AD 98-17-04

This amendment adopts a new airworthiness directive (AD) that is applicable to Hartzell Propeller Inc. HC-E4A-3(A,I,J) series propellers. This action requires a one-time inspection of the propeller blade counterweight clamps for thread damage in the bolt holes, and, if necessary, replacement with serviceable parts. This amendment is prompted by a report of a counterweight clamp bolt hole thread failure that resulted in the separation of the counterweight and the separation of a blade following impact with the counterweight. The actions specified in this AD are intended to prevent propeller blade counterweight clamp bolt hole thread failure, which can result in counterweight and propeller blade separation, and possible damage to the aircraft.

Final rule; request for comments.

98-17-04 Hartzell Propeller Inc.: Amendment 39-10706. Docket 98-ANE-53-AD.
Applicability: Hartzell Propeller Inc. HC-E4A-3(A,I,J) series propellers, with serial numbers (S/Ns) HJ1 through HJ1040, that have been previously overhauled or have had a counterweight clamp bolt removed for any reason. These propellers are installed on but not limited to Raytheon (Beech) 1900D series aircraft.

NOTE 1: This airworthiness directive (AD) applies to each propeller 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 propellers 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 (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair onthe 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, unless accomplished previously.

To prevent propeller blade counterweight clamp bolt hole thread failure, which can result in counterweight and propeller blade separation, and possible damage to the aircraft, accomplish the following:

(a) Perform a one-time inspection of the propeller blade counterweight clamps for thread damage in the bolt holes in accordance with the Accomplishment Instructions of Hartzell Propeller Inc. Alert Service Bulletin (ASB) No. HC-ASB-61-237, dated July 17, 1998, as follows:

(1) For propellers with 2,500 or more hours time in service (TIS) since last overhaul, inspect within 300 hours time in service (TIS), or 45 days after the effective date of this AD, whichever occurs first.

(2) For all other propellers inspect within 600 hours TIS, or 90 days after the effective date of this AD, whichever occurs first.

(3) For propeller blade counterweight clamps that do not meet the return to service criteria stated in the ASB, prior to further flight remove from service propeller blade counterweight clamps and replace and reassemble with serviceable parts in accordance with the ASB.

(4) For propeller blade counterweight clamps that meet the return to service criteria stated in the ASB, reassemble in accordance with the ASB.

(b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Chicago Aircraft Certification Office. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Chicago Aircraft Certification Office.

NOTE 2: Information concerning the existence of approved alternative methods of compliance withthis airworthiness directive, if any, may be obtained from the Chicago Aircraft Certification Office.

(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 aircraft to a location where the requirements of this AD can be accomplished.

(d) The actions required by this AD shall be done in accordance with the following Hartzell Propeller Inc. service documents:

Document No
Pages
Date
HC-ASB-61-237
1-20
July 17, 1998
Total pages: 20.

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 Hartzell Propeller Inc., One Propeller Place, Piqua, OH 45356-2634, ATTN: Product Support; telephone (937) 778-4200, fax (937) 778-4321. Copies may be inspected at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(e) This amendment becomes effective on August 31, 1998.

On May 4, 1998, a Raytheon (Beech) 1900D aircraft experienced a Hartzell Propeller Inc. HC-E4A-3(A,I,J) series propeller blade separation in Syracuse, NY. The investigation revealed that a propeller counterweight clamp bolt pulled out from the counterweight clamp assembly and the counterweight separated inflight. The departing counterweight broke the adjacent propeller blade about 12 inches from the hub. Inspection of the counterweight clamp bolt holes revealed that threads in the counterweight clamp bolt hole failed and that the threads had been damaged by cross threading. During the failure investigation, additional counterweight clamps with damaged threads were found. This condition, if not corrected, could result in propeller blade counterweight clamp bolt hole thread failure, which can result in counterweight and propeller blade separation, and possible damage to the aircraft.

The FAA has reviewed and approved the technical contents of Hartzell Propeller Inc. Alert Service Bulletin (ASB) No. HC-ASB-61-237, dated July 17, 1998, that describes procedures for inspection of the propeller blade counterweight clamps for thread damage in the bolt holes, and, if necessary, replacement with serviceable parts.

Since an unsafe condition has been identified that is likely to exist or develop on other propellers of the same type design, this AD is being issued to prevent propeller blade counterweight clamp bolt hole thread failure. This AD requires a one-time inspection of the propeller blade counterweight clamps for thread damage in the bolt holes. Based upon the results of the inspection, operators must, if necessary, replace propeller blade counterweight clamps with serviceable parts.

Since a situation exists that requires the immediate adoption of this regulation, it is found that notice and opportunity for prior public comment hereon are impracticable, and that good cause exists for making this amendment effective inless than 30 days.

Comments Invited
Although this action is in the form of a final rule that involves requirements affecting flight safety and, thus, was not preceded by notice and an opportunity for public comment, comments are invited on this rule. Interested persons are invited to comment on this 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 under the caption "ADDRESSES." All communications received on or before the closing date for comments will be considered, and this rule may be amended in light of the comments received. Factual information that supports the commenter's ideas and suggestions is extremely helpful in evaluating the effectiveness of the AD action and determining whether additional rulemaking action would be needed.

Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify the 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 AD will be filed in 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 Number 98-ANE-53-AD." The postcard will be date stamped and returned to the commenter.

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 ruledoes not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.

The FAA has determined that this regulation is an emergency regulation that must be issued immediately to correct an unsafe condition in aircraft, and is not a "significant regulatory action" under Executive Order 12866. It has been determined further that this action involves an emergency regulation under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). If it is determined that this emergency regulation otherwise would be significant under DOT Regulatory Policies and Procedures, a final regulatory evaluation will be prepared and placed in the Rules Docket. A copy of it, if filed, may be obtained from 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 tothe 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 the following new airworthiness directive: