[Federal Register Volume 63, Number 243 (Friday, December 18, 1998)]
[Rules and Regulations]
[Pages 69996-69999]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-33028]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-ANE-34-AD; Amendment 39-10939, AD 98-25-13]
RIN 2120-AA64
Airworthiness Directives; McCauley Propeller Systems Models
2A36C23/84B-0 and 2A36C82/84B-2 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 McCauley Propeller Systems (formerly McCauley
Accessory Division, The Cessna Aircraft Company)
[[Page 69997]]
Models 2A36C23/84B-0 and 2A36C82/84B-2 propellers. This action
supersedes priority letter AD 89-26-08 that currently requires
penetrant inspections for cracks in the propeller blade threaded
retention area, and modifying the propeller hub to a red dye filled
configuration. This action adds an explanatory note to better define
the AD applicability and makes minor adjustments to compliance section
language to reflect current AD practice. This amendment is prompted by
reports of confusion from operators as to if the AD is applicable to
their particular model propeller. The actions specified by this AD are
intended to prevent possible cracks in the propeller blade threaded
retention area from progressing to blade separation, which can result
in loss of aircraft control.
DATES: Effective January 4, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 14, 1999.
Comments for inclusion in the Rules Docket must be received on or
before February 16, 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-34-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
McCauley Propeller Systems, 3535 McCauley Dr., PO Drawer 5053,
Vandalia, OH 45377; telephone (937) 890-5246, fax (937) 890-6001. 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: Tim Smyth, Aerospace Engineer, Chicago
Aircraft Certification Office, FAA, Small Airplane Directorate, 2300
East Devon Avenue, Des Plaines, IL 60018; telephone (847) 294-7132; fax
(847) 294-7834.
SUPPLEMENTARY INFORMATION: On December 20, 1989, the Federal Aviation
Administration (FAA) issued priority letter airworthiness directive
(AD) 89-26-08, applicable to McCauley Propeller Systems (formerly
McCauley Accessory Division, The Cessna Aircraft Company) Models
2A36C23/84B-0 and 2A36C82/84B-2 propellers, which requires penetrant
inspections for cracks in the propeller blade threaded retention area,
and modifying the propeller hub to a red dye filled configuration. That
action was prompted by reports of cracks in the propeller blade
threaded retention area. That condition, if not corrected, could result
in possible cracks in the propeller blade threaded retention area from
progressing to blade separation, which can result in loss of aircraft
control.
Since the issuance of that priority letter AD, the FAA has received
reports of confusion from operators as to if the AD is applicable to
their particular model propeller.
The FAA has reviewed and approved the technical contents of
McCauley Service Letter (SL) 1989-5, dated November 14, 1989, that
describes procedures for propeller disassembly and modification of the
propeller hub assembly to red dye filled configuration, and McCauley
Service Manual No. 720415, Revision No. 1, dated May 1972, Chapter I,
Page 4-6, Paragraph 4-6, that describes procedures for penetrant
inspections for cracks in the propeller blade threaded retention area.
Since an unsafe condition has been identified that is likely to
exist or develop on other propellers of this same type design, this AD
supersedes priority letter AD 89-26-08 to add an explanatory note to
better define the AD applicability and makes minor adjustments to
compliance section language to reflect current AD practice. The actions
are required to be accomplished in accordance with the service
information 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 98-ANE-34-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.
[[Page 69998]]
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:
98-25-13 McCauley Propeller Systems: Amendment 39-10939. Docket No.
98-ANE-34-AD. Supersedes AD 89-26-08.
Applicability: McCauley Propeller Systems (formerly McCauley
Accessory Division, The Cessna Aircraft Company) Models 2A36C23/84B-
0 and 2A36C82/84B-2 propellers installed on, but not limited to,
Raytheon (formerly Beech) 35-B33, 35-A33, 35-33, 35-C33, 35-C33A,
36, A36, A45, E33, E33A, E33C, F33, F33A, F33C, G33, H35, J35, K35,
M35, N35, P35, S35, V35, V35A, V35B Model aircraft, and S35, V35,
V35A, V35B series aircraft.
Note 1: This 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 (f) 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 possible cracks in the propeller blade threaded
retention area from progressing to blade separation, which can
result in loss of aircraft control, accomplish the following
penetrant inspection and modification of the below listed hub
models, in accordance with the compliance schedule as indicated, in
which hours refer to time-in-service:
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Compliance schedule of
propeller inspection and
modification
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Propeller hub model 2A36C23-( )-( ),
regardless of blade model type,
installed on flight training airplanes
and/or acrobatic category airplanes:
Greater than 400 hours or 59 Within the next 100 hours or
calendar months since last one (1) calendar month after
overhaul/penetrant inspection or the effective date of this AD,
installed new; or prior time-in- whichever occurs first.
service unknown.
Less than or equal to both 400 Prior to the accumulation of
hours and 59 calendar months since 500 hours or 60 calendar
last overhaul/penetrant inspection months since last overhaul/
or installed new. penetrant inspection or
installed new, whichever
occurs first.
Propeller hub model 2A36C23-( )-( ),
regardless of blade model, installed
on other than flight training
airplanes and/or acrobatic category
airplanes:
Greater than 900 hours or 59 Within the next 200 hours, or
calendar months since last at the next annual inspection,
overhaul/penetrant inspection or or within 12 calendar months
installed new; time-in-service after the effective AD,
unknown. whichever occurs first.
