
[Federal Register: April 14, 2008 (Volume 73, Number 72)]
[Rules and Regulations]               
[Page 19971-19972]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14ap08-6]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25173; Directorate Identifier 2006-NE-24-AD; 
Amendment 39-15453; AD 2008-08-01]
RIN 2120-AA64

 
Airworthiness Directives; McCauley Propeller Systems Propeller 
Models B5JFR36C1101/114GCA-0, C5JFR36C1102/L114GCA-0, B5JFR36C1103/
114HCA-0, and C5JFR36C1104/L114HCA-0

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is superseding three existing airworthiness directives 
(ADs) for McCauley Propeller Systems propeller models B5JFR36C1101/
114GCA-0, C5JFR36C1102/L114GCA-0, B5JFR36C1103/114HCA-0, and 
C5JFR36C1104/L114HCA-0. Those ADs currently require fluorescent 
penetrant inspections (FPI) and eddy current inspections (ECI) of 
propeller blades for cracks, and if any crack indications are found, 
removing the blade from service. This AD requires the same initial 
inspections, but extends the compliance times and intervals, adds 
repetitive inspections, and mandates a life limit for the blades. This 
AD results from our determination that we must require repetitive 
inspections for cracks, and from reports of blunt leading edges of the 
propeller blades due to erosion. We are issuing this AD to detect 
cracks in the propeller blade that could cause failure and separation 
of the propeller blade and loss of control of the airplane, and to 
detect blunt leading edges on the propeller blades, which could cause 
airplane single engine climb performance degradation and could result 
in an increased risk of collision with terrain.

DATES: This AD becomes effective May 19, 2008. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of May 19, 2008.

ADDRESSES: You can get the service information identified in this AD 
from McCauley Propeller Systems, P.O. Box 7704, Wichita, KS 67277-7704, 
telephone (800) 621-7767.
    The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

FOR FURTHER INFORMATION CONTACT: Jeff Janusz, Aerospace Engineer, 
Wichita Aircraft Certification Office, FAA, Small Airplane Directorate, 
1801 Airport Road, Room 100, Wichita, KS 67209; e-mail: 
jeff.janusz@faa.gov; telephone: (316) 946-4148; fax: (316) 946-4107.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 by 
superseding AD 2003-15-01, Amendment 39-13243 (68 FR 42244, July 17, 
2003); AD 2003-17-10, Amendment 39-13285 (68 FR 50462, August 21, 
2003); and AD 2006-15-13, Amendment 39-14693 (71 FR 42258, July 26, 
2006), with a proposed AD. The proposed AD applies to McCauley 
Propeller Systems propeller models B5JFR36C1101/114GCA-0, C5JFR36C1102/
L114GCA-0, B5JFR36C1103/114HCA-0, and C5JFR36C1104/L114HCA-0. We 
published the proposed AD in the Federal Register on November 1, 2007 
(72 FR 61824). That action proposed to require the same initial 
inspections as the three ADs being superseded, but to extend the 
compliance times and intervals, to add repetitive inspections, and to 
mandate a life limit for the blades.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is provided in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the one comment received. 
The commenter supports the proposal. We also found we needed to clarify 
that blades that had crack indications were no longer eligible for 
installation on any other airframe or in any other configuration. We 
clarified the AD on the point.

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD as proposed.

Costs of Compliance

    We estimate that this AD will affect 22 propeller assemblies 
installed on airplanes of U.S. registry. We estimate that it will take 
about 47 work-hours per propeller to perform the required actions, and 
that the average labor rate is $80 per work-hour. Required parts will 
cost about $260 per propeller. Based on these figures, we estimate the 
total cost of the AD to U.S. operators to be $88,440.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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

[[Page 19972]]

the AD Docket. You may get a copy of this summary at the address listed 
under ADDRESSES.

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 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 removing Amendment 39-13243 (68 FR 
42244, July 17, 2003), Amendment 39-13285 (68 FR 50462, August 21, 
2003), and Amendment 39-14693 (71 FR 42258, July 26, 2006), and by 
adding a new airworthiness directive, Amendment 39-15453, to read as 
follows:

2008-08-01 McCauley Propeller Systems: Amendment 39-15453. Docket 
No. FAA-2006-25173; Directorate Identifier 2006-NE-24-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective May 19, 
2008.

Affected ADs

    (b) This AD supersedes AD 2003-15-01, Amendment 39-13243; AD 
2003-17-10, Amendment 39-13285; and AD 2006-15-13, Amendment 39-
14693.

