AD 2002-13-05 R1

AD Final Rules - 021305R1.pdf
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AD Number:
2002-13-05 R1
Document Type:
AD Final Rules
Docket Number:
2001-SW-40-AD
Subject Heading:
Airworthiness Directives; MD Helicopters, Inc. Model 369D, 369E, 369F, and 369FF Helicopters
Subject:
Tail rotor gearbox
Status:
Current
Citation:
(Federal Register: January 21, 2003 (Volume 68, Number 13))
Citation Publish Date:
01/21/2003
Effective Date:
02/25/2003
Make:
MD Helicopters, Inc.
Model:
369D | 369E | 369F | 369FF
Product Type:
Aircraft
Product Subtype:
Rotorcraft
Affected AD:
Superseded AD:
2002-13-05
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
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1


[Federal Register: January 21, 2003 (Volume 68, Number 13)]


[Rules and Regulations]


[Page 2687-2689]


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


[DOCID:fr21ja03-5]


–––––––––––––––––––––––––––––––––––


DEPARTMENT OF TRANSPORTATION


Federal Aviation Administration


14 CFR Part 39


[Docket No. 2001-SW-40-AD; Amendment 39-13022; AD 2002-13-05 R1]


RIN 2120-AA64


Airworthiness Directives; MD Helicopters, Inc. Model 369D, 369E, 369F, and 369FF


Helicopters


AGENCY:
 
Federal Aviation Administration, DOT.


ACTION:
 
Final rule.


–––––––––––––––––––––––––––––––––––


SUMMARY:
 
This amendment revises an airworthiness directive (AD) for the specified MD


Helicopters, Inc. (MDHI) helicopters that currently requires identifying the part number (P/N) of the


bolts that attach the tail rotor gearbox to the tailboom and replacing any bolt of inadequate grip length


with an airworthy bolt. That AD also requires adding an additional washer if more than four threads


protrude from the nutplate. This amendment requires the same actions as the existing AD but reduces


the applicability to only certain tailboom serial numbers and parts modified in accordance with either


Supplemental Type Certificate (STC) SH5055NM or SH4801NM. This amendment also corrects a


typographical error and clarifies that a slippage mark needs to be reapplied to each bolt regardless of


the outcome of the required torque test. This amendment is prompted by the need to correct and


clarify the applicability and other portions of the existing AD. The actions specified by this AD are


intended to prevent loss of a tail rotor gearbox due to bolts of inadequate grip length and subsequent


loss of control of the helicopter.


DATES:
 
Effective February 25, 2003.


FOR FURTHER INFORMATION CONTACT:
 
John Cecil, Aviation Safety Engineer, FAA, Los


Angeles Aircraft Certification Office, Airframe Branch, 3960 Paramount Blvd., Lakewood,


California 90712-4137, telephone (562) 627-5228, fax (562) 627-5210.


SUPPLEMENTARY INFORMATION:
 
A proposal to amend 14 CFR part 39 by revising AD


2002-13-05, Amendment 39-12793 (67 FR 43227, June 27, 2002), for the specified MDHI model


helicopters with a tailboom modified according to either Aerometals STC SH5055NM or


SH4801NM, was published in the Federal Register on September 24, 2002 (67 FR 185).


Before issuing AD 2002-13-05, the FAA solicited comments by a Notice of Proposed


Rulemaking, published in the Federal Register on December 27, 2001 (66 FR 66821). A commenter


stated that the applicability of the AD should be limited to certain part-numbered tailbooms with
2


serial number (S/N) 5001-5032 specified in the FAA-approved Aerometals service bulletin. We did


not agree with the commenter and, except for minor editorial changes, issued the AD as proposed (67


FR 43227, June 27, 2002). Since issuing AD 2002-13-05, we have determined that we


inappropriately responded to the comment and that the commenter's concern was valid. We are now


reducing the applicability of AD 2002-13-05 to include only certain tailboom S/N's and parts that are


modified in accordance with either STC SH5055NM or SH4801NM. We are also correcting the P/N


for the washer to P/N AN960D416 in Figure 1 of this AD and clarifying that a slippage mark needs to


be reapplied to each bolt regardless of the outcome of the required torque test.


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 this AD will affect 500 helicopters of U.S. registry. Also, the FAA


estimates this AD will require 1/2 work hour per helicopter to determine whether a helicopter has


been modified by either STC and 1 work hour to inspect and replace the bolts for each of


approximately 40 helicopters modified by the STC's. The average labor rate is $60 per work hour.


Required parts will cost approximately $40 per helicopter. Based on these figures, we estimate the


total cost impact of the AD on U.S. operators to be $19,000.


The regulations adopted herein will not have a substantial direct effect 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, it is determined that this final


rule does not have federalism implications under Executive Order 13132.


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 FAA, Office of the Regional Counsel,


Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas.


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 removing Amendment 39-12793 (67 FR 43227, June 27, 2002),


and by adding a new airworthiness directive to read as follows: