[Federal Register Volume 60, Number 231 (Friday, December 1, 1995)]
[Rules and Regulations]
[Pages 61645-61647]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-28957]



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 Rules and Regulations
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  Federal Register / Vol. 60, No. 231 / Friday, December 1, 1995 / 
Rules and Regulations  

[[Page 61645]]


DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94-ANE-47; Amendment 39-9437; AD 95-24-05]


Airworthiness Directives; McCauley Accessory Division, The Cessna 
Aircraft Company, Model C35, C72, C74, C75, C80, C86, C87, C92, and C93 
Series Propellers

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to McCauley Accessory Division, The Cessna Aircraft 
Company, Model C35, C72, C74, C75, C80, C86, C87, C92, and C93 series 
propellers. This action requires initial and repetitive visual and dye 
penetrant inspections of the propeller hub for cracks. This action also 
requires a one-time eddy current inspection for cracks in the threaded 
areas of the propeller hub followed by modification of the hub to 
contain oil with red dye as a terminating action to the repetitive 
inspections. This amendment is prompted by reports of cracked propeller 
hubs. The actions specified in this AD are intended to prevent 
propeller blade separation due to a cracked propeller hub, which could 
result in separation of the engine from the aircraft and subsequent 
loss of aircraft control.

DATES: Effective December 18, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 18, 1995.
    Comments for inclusion in the Rules Docket must be received on or 
before January 30, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Assistant Chief 
Counsel, Attention: Rules Docket No. 94-ANE-47, 12 New England 
Executive Park, Burlington, MA 01803-5299.
    The service information referenced in this AD may be obtained from 
McCauley Accessory Division, The Cessna Aircraft Company, 3535 McCauley 
Dr., Vandalia, OH 45377-0430; telephone (513) 890-5246, fax (513) 890-
6001. 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: Patricia Bonnen, Aerospace Engineer, 
Chicago Aircraft Certification Office, FAA, Small Airplane Directorate, 
2300 East Devon Ave., Room 232, Des Plaines, IL 60018; telephone (708) 
294-7134, fax (708) 294-7834.

SUPPLEMENTARY INFORMATION: The Federal Aviation Administration (FAA) 
has received several reports of cracked propeller hubs on McCauley 
Accessory Division, The Cessna Aircraft Company, Model C35, C72, C74, 
C75, C80, C86, C87, C92, and C93 series propellers. Additionally, two 
incidents have occurred where the propeller blades separated during 
flight. This condition, if not corrected, could result in propeller 
blade separation due to a cracked propeller hub, which could result in 
separation of the engine from the aircraft and subsequent loss of 
aircraft control.
    The FAA has reviewed and approved the technical contents of the 
following service documents:
    (a) McCauley Accessory Division, The Cessna Aircraft Company, 
Service Bulletin (SB) No. 200C, dated January 20, 1994, that describes 
procedures for an initial and repetitive visual and dye penetrant 
inspections of propeller hubs for cracks, and
    (b) McCauley Service Letter (SL) No. 1993-11A, dated June 20, 1995, 
that describes procedures for eddy current inspection for cracks in the 
threaded areas of the propeller hub and modification of the hub to 
contain oil with red dye, which provides a built-in means of crack 
detection, as well as improved lubrication and corrosion protection.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other propellers of the same type design, this 
airworthiness directive (AD) is being issued to prevent propeller blade 
separation due to a cracked propeller hub, which could result in 
separation of the engine from the aircraft and subsequent loss of 
aircraft control. This AD requires initial and repetitive visual and 
dye penetrant inspections of the propeller hub for cracks. This AD also 
requires a one-time eddy current inspection for cracks in the threaded 
areas of the propeller hub followed by modification of the hub to 
contain oil with red dye, which constitutes terminating action to the 
repetitive visual and dye-penetrant inspections. The actions are 
required to be accomplished in accordance with the service documents 
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 

[[Page 61646]]
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 94-ANE-47.'' 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 USC 106(g), 40101, 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

95-24-05  McCauley Accessory Division, The Cessna Aircraft Company: 
Amendment 39-9437. Docket 94-ANE-47.

