effective Date: October 10, 1996.

(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 Dornier Model Do 27 Q-6 airplanes was published in the Federal Register as a notice of proposed rulemaking (NPRM) on September 14, 1998 (63 FR 49048). The NPRM proposed to require repetitively inspecting the rivets that attach the forward stabilizer attach fitting to the airplane fuselage for looseness, and replacing any loose rivets. Accomplishment of the proposed action as specified in the NPRM would be required in accordance with Dornier Service Bulletin No. 1140-0000, Date of Issue: September 29, 1995.

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.

Compliance Time of this AD

The initial compliance time of this AD is presented in calendar time in order to assure that any rivets that are already loose are detected and corrected in a timely manner. The FAA has determined that 3 calendar months is a reasonable time for all owners/operators of the affected airplanes to comply with the initial inspection and possible replacement specified in this AD.

The repetitive inspection interval is at 100 hours time-in-service (TIS). After examining the information related to this subject, the FAA has determined that the rivets should not become loose within 100 hours TIS if they were not found loose or replaced during the last inspection. This will not put an undue burden on low usage airplanes of having to repetitively inspect every 3 calendar months if the airplanes had been rarely or never utilized.

Cost Impact

The FAA estimates that 13 airplanes in the U.S. registry will be affected by the initial 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 initial inspection on U.S. operators is estimated to be $780, or $60 per airplane. These figures only take into account the costs of the initial inspection and do not take into account the costs of any repetitive inspections. The FAA has no way of determining the number of repetitive inspections each owner/operator will incur over the life of the affected airplanes.

If loose rivets are found and replacement is necessary, the FAA estimates that it will take approximately 8 workhours per airplane to accomplish the replacement, and that the average labor rate is approximately $60 an hour. Replacement rivets will be supplied by Dornier at no cost to the owners/operators of the affected airplanes. Based on these figures, the cost impact of the replacement on U.S. operators is estimated to be $480 per airplane where loose rivets are found.

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 FederalismAssessment.

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: