[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
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
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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.
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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:
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Propeller Time-In-Service (TIS) on the
effective date of this AD Compliance required
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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.
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[[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:
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Document No. Pages Date
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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..................
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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 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]
BILLING CODE 4910-13-U
