[Federal Register Volume 62, Number 124 (Friday, June 27, 1997)]
[Rules and Regulations]
[Pages 34619-34621]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-16281]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-ANE-24-AD; Amendment 39-10054; AD 97-13-07]
RIN 2120-AA64
Airworthiness Directives; Hamilton Standard 54H60 Series
Propellers
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to Hamilton Standard 54H60 series propellers. This action
requires removing from service affected propeller blades, and returning
those blades to the manufacturer or an approved facility for
inspection, rework, and return to service. This amendment is prompted
by reports of a propeller blade manufacturing defect. The actions
specified in this AD are intended to prevent propeller blade fracture
due to the manufacturing defect, which could result in propeller blade
separation and loss of control of the aircraft.
DATES: Effective July 14, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 14, 1997.
Comments for inclusion in the rules docket must be received on or
before August 26, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 97-ANE-24-AD, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may also be sent
via the Internet using the following address: ``9-ad-
[email protected]''. Comments sent via the Internet must contain
the docket number in the subject line.
The service information referenced in this AD may be obtained from
Hamilton Standard, Attn: Publications Mail Stop 6-B12, One Hamilton
Rd., Windsor Locks, CT 06096-1010; telephone (860) 654-6876, fax (860)
654-6906. This information may be examined at the FAA, New England
Region, Office of the Assistant Chief 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.
FOR FURTHER INFORMATION CONTACT: Frank Walsh, Aerospace Engineer,
Boston Aircraft Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299;
telephone (617) 238-7158, fax (617) 238-7199.
SUPPLEMENTARY INFORMATION: The Federal Aviation Administration (FAA)
has received reports of a propeller blade fracture and subsequent blade
departure on a Hamilton Standard Model 54H60-111 propeller installed on
a military Lockheed Martin KC-130 aircraft. Propellers with the same or
similar design are installed on many civil aircraft. The crack
initiated in the beveled radius of the blade root. The investigation
revealed that the propeller blades were manufactured during the fourth
quarter of 1983 when a possible random deficiency cold rolling
intensity occurred. Further investigation revealed that this
manufacturing defect may exist for a larger propeller blade population
than those propellers originally inspected in accordance with Hamilton
Standard Alert Service Bulletin (ASB) No. 54H60-61-A125, dated May 23,
1990. This condition, if not corrected, could result in propeller blade
fracture due to the manufacturing defect, which could result in
propeller blade separation and loss of control of the aircraft.
The FAA has reviewed and approved the technical contents of
Hamilton Standard Alert Service Bulletin (ASB) No. 54H60-61-A133,
Revision 1, dated May 29, 1997, that lists serial numbers of affected
propeller blades, and describes procedures for removing from service
affected propeller blades, and returning those blades to the
manufacturer or an approved repair facility for return to service. The
FAA is concerned with the structural integrity of certain propeller
blades in the suspect population, identified in that SB, with propeller
repair records indicating that the beveled radius was recut and cold
rolled at a repair facility as the result of repair of the beveled
radius area of the blade root. The recutting and cold rolling repair
procedure may mask damage and permit the blade to be acceptable with
the inspection method specified in this AD. These propeller blades must
be retained
[[Page 34620]]
at the repair facility and further inspected by a more extensive
inspection procedure now under development. These propeller blades may
only be returned to service when this more extensive inspection
procedure and subsequent repair is approved by the FAA.
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 fracture. This AD requires
removing from service affected propeller blades, and returning those
blades to the manufacturer or an approved facility for inspection,
rework, and return to service. The actions are required to be
accomplished in accordance with the ASB described previously.
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 in less 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 97-ANE-24-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
rule does 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 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 adding the following new
airworthiness directive:
97-13-07 Hamilton Standard: Amendment 39-10054. Docket 97-ANE-24-
AD.
Applicability: Hamilton Standard Models 54H60-77, -91, -111, -
117, -123, and -125 propellers, with serial numbers listed in
Hamilton Standard Alert Service Bulletin (ASB) No. 54H60-61-A133,
Revision 1, dated May 29, 1997. These propellers are installed on
but not limited to Lockheed Martin C-130, C-130A, 382 series, L-100
series, L-188 series; Aero Space Lines Model 3775GT, and Lockheed
Martin (Convair) CV580 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 (c) 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, unless accomplished
previously.
To prevent propeller blade fracture due to a manufacturing
defect, which could result in propeller blade separation and loss of
control of the aircraft, accomplish the following:
(a) Within 50 hours time in service after the effective date of
this AD, remove from service affected propeller blades, and return
those blades to the manufacturer or an approved facility for
inspection, rework, and return to service, in accordance with
Hamilton Standard ASB No. 54H60-61-A133, Revision 1, dated May 29,
1997.
(b) Those propeller blades that had the beveled radius recut and
cold rolled at an FAA approved repair facility in accordance with
the reference maintenance documents and cannot be returned to
service at this time. Inspection and repair procedures are currently
under development.
(c) 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, Boston 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, Boston Aircraft Certification Office.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Boston Aircraft Certification
Office.
(d) 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.
(e) The actions required by this AD shall be done in accordance
with the following Hamilton Standard ASB:
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Document No. Pages Revision Date
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54H60-61-A133................. 1-9 1 May 29, 1997.
Total Pages: 9.
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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 Hamilton Standard, Attn:
Publications Mail Stop 6-B12, One Hamilton Rd., Windsor Locks, CT
06096-1010; telephone (860) 654-6876, fax (860) 654-6906. Copies may
be inspected at the FAA, New England Region, Office of the Assistant
Chief 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.
(f) This amendment becomes effective on July 28, 1997.
Issued in Burlington, Massachusetts, on June 13, 1997.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 97-16281 Filed 6-26-97; 8:45 am]
BILLING CODE 4910-13-U