[Federal Register Volume 63, Number 232 (Thursday, December 3, 1998)]
[Rules and Regulations]
[Pages 66737-66739]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-31701]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-ANE-59-AD; Amendment 39-10920; AD 98-24-34]
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 affected propeller blades to be removed from service and
shipped to designated repair facilities for inspection for insufficient
cold rolling of the beveled radius of the blade flange. Affected blades
are identified by serial number. This amendment is prompted by reports
of propeller blades that cracked due to incomplete cold rolling in the
beveled radius area of the blade flange. The actions specified in this
AD are intended to prevent propeller blade cracks due to incomplete
cold rolling during manufacture, which can result in propeller blade
separation and damage to the aircraft.
DATES: Effective December 18, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 18, 1998.
Comments for inclusion in the Rules Docket must be received on or
before February 1, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Regional
Counsel, Attention: Rules Docket No. 98-ANE-59-AD, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may also be sent
via the Internet using the following address: ``engineprop@faa.dot.gov''. 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, Publications Distribution Group, 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 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.
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 (781) 238-7158, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The Federal Aviation Administration (FAA)
has received reports of 16 propeller blades with insufficient cold
rolling in the beveled radius of the blade flange area. Two of these
blades were found with cracks and two others experienced a blade
fracture and separation. Incomplete cold rolling in the beveled radius
area of the blade flange may have occurred during manufacture of the
affected Hamilton Standard Models 54H60-77, -91, -117, -123, and -125
propellers. The FAA issued airworthiness directive AD 97-13-07 (62 FR
34619, June 27, 1997) to correct the unsafe condition in the most
critical population. This AD expands the population to include 13,372
additional propeller blades that require removal for inspection, and,
if necessary, repair. This condition, if not corrected, could result in
propeller blade cracks due to incomplete cold rolling during
manufacture, which can result in propeller blade separation and damage
to the aircraft.
The FAA has reviewed and approved the technical contents of
Hamilton Standard Alert Service Bulletin (ASB) No. 54H60-61-A134,
Revision 1, dated June 24, 1998, and ASB No. 54H60-61-A135, dated June
24, 1998, that identify affected propeller blades by serial number (S/
N), and list the designated repair facilities for shipment of blades
following removal from service for inspection and repair.
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 cracking. This AD requires,
for affected propeller blades identified by S/N, removal from service
and shipment to designated repair facilities for inspection for
incomplete cold rolling during manufacture, and, repair, if necessary.
The propeller blades identified in ASB No. 54H60-61-A135, dated June
24, 1998 are to be inspected within 100 hours time in service (TIS)
while the propeller blades identified in ASB No. 54H60-61-A134,
Revision 1, dated June 24, 1998, are to be inspected within 4,500 hours
time since overhaul or for blades that have never been overhauled,
4,500 hours time since new. In addition all propeller blades must be
inspected or repaired, if necessary, prior to September 30, 2002. This
calendar end-date was determined by engineering study and evaluations.
The actions are required to be accomplished in accordance with the ASBs
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
[[Page 66738]]
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-59-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.
39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
98-24-34 Hamilton Standard: Amendment 39-10920. Docket 98-ANE-59-
AD.
Applicability: Hamilton Standard Models 54H60-77, -91, -117, -
123, and -125 propellers, with propeller blades identified by serial
number (S/N) in Hamilton Standard Alert Service Bulletin (ASB) No.
54H60-61-A134, Revision 1, dated June 24, 1998, and ASB No. 54H60-
61-A135, dated June 24, 1998. These propellers are installed on but
not limited to Lockheed L100, L188, L200, L288, L382, C130, P-3, and
General Dynamics (Convair) CV580 and Guppy 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 cracks due to incomplete cold rolling
during manufacture, which can result in propeller blade separation
and damage to the aircraft, accomplish the following:
(a) Within 100 hours time in service (TIS) after the effective
date of this AD, or prior to September 30, 2002, whichever occurs
first, remove from service affected propeller blades identified by
S/N in Hamilton Standard ASB No. 54H60-61-A135, dated June 24, 1998,
and ship to designated repair facilities listed in that ASB for
inspection, and, if necessary, repair.
(b) For affected propeller blades identified by S/N in ASB No.
54H60-61-A134, Revision 1, dated June 24, 1998, remove from service
and ship to designated repair facilities listed in that ASB for
inspection, and, if necessary, repair, after the effective date of
this AD, in accordance with paragraphs (b)(1) and (b)(2) of this AD,
or prior to September 30, 2002, whichever occurs first.
(1) Remove from service within 100 hours TIS propellers that
have greater than 4,400 hours time since overhaul (TSO), or for
propellers that have never been overhauled remove from service
propellers that have greater than 4,400 hours time since new (TSN).
(2) For propellers with less than 4,400 hours (TSO) remove from
service prior to accumulating 4,500 hours TSO, or for propellers
with less than 4,400 hours TSN that have never been overhauled
remove from service prior to accumulating 4,500 hours TSN.
(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 ASBs:
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Document No. Pages Revision Date
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54H60-61-A134........................ 1-5.................... 1...................... June 24, 1998
54H60-61-A134........................ 1-5.................... 1...................... June 24, 1998
Total pages: 5...................
54H60-61-A135........................ 1-10................... Original............... June 24, 1998
Total pages: 10..................
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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, Publications
Distribution Group, 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 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.
(f) This amendment becomes effective on December 18, 1998.
[[Page 66739]]
Issued in Burlington, Massachusetts, on October 20, 1998.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 98-31701 Filed 12-2-98; 8:45 am]
BILLING CODE 4910-13-P
