[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: ``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 
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:

------------------------------------------------------------------------
                                              Compliance schedule of
                                             propeller inspection and
                                                   modification
------------------------------------------------------------------------
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.
------------------------------------------------------------------------

    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:

------------------------------------------------------------------------
             Document No.                Page             Date
------------------------------------------------------------------------
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
------------------------------------------------------------------------

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