AD 98-07-19

Airworthiness directive · Tail Rotor Control Rod Assembly · MD Helicopters 369F and 369FF

Effective
May 7, 1998
Published
April 2, 1998 · 63 FR 16109–16110
Models
369F, 369FF
Data sheet
TCDSH3WE
Registered aircraft
118 matched by model
Product
Aircraft · Rotorcraft
Amendment
39-10440
Docket
97-SW-03-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.

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Summary

This amendment adopts a new airworthiness directive (AD), applicable to McDonnell Douglas Helicopter Systems (MDHS) Model 369F and 369FF helicopters, that requires removing the tail rotor control rod assembly (rod assembly) and replacing it with an airworthy rod assembly. This amendment is prompted by a failure of a rod assembly during a proof-load test conducted by the manufacturer. The actions specified by this AD are intended to prevent buckling of the rod assembly when subjected to ultimate jam loads, loss of tail rotor control, and subsequent loss of control of the helicopter.

The airworthiness directive

98-07-19 MCDONNELL DOUGLAS HELICOPTER SYSTEMS: Amendment 39-10440. Docket No. 97-SW-03-AD.

Applicability: Model 369F and 369FF helicopters, certificated in any category.

NOTE 1: This AD applies to each helicopter 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 helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (b) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any helicopter from the applicability of this AD.

Compliance: Required within 300 hours time-in-service after the effective date of this AD, unless accomplished previously.

To prevent buckling of the tail rotor control rod assembly (rod assembly) when subjected to ultimate jam loads, loss of tail rotor control, and subsequent loss of control of the helicopter, accomplish the following:

(a) Remove the rod assembly, part number (P/N) 369D27516, and replace it with an airworthy rod assembly, P/N 369D27516-5. Replacement of the rod assembly with an airworthy rod assembly, P/N 369D27516-5, constitutes a terminating action for the requirements of this AD.

(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, Los Angeles Aircraft Certification Office. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles Aircraft Certification Office.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles 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 helicopter to a location where the requirements of this AD can be accomplished.

(d) This amendment becomes effective on May 7, 1998.

Rule preamble

The FAA’s background, reasoning and cost estimate, published with the AD.

Supplementary information

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to MDHS Model 369F and 369FF helicopters was published in the Federal Register on August 20, 1997 (62 FR 44245). That action proposed to require removing the rod assembly and replacing it with an airworthy rod assembly.

Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposal or the FAA's determination of the cost to the public. The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.

The FAA estimates that 17 helicopters of U.S. registry will be affected by this AD, that it will take approximately 4 work hours per helicopter to accomplish the required actions, and that the average labor rate is $60 per work hour. Based on these figures, the total cost impact of theAD on U.S. operators is estimated to be $4,080.

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 final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket maintained in the Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, 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 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 · 118

Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.

By aircraft maker
  • MD Helicopters94 aircraft
  • Mcdonnell Douglas Heli17 aircraft
  • Hughes Helicopters5 aircraft
  • Hughes2 aircraft
By year built
19842026
Registered aircraft by year built: 89 aircraft
19842
19852
19872
19883
19894
19902
19911
19922
19945
19961
19981
19992
20006
20012
20063
20072
20084
20098
20101
20111
20123
20131
20153
20161
20172
20194
20203
20223
20236
20248
20261

29 with no year recorded

By model

Aircraft

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