Airworthiness Directives; McCauley Propeller Systems, Inc. Propeller Hub Models B5JFR36C1101, C5JFR36C1102, B5JFR36C1103, and C5JFR36C1104

[Federal Register Volume 68, Number 137 (Thursday, July 17, 2003)]
[Rules and Regulations]
[Pages 42244-42246]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-18236]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NE-32-AD; Amendment 39-13243; AD 2003-15-01]
RIN 2120-AA64


Airworthiness Directives; McCauley Propeller Systems, Inc. 
Propeller Hub Models B5JFR36C1101, C5JFR36C1102, B5JFR36C1103, and 
C5JFR36C1104

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain McCauley Systems, Inc. propellers that are installed on BAE 
Systems (Operations) Limited Jetstream Model 4101 airplanes. This AD 
requires a fluorescent penetrant inspection (FPI) of the propeller 
blades for cracks. This AD is prompted by a report of a significant 
crack in a propeller blade shank and two reports of cracks in the hubs 
of the same propeller model. We are issuing this AD to detect cracks in 
the propeller blade shank that could cause a failure of the propeller 
blade and loss of control of the airplane.

DATES: Effective July 17, 2003. The Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulations as of July 17, 2003.
    We must receive any comments on this AD by September 15, 2003.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
    [sbull] By mail: The Federal Aviation Administration (FAA), New 
England Region, Office of the Regional Counsel, Attention: Rules Docket 
No. 2003-NE-32-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
    [sbull] By fax: (781) 238-7055.
    [sbull] By e-mail: [email protected]
    You may get the service information referenced in this AD from 
McCauley Propeller Systems, 3535 McCauley Drive, Vandalia, OH 45377.
    You may examine the AD docket at the FAA, New England Region, 
Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA. You may examine the service information 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: Timothy Smyth, Aerospace Engineer, 
Chicago Aircraft Certification Office, FAA, Small Airplane Directorate, 
2300 East Devon Avenue, Room 107, Des Plaines, IL 60018; telephone: 
(847) 294-7132; fax: (847) 294-7834.

SUPPLEMENTARY INFORMATION: This AD applies to the following McCauley 
Systems, Inc. propeller assemblies that are installed on BAE Systems 
(Operations) Limited Jetstream Model 4101 airplanes:
    [sbull] Hub Model B5JFR36C1101, with Model 114GC series propeller 
blades,
    [sbull] Hub Model C5JFR36C1102, with Model L114GC series propeller 
blades, and
    [sbull] Hub Model B5JFR36C1103, with Model 114HC series propeller 
blades,
    [sbull] Hub Model C5JFR36C1104, with Model L114HC series propeller 
blades. This AD requires a one time FPI of the retention area of the 
propeller blade. A July 1, 2003, report of vibration prompted this AD. 
An operator of a Jetstream Model 4101 airplane notified McCauley 
Propeller Systems, Inc. of a vibration during flight. Investigation 
found a crack that appeared to extend through the butt of the propeller 
blade for about one-half of the circumference of the blade shank. We 
also received two reports of cracks in the hubs of the same propeller 
models that may be related to this issue. We are requiring the actions 
specified in this AD to detect cracks in the propeller blade shank that 
could cause a failure of the propeller blade and loss of control of the 
airplane.

Relevant Service Information

    We have reviewed and approved the technical contents of McCauley 
Alert Service Bulletin (ASB) ASB246B, Revision 2, dated July 11, 2003, 
that describes procedures for FPI of the propeller blade.

Differences Between This AD and the Service Information

    McCauley ASB ASB246B, Revision 2, dated July 11, 2003, requires the 
operator to perform a blade shake check at 72-hour intervals. This AD 
does not require the blade shake check.

FAA's Determination and Requirements of This AD

    The unsafe condition described previously is likely to exist or 
develop on other McCauley Systems, Inc. propeller hub Models 
B5JFR36C1101, C5JFR36C1102, B5JFR36C1103, and C5JFR36C1104, of the same 
type design that are installed on BAE Systems (Operations) Limited 
Jetstream Model 4101 airplanes. We are issuing this AD to detect cracks 
in the propeller blade shank that could cause a failure of the 
propeller blade and loss of control of the airplane. You must use the 
service information described previously to perform these actions.

FAA's Determination of the Effective Date

    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we have found that notice and opportunity for 
public comment before issuing this AD are impracticable, and that good 
cause exists for making this amendment effective in less than 30 days.

Changes to 14 CFR Part 39--Effect on the AD

    On July 10, 2002, we issued a new version of 14 CFR part 39 (67 FR 
47997, July 22, 2002), which governs our AD system. This regulation now 
includes material that relates to special flight permits, alternative 
methods of compliance, and altered products. This material previously 
was included in each individual AD. Since this material is included in 
14 CFR part 39, we will not include it in future AD actions.