    Applicability: McCauley Accessory Division, The Cessna Aircraft 
Company, Model C35, C72, C74, C75, C80, C86, C87, C92, and C93 
series propellers, incorporating the following Hub Models:

D3AF32C35-( )
3AF32C72-( )
3AF34C74-( )
3AF32C75-( )
D3AF32C80-( )
3AF34C86-( )
3AF32C87-( )
D3AF32C87-( )
3AF34C92-( )
3AF32C93-( )

    The parentheses used in the above list indicate the presence or 
absence of an additional letter(s) which vary the basic propeller 
hub model designation. These letter(s) define minor changes that do 
not affect interchangeability or eligibility, and therefore, this 
airworthiness directive (AD) still applies regardless of whether 
these letters are present or absent on the propeller hub model 
designation.
    These propellers are installed on but not limited to the 
following aircraft: Beech 58, 58A, 95-C55, -C55A, -D55, -D55A, -E55, 
-E55A.
    British Aerospace B-206 Series 2.
    Cessna 310K, 310L, 310N, 310P, 310Q, 310R, T310P, T310Q, T310R, 
320D, 320E, 320F, 335, 340, 340A, 401, 401A, 401B, 402, 402A, 402B, 
402C, 411, 411A, 414, 414A, 421, 421A, 421B.
    Colemill Executive 600 (Conversion of Cessna 310I, 310J, 310K, 
310L, 310N).
    RAM Conversion of Cessna 340.

    Note 1: The above is not an exhaustive list of aircraft which 
may contain the affected McCauley Model C35, C72, C74, C75, C80, 
C86, C87, C92, and C93 series propellers, incorporating Models 
D3AF32C35, 3AF32C72, 3AF34C74, 3AF32C75, D3AF32C80, 3AF34C86, 
3AF32C87, D3AF32C87, 3AF34C92, and 3AF32C93 propeller hubs because 
of installation approvals made by Supplemental Type Certificate or 
Federal Aviation Administration (FAA) Form 337 ``Major Repair and 
Alteration,'' etc. It is the responsibility of the owner, operator 
and person returning the aircraft to service to determine if an 
aircraft has an affected propeller

    .Note 2: 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 use the authority 
provided in paragraph (g) 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 propeller from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent propeller blade separation due to a cracked propeller 
hub, which could result in separation of the engine from the 
aircraft and subsequent loss of aircraft control, accomplish the 
following:
    (a) Within the next 25 hours time in service (TIS) after the 
effective date of this AD, unless already accomplished within the 
last 35 hours TIS, and thereafter at intervals not to exceed 60 
hours TIS, perform a visual and dye penetrant inspection for cracks 
in propeller hubs in accordance with McCauley Accessory Division, 
The Cessna Aircraft Company, Service Bulletin (SB) No. 200C, dated 
January 20, 1994. Any propeller hubs found cracked during this 
inspection are to be permanently retired from service and replaced 
with a serviceable hub modified in accordance with paragraph (c) of 
this AD, or with an equivalent initial production propeller which 
has incorporated a hub containing oil with red dye.
    (b) For affected propellers identified with the change letter 
``R'' following the hub model designation and having an oil-fill 
plug in the side of the hub, compliance is required only with 
paragraphs (d) and (f) of this AD.
    (c) Perform a one-time eddy current inspection and modify 
serviceable propeller hubs in accordance with the following schedule 
and requirements:

------------------------------------------------------------------------
 Propeller Time-In-Service (TIS) on the                                 
       effective date of this AD               Compliance required      
------------------------------------------------------------------------
Greater than 900 hours or 59 calendar    Within the next 300 hours or at
 months since last overhaul/penetrant     the next annual inspection or 
 inspection or installed new, or prior    within 12 months after the    
 TIS unknown.                             effective date of this AD,    
                                          whichever occurs first.       
Less than or equal to both 900 hours     Prior to the accumulation of   
 and 59 calendar months since last        1,200 hours or 60 calendar    
 overhaul/penetrant inspection or         months since last overhaul/   
 installed new.                           penetrant inspection or       
                                          installed new, whichever      
                                          occurs first.                 
------------------------------------------------------------------------


[[Page 61647]]


    (1) Perform a one-time eddy current inspection for cracks in the 
threaded areas of the propeller hubs in accordance with McCauley 
Accessory Division, The Cessna Aircraft Company, Service Letter (SL) 
No. 1993-11A, dated June 20, 1995.
    (2) Any propeller hubs found cracked during the eddy current 
inspection are to be permanently retired from service and replaced 
with a serviceable hub modified in accordance with paragraph (c) of 
this AD, or with an equivalent initial production propeller which 
has incorporated a hub containing oil with red dye.
    (3) Modify affected propeller hubs to contain oil with red dye, 
in accordance with McCauley Accessory Division, The Cessna Aircraft 
Company, SL No. 1993-11A, dated June 20, 1995. Completion of this 
modification of the hub to contain oil with red dye constitutes 
terminating action to the repetitive inspections required by 
paragraph (a) of this AD.

