[Federal Register Volume 62, Number 195 (Wednesday, October 8, 1997)]
[Rules and Regulations]
[Pages 52489-52490]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-26621]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-SW-32-AD; Amendment 39-10151; AD 97-20-15]
RIN 2120-AA64
Airworthiness Directives; Hiller Aircraft Corporation Model UH-
12A, UH-12B, UH-12C, UH-12D, and UH-12E Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to Hiller Aircraft Corporation Model UH-12A, UH-12B,
UH-12C, UH-12D, and UH-12E helicopters, that currently requires a dye
penetrant inspection of the head of the main rotor outboard tension-
torsion (T-T) bar pin for cracks; a visual inspection of the outboard
T-T bar pin for proper alignment and an adjustment, if necessary; and,
installation of shims at the inboard end of the drag strut. This
amendment requires the same actions required by the existing AD, but
allows a magnetic particle inspection of the T-T bar pin as an
alternative to the currently required dye penetrant inspection, and
requires reporting the results of the inspections only if cracks are
found, rather than reporting all results of inspections as required by
the existing AD. This amendment is prompted by an FAA analysis of a
comment to the existing AD, and the fact that no cracks have been
reported since the issuance of the existing AD. The actions specified
by this AD are intended to prevent cracks in the head area of the
outboard T-T bar pin, which could result in loss of in-plane stability
of the main rotor blade and subsequent loss of control of the
helicopter.
DATES: Effective November 12, 1997.
The incorporations by reference of certain publications listed in
the regulations were approved by the Director of the Federal Register
as of June 23, 1995 (60 FR 30184, June 8, 1995).
ADDRESSES: The service information referenced in this AD may be
obtained from Hiller Aircraft Corporation, 3200 Imjin Road, Marina,
California 93933-5101, telephone (408) 384-4500, fax (408) 883-3648.
This information may be examined at the FAA, Office of the Assistant
Chief Counsel, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at
the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Mr. Charles Matheis, Aerospace
Engineer, FAA, Los Angeles Aircraft Certification Office, 3960
Paramount Blvd., Lakewood, California 90712-4137, telephone (562) 627-
5235, fax (562) 627-5210.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 95-12-02,
Amendment 39-9252 (60 FR 30184), which is applicable to Hiller Model
UH-12A, UH-12B, UH-12C, UH-12D, and UH-12E helicopters, was published
in the Federal Register on January 7, 1997 (62 FR 951). That action
proposed to require (1) an inspection of the alignment of the outboard
T-T bar pin and an adjustment, if necessary; and (2) an inspection for
cracks in the head of the outboard T-T bar pin using a dye penetrant
method or a magnetic particle method. Additionally, that action
proposed to require, within 25 hours TIS or at the next 100 hour
inspection, whichever occurs first, the installation of shims between
the inboard end of the drag strut and the outboard T-T bar pin.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comment received.
The one commenter states that AD 95-12-02 should be eliminated, and
that the requirement to report results of each 100 hour TIS inspection
to the FAA should be discontinued, unless a crack is found. The
commenter states that they have not experienced a T-T bar pin failure
in 30 years of service history, and that if the procedures in the
manufacturer's service information is followed, the AD is not needed.
The FAA concurs that the reporting of the inspection should be
accomplished only if the inspection reveals a crack. However, the FAA
does not concur that the AD should be eliminated. The
[[Page 52490]]
National Transportation Safety Board recommended that the FAA issue an
AD to make the requirements of the applicable service information
mandatory. The FAA concurred, and issued AD 95-12-02. Based on an FAA
analysis, the FAA has determined that the amendment will not be
removed, but the reporting requirement will be changed.
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed.
The FAA estimates that 700 helicopters of U.S. registry will be
affected by this AD, that it will take approximately 2 work hours per
helicopter to accomplish the required actions, and that the average
labor rate is $60 per work hour. Required parts will cost approximately
$700 per pin. Based on these figures, the total cost impact of the AD
on U.S. operators is estimated to be $574,000, assuming one pin must be
replaced on every helicopter in the fleet.
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 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.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing Amendment 39-9252 (60 FR
30184), and by adding a new airworthiness directive (AD), Amendment 39-
10151, to read as follows:
97-20-15 Hiller Aircraft Corporation: Amendment 39-10151. Docket
No. 96-SW-32-AD. Supersedes AD 95-12-02, Amendment 39-9252.
Applicability: Model UH-12A, UH-12B, UH-12C, UH-12D, and UH-12E
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 (e) 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 as indicated, unless accomplished
previously.
To prevent cracks in the head area of the outboard tension-
torsion (T-T) bar pin, which could result in loss of in-plane
stability of the main rotor blade and subsequent loss of control of
the helicopter, accomplish the following:
(a) Within 25 hours time-in-service (TIS) after the effective
date of this AD, or at the next 100 hour inspection, whichever
occurs first, and thereafter at intervals not to exceed 100 hours
TIS, inspect the alignment of the outboard T-T bar pin, part number
(P/N) 51452, and adjust the alignment, if necessary, in accordance
with Hiller Aviation Service Letter (SL) 51-2, dated March 31, 1978.
(b) Within 25 hours TIS after the effective date of this AD, or
at the next 100 hour inspection, whichever occurs first, and
thereafter at intervals not to exceed 100 hours TIS, inspect the
head of the outboard T-T bar pin for cracks using a dye penetrant or
magnetic particle inspection method.
(c) If a crack is found as a result of the inspection required
by paragraph (b) of this AD, report the results within 7 working
days following the inspection to the Manager, Los Angeles Aircraft
Certification Office, Attention Charles Matheis, ANM-120L, 3960
Paramount Blvd., Lakewood, California 90712-4137. Include the
helicopter model number, serial number, and total TIS of the
outboard T-T bar pin in the report. Reporting requirements have been
approved by the Office of Management and Budget and assigned OMB
control number 2120-0056.
(d) Within 25 hours TIS after the effective date of this AD, or
at the next 100 hour inspection, whichever occurs first, install
shims between the inboard end of the drag strut and the outboard T-T
bar pin in accordance with the Accomplishment Instructions of Hiller
Aviation Service Bulletin No. 51-9, dated April 8, 1983.
(e) 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, FAA. 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.
(f) 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.
(g) The adjustment of the alignment of the T-T bar pin shall be
done in accordance with Hiller Aviation SL 51-2, dated March 31,
1978, and the installation of the shims shall be done in accordance
with Hiller Aviation Service Bulletin No. 51-9, dated April 8, 1983.
These incorporations by reference were approved by the Director of
the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51 as of June 23, 1995 (60 FR 30184, June 8, 1995). Copies may
be obtained from Hiller Aircraft Corporation, 3200 Imjin Road,
Marina, California 93933-5101, telephone (408) 384-4500, fax (408)
883-3648. Copies may be inspected at the FAA, Office of the
Assistant Chief Counsel, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas; or at the Office of the Federal Register, 800 North Capitol
Street, NW., suite 700, Washington, DC.
(h) This amendment becomes effective on November 12, 1997.
Issued in Fort Worth, Texas, on September 26, 1997.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 97-26621 Filed 10-7-97; 8:45 am]
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