[[Page 42245]]

Interim Action

    These actions are interim actions and we may take further 
rulemaking actions in the future.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to submit any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. 2003-NE-32-AD'' in the 
subject line of your comments. If you want us to acknowledge receipt of 
your mailed comments, send us a self-addressed, stamped postcard with 
the docket number written on it; we will date-stamp your postcard and 
mail it back to you. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the rule 
that might suggest a need to modify it. If a person contacts us 
verbally, and that contact relates to a substantive part of this AD, we 
will summarize the contact and place the summary in the docket. We will 
consider all comments received by the closing date and may amend the AD 
in light of those comments.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications with you. You may get more information about plain 
language at http://www.faa.gov/language and http://www.plainlanguage.gov.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect 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.
    For the reasons discussed above, I certify that the regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket No. 2003-NE-32-AD'' in your request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under 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

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2003-15-01 McCauley Propeller Systems, Inc.: Amendment 39-13243. 
Docket No. 2003-NE-32-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective July 17, 
2003.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to McCauley Propeller Systems, Inc. 
propeller models that are listed in Table 1 of this AD, and are 
installed on BAE Systems (Operations) Limited Jetstream Model 4101 
airplanes. Table 1 follows:

         Table 1.--Propeller Models by Hub Model and Blade Model
------------------------------------------------------------------------
                                            With propeller blade model
          Propeller hub model                       installed
------------------------------------------------------------------------
B5JFR36C1101...........................  114GC series.
C5JFR36C1102...........................  L114GC series.
B5JFR36C1103...........................  114HC series.
C5JFR36C1104...........................  L114HC series.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD is prompted by a report of a significant crack in a 
propeller blade shank and two reports of cracks in the hubs of the 
same propeller model. We are issuing this AD to detect cracks in the 
propeller blade shank that could cause a failure of the propeller 
blade and loss of control of the airplane.

Compliance

    (e) You must perform the actions within the compliance times 
specified in this AD unless the actions have already been done.

Fluorescent Penetrant Inspection (FPI) of Propeller Blades

    (f) Fluorescent-penetrant inspect the propeller blade using the 
procedures specified in 3.A. through 3.I. of McCauley Alert Service 
Bulletin (ASB) ASB246B, Revision 2, dated July 11, 2003, and the 
compliance times specified in the following Table 2:

         Table 2.--Compliance Times for FPI of Propeller Blades
------------------------------------------------------------------------
If the propeller blade time-
    since-new (TSN) is--             Or if--           Then inspect--
------------------------------------------------------------------------
(1) 10,000 hours TSN or more  The blade was         Within 50 hours time-
                               overhauled at least   in-service (TIS)
                               twice.                after the effective
                                                     date of this AD.
(2) 10,000 hours TSN or more  The blade was         Within 250 hours TIS
 and the blade has been        overhauled at least   after the effective
 overhauled within the last    twice, and the last   date of this AD.
 200 hours TIS before the      overhaul was within
 effective date of this AD.    the last 200 hours
                               TIS before the
                               effective date of
                               this AD.
(3) 6,000 hours TSN or more.  The blade was         Within 200 hours TIS
                               overhauled at least   after the effective
                               once.                 date of this AD.
(4) Fewer than 6,000 TSN....  The blade has not     At the next
                               been overhauled.      overhaul.
------------------------------------------------------------------------

Reporting Requirements

    (g) The Office of Management and Budget (OMB) has approved the 
reporting requirements specified in 3.H. of McCauley ASB ASB246B, 
Revision 2, dated July 11, 2003, and assigned OMB control number 
2120-0056.

Alternative Methods of Compliance (AMOCs)

    (h) You must request AMOCs as specified in 14 CFR 39.19. All 
AMOCs must be

[[Page 42246]]

approved by the Manager, Chicago Aircraft Certification Office, FAA.

Material Incorporated by Reference

    (i) You must use McCauley Propeller Systems, Inc., Alert Service 
Bulletin ASB246B, Revision 2, dated July 11, 2003, to perform the 
FPI. The Director of the Federal Register approved the incorporation 
by reference of this service bulletin in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51. You may get a copy from McCauley Propeller 
Systems, 3535 McCauley Drive, Vandalia, OH 45377. You may review 
copies 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.

Related Information

    (j) None.

    Issued in Burlington, Massachusetts, on July 14, 2003.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 03-18236 Filed 7-15-03; 12:42 pm]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T04:12:04.297710+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

220accd1aafa2dac4a4a85d7e4b4bbb9caab6a5556efc49138259d15d1f2f579

Text SHA-256

d9c9580fe55d4e92cf6059832369a8f5cab0a7dd5305df6e2f2332bc36d42630