    Note: 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 of the propeller assembly and also improves 
lubrication and corrosion protection. The oil will add approximately 
4.0 lbs. to the weight of the propeller assembly.

    (4) Previous compliance with McCauley Accessory Division SL 
1993-11, dated September 15, 1993, also constitutes compliance with 
paragraphs (a) and (c) of this AD.
    (5) Install Decal-Warning ``Oil Filled'', part number B-6493, in 
accordance with McCauley Accessory Division, The Cessna Aircraft 
Company, SL No. 1993-11A, dated June 20, 1995, Figure F-9.
    (d) If leakage of oil containing red dye is detected in service 
(whether during flight or while on the ground), determine, prior to 
further flight, the source of leakage in accordance with the 
procedures specified in Section A-7 of McCauley SL No. 1993-11A, 
dated June 20, 1995. Remove from service, prior to further flight, 
propeller assemblies that exhibit cracks and replace with a 
serviceable unit, modified in accordance with paragraph (c) of this 
AD, or with an equivalent initial production propeller that has 
incorporated a hub containing oil with red dye. Oil-filled 
propellers are identified with the change letter ``R'' following the 
Hub Model Designation and have an oil-fill plug in the side of the 
hub.
    (e) The ``calendar month'' compliance times stated in this AD 
allow the performance of the required action up to the last day of 
the month in which compliance is required. For example, a required 
eddy current inspection and modification 60 calendar months from 
last overhaul/penetrant inspection that was performed on December 
15, 1991, would allow the eddy current inspection and modification 
to be performed no later than December 31, 1996.
    (f) Report in writing any cracks found during the accomplishment 
of paragraphs (a), (c) or (d) of this AD to the Manager, Chicago 
Aircraft Certification Office, FAA, Small Airplane Directorate, 2300 
East Devon Avenue, Room 232, Des Plaines, IL 60018; telephone (708) 
294-7134, fax (708) 294-7834, within 10 days of the inspection. 
Information collection requirements contained in the regulation have 
been approved by the Office of Management and Budget (OMB) under the 
provisions of the Paperwork Reduction Act of 1980 (P.L. 96-511) and 
has been assigned OMB Control Number 2120-0056.
    (g) 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. The request should be forwarded through an appropriate FAA 
Maintenance Inspector, who may add comments and then send it to the 
Manager, Chicago Aircraft Certification Office.

    Note: 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.

    (h) 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.
    (i) The inspections and modification required by this AD shall 
be done in accordance with the following McCauley Accessory 
Division, The Cessna Aircraft Company, service documents:

------------------------------------------------------------------------
             Document No.                Pages             Date         
------------------------------------------------------------------------
SB 200C..............................    1-4     January 20, 1994.      
    Total pages: 4...................                                   
SL 1993-11A:                                                            
Cover Page...........................      1     June 20, 1995.         
Section A............................    1-4     June 20, 1995.         
Section B............................      1     June 20, 1995.         
Section C............................      1     June 20, 1995.         
Section D............................    1-7     June 20, 1995.         
Section E............................   1-10     June 20, 1995.         
Section F............................   1-15     June 20, 1995.         
Section G............................      1     June 20, 1995.         
Section H............................    1-4     June 20, 1995.         
Section I............................    1-4     June 20, 1995.         
    Total pages: 48..................                                   
------------------------------------------------------------------------

    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 Accessory Division, 
The Cessna Aircraft Company, 3535 McCauley Dr., Vandalia, OH 45377-
0430; telephone (513) 890-5246, fax (513) 890-6001. 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.
    (j) This amendment becomes effective on December 18, 1995.

    Issued in Burlington, Massachusetts, on November 7, 1995.
James C. Jones,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 95-28957 Filed 11-30-95; 8:45 am]
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