Applicability

    (c) This AD applies to McCauley Propeller Systems propeller 
models B5JFR36C1101/114GCA-0, C5JFR36C1102/L114GCA-0, B5JFR36C1103/
114HCA-0, and C5JFR36C1104/L114HCA-0. These propellers are installed 
on BAE Systems (Operations) Limited Jetstream Model 4100 and 4101 
series airplanes (Jetstream 41).

Unsafe Condition

    (d) This AD results from our determination that we must require 
repetitive inspections for cracks, and from reports of blunt leading 
edges of the propeller blades due to erosion. We are issuing this AD 
to detect cracks in the propeller blade that could cause failure and 
separation of the propeller blade and loss of control of the 
airplane, and to detect blunt leading edges on the propeller blades, 
which could cause airplane single engine climb performance 
degradation and could result in an increased risk of collision with 
terrain.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

Life Limit

    (f) Remove all 114GCA-0, L114GCA-0, 114HCA-0, and L114HCA-0 
propeller blades upon reaching 10,000 operating hours time-since-
new.

Initial Propeller Blade Inspection

    (g) Perform an initial fluorescent penetrant inspection and eddy 
current inspection of propeller blades. Use the Equipment Required 
and Accomplishment Instructions of McCauley Propellers Alert Service 
Bulletin ASB255, dated January 8, 2007, and the following compliance 
schedule:

                      Table 1.--Compliance Schedule
------------------------------------------------------------------------
                                            Then inspect the propeller
        If the propeller blade:                       blade:
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(1) Has more than 2,400 operating hours  Within 100 operating hours time-
 time-since-new (TSN), time-since-last    in-service (TIS) after the
 inspection (TSLI), or time-since-        effective date of this AD.
 overhaul (TSO).
(2) Has 2,400 or fewer operating hours   Upon reaching 2,500 operating
 TSN, TSLI, or TSO.                       hours TSN, TSLI, or TSO.
------------------------------------------------------------------------

Propeller Blades Found Cracked

    (h) Remove from service propeller blades found with any crack 
indications. Blades found with crack indications are no longer 
eligible for installation in any configuration. Do not install them 
in any configuration on any airframe.

Repetitive Propeller Blade Inspection

    (i) Thereafter, inspect the propeller blades within 2,500 
operating hours TSLI or TSO. Use the Equipment Required and 
Accomplishment Instructions of McCauley Propellers Alert Service 
Bulletin ASB255, dated January 8, 2007.

Inspection for Blunt Erosion on the Leading Edge of the Propeller Blade

    (j) Every time the propeller is removed for the inspection for 
cracks, inspect the blade for erosion and, if necessary, repair the 
erosion. The McCauley Propeller Systems Blade Overhaul Manual No., 
BOM 100, contains information on inspecting and repairing erosion on 
the propeller blade.

Reporting Requirements

    (k) Within 10 calendar days of the inspection, use the Reporting 
Form for Service Bulletin 255 to report all inspection findings to 
McCauley Propeller Systems, P.O. Box 7704, Wichita, KS 67277-7704, 
telephone (800) 621-7767.
    (l) The Office of Management and Budget (OMB) has approved the 
reporting requirements and assigned OMB control number 2120-0056.

Alternative Methods of Compliance

    (m) The Manager, Wichita Aircraft Certification Office, has the 
authority to approve alternative methods of compliance for this AD 
if requested using the procedures found in 14 CFR 39.19.

Special Flight Permits

    (n) Under 39.23, we are limiting the availability of special 
flight permits for this AD. Special flight permits are available 
only if:
    (1) The operator has not seen signs of external oil leakage from 
the hub; and
    (2) The operator has not observed abnormal propeller vibration 
or abnormal engine vibration; and
    (3) The operator has not observed any other abnormal operation 
from the propeller; and
    (4) The operator has not made earlier reports of abnormal 
propeller vibration, abnormal engine vibration, or other abnormal 
propeller operations that have not been addressed.

Related Information

    (o) Contact Jeff Janusz, Aerospace Engineer, Wichita Aircraft 
Certification Office, FAA, Small Airplane Directorate, 1801 Airport 
Road, Room 100, Wichita, KS 67209; e-mail: jeff.janusz@faa.gov; 
telephone: (316) 946-4148; fax: (316) 946-4107, for more information 
about this AD.

Material Incorporated by Reference

    (p) You must use the McCauley Propellers Alert Service Bulletin 
ASB255, dated January 8, 2007, to perform the inspections required 
by this AD. 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. Contact McCauley Propeller 
Systems, P.O. Box 7704, Wichita, KS 67277-7704, telephone (800) 621-
7767, for a copy of this service information. You may review copies 
at the FAA, New England Region, 12 New England Executive Park, 
Burlington, MA; or at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://
www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on March 31, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E8-7162 Filed 4-11-08; 8:45 am]

BILLING CODE 4910-13-P
