Airworthiness Directives; McCauley Propeller Systems Propeller Models B5JFR36C1101/114GCA-0, C5JFR36C1102/L114GCA-0, B5JFR36C1103/114HCA-0, and C5JFR36C1104/L114HCA-0, 3462-3465 [E9-1028]

Download as PDF 3462 Federal Register / Vol. 74, No. 12 / Wednesday, January 21, 2009 / Proposed Rules [FR Doc. E9–948 Filed 1–16–09; 8:45 am] BILLING CODE 6450–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25173; Directorate Identifier 2006–NE–24–AD] RIN 2120–AA64 Airworthiness Directives; McCauley Propeller Systems Propeller Models B5JFR36C1101/114GCA–0, C5JFR36C1102/L114GCA–0, B5JFR36C1103/114HCA–0, and C5JFR36C1104/L114HCA–0 mstockstill on PROD1PC66 with PROPOSALS AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) for McCauley Propeller Systems propeller models B5JFR36C1101/114GCA–0, C5JFR36C1102/L114GCA–0, B5JFR36C1103/114HCA–0, and C5JFR36C1104/L114HCA–0. That AD currently requires initial and repetitive 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. That AD also mandates a life limit for the blades. This proposed AD would require the same inspections, add a visual inspection, and would further reduce the propeller blade life limit. This proposed AD would also require removing blades with more than 10,000 operating hours time-since-new (TSN), before further VerDate Nov<24>2008 16:26 Jan 16, 2009 Jkt 217001 flight. This proposed AD would also require removal from service of all the propeller blades and the propeller hub if one or more propeller blades have been found cracked on a propeller assembly. This proposed AD would also require removing from service all C– 5963 split retainers. This proposed AD results from 8 reports of propeller blades found cracked since May of 2006. We are proposing 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. DATES: We must receive any comments on this proposed AD by March 23, 2009. ADDRESSES: Use one of the following addresses to comment on this proposed AD. • Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. Contact McCauley Propeller Systems, 5800 E. Pawnee, Wichita, KS 67218, telephone (800) 621–7767, for the service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Jeff Janusz, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, Small Airplane Directorate, 1801 Airport Road, Room 100, Wichita, KS 67209; email: jeff.janusz@faa.gov; telephone: (316) 946–4148; fax: (316) 946–4107. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 2006–25173; Directorate Identifier 2006–NE–24–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of the Web site, anyone can find and read the comments in any of our dockets, including, if provided, the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78). Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Discussion The FAA proposes to amend 14 CFR part 39 by superseding AD 2008–08–01, Amendment 39–15453 (73 FR 19971, April 14, 2008). That AD requires initial and repetitive FPI and ECI of propeller blades for cracks, and if any crack indications are found, removing the blade from service. That AD also E:\FR\FM\21JAP1.SGM 21JAP1 EP21JA09.125</GPH> 3.5.3.4 Wireless Control Signal. The power supplied to a ballast using a wireless signal is not easily measured, but is estimated to be well below 1.0 watt. Therefore, the wireless control signal power is not measured as part of this test procedure. Federal Register / Vol. 74, No. 12 / Wednesday, January 21, 2009 / Proposed Rules mandates a life limit for the blades. That condition, if not corrected, could result in failure and separation of the propeller blade and loss of control of the airplane. Actions Since AD 2008–08–01 Was Issued Since that AD was issued, propeller blades have cracked below the current 10,000 hour TSN life limit of the propeller blade. The cracks have all been found in the blade retention groove, near the ledge where the split retainers seat, on or near the shot peened area of the propeller blade retention groove. All cracked propeller blades have been found on propeller assemblies that are installed on Jetstream 41 airplanes operated by South African Airlink. All propeller blades that have been found cracked are part number L114HCA, which are installed in the propeller assembly on the No. 2 (right-side) engine. This propeller rotates counter-clockwise when viewed from the rear, on the Jetstream 41 airplane. To date, there have been no other field reports of the same condition as described above, or occurrences of propeller blade failure and separation attributed to this particular unsafe condition. We have not yet determined if the blade cracking is the result of a design issue, an operational issue, or a combination of the two. mstockstill on PROD1PC66 with PROPOSALS Relevant Service Information We have reviewed and approved the technical contents of McCauley Propellers Alert Service Bulletin (ASB) No. ASB255A, dated October 6, 2008. That ASB: • Describes procedures for an FPI and ECI of propeller blades for cracks; • Describes procedures for a visual inspection of the blade shank for a step condition; • Reduces the propeller blade life limit to 3,500 hours TSN; • Removes from service all the propeller blades and the propeller hub if one or more propeller blades have been found cracked on a propeller assembly; and • Removes from service all C–5963 split retainers. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design. For that reason, we are proposing this AD, which would require an FPI and ECI of propeller blades for cracks, would visually inspect the blade shank for a step condition, and would VerDate Nov<24>2008 16:26 Jan 16, 2009 Jkt 217001 reduce the propeller blade life limit to 3,500 hours TSN. This proposed AD would also require removing blades with more than 10,000 operating hours TSN, before further flight. This proposed AD