Less than or equal to both 900 Prior to the accumulation of
hours and 59 calendar months since 1100 hours or 60 calendar
last overhaul/penetrant inspection months since last overhaul/
or installed new. penetrant inspection or
installed new, whichever
occurs first.
Propeller hub model 2A36C82-( )-( ),
regardless of blade model installed on
all category airplanes:
Greater than 1300 hours or 59 Within the next 200 hours, or
calendar months since last at the next annual inspection,
overhaul/penetrant inspection or or within 12 calendar months
installed new; prior time-in after the effective date of
service unknown. this AD, whichever occurs
first.
Less than or equal to both 1300 Prior to the accumulation of
hours and 59 calendar months since 1500 hours or 60 calendar
last overhaul/penetrant inspection months since last overhaul/
or installed new. penetrant inspection or
installed new, whichever
occurs first.
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Note 2: The parentheses used in the above list indicate the
presence or absence of an additional letter(s) which vary the basic
hub model designation. These letter(s) define minor changes that do
not affect interchangeability or eligibility, and therefore, this AD
still applies regardless of whether these letters are present or
absent on the hub model designation.
Note 3: For propellers which have incorporated an oil-filled
configuration with red dye and have been designated as hub Model
2A36C23-( )-G or Model 2A36C82- ( )-G at initial production; or
prior manufactured propellers which have been modified to an oil-
filled configuration with red dye and reidentified as hub Model
2A36C23-( )-( )G or Model 2A36C82-( )-( )G, this airworthiness
directive (AD) requires compliance with paragraph (d) only.
Note 4: Flight training airplanes for purposes of complying with
this AD are defined as airplanes which are used currently for flight
training instruction.
Note 5: The ``calendar month'' compliance times stated in this
AD allow the performance of the required action to be extended to
the last day of the month in which compliance is required. Example,
a required inspection and modification of 60 months from last
overhaul/penetrant inspection that was performed on December 15,
1985, would allow the penetrant inspection and modification to be
performed no later than December 31, 1990.
(a) Perform disassembly in accordance with McCauley Service
Letter (SL) 1989-5, dated November 14, 1989, and penetrant inspect
for cracks in the propeller blade threaded retention area in
accordance with McCauley Service Manual No. 720415, Revision No. 1,
dated May 1972, Chapter I, Page 4-6, Paragraph 4-6.
(b) If any indication of a crack is found, prior to further
flight, remove propeller assembly and replace with a serviceable
unit, complying with paragraph (c) below, or an equivalent initial
production oil filled hub Model with red dye.
(c) Modify propeller hub assembly Model 2A36C23-( )-( ) to Model
2A36C23-( )-( )G, and Model 2A36C82-( )-( ) to Model 2A36C82-( )-(
)G, as appropriate to contain oil with a red dye and reidentify in
accordance with McCauley SL 1989-5, dated November 14, 1989.
Note 6: The modification of the propeller hub assembly to
contain oil with a red dye provides an ``on-condition'' (in-service)
means of early crack detection to prevent a blade separation and
also improves lubrication and corrosion protection.
[[Page 69999]]
(d) If red dye is observed in service on hub Models in
compliance with paragraph (c), or on an equivalent initial
production oil filled hub Model with red dye, before further flight,
or if in flight land as soon as practicable, as applicable,
determine source of leakage in accordance with McCauley SL 1989-5,
dated November 14, 1989. In the event the inspection reveals a
crack, remove propeller assembly and replace with a serviceable oil
filled hub Model with red dye.
(e) Report in writing any cracks found to the Manager, Chicago
Aircraft Certification Office, within ten (10) days of the
inspection. Reporting approved by the Office of Management and
Budget under OMB No. 2120-0056.
(f) 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, Chicago 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, Chicago Aircraft Certification Office.
Note 7: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Chicago Aircraft Certification
Office.
(g) 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.
(h) The actions required by this AD shall be accomplished in
accordance with the following McCauley service documents:
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Document No. Page Date
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Service letter 1989-5A:
Cover............................... 1 July 16, 1990.
Section A........................... 1-4 July 16, 1990.
Section B........................... 1 July 16, 1990.
Section C........................... 1 July 16, 1990.
Section D........................... 1-3 July 16, 1990.
Section E........................... 1-6 July 16, 1990.
Section F........................... 1-8 July 16, 1990.
Section G........................... 1 July 16, 1990.
Section H........................... 1,2 July 16, 1990.
Section I........................... 1 July 16, 1990.
--------
Total pages..................... 28 Undated.
Service manual 720415, Chapter 1...... 4-6
Total pages..................... 1
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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 McCauley Propeller Systems, 3535
McCauley Dr., PO Drawer 5053, Vandalia, OH 45377; telephone (937)
890-5246, fax (937) 890-6001. 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.
(i) This amendment supersedes priority letter AD 89-26-08,
issued December 20, 1989.
(j) This amendment becomes effective on January 4, 1999.
Issued in Burlington, Massachusetts, on December 4, 1998.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 98-33028 Filed 12-17-98; 8:45 am]
BILLING CODE 4910-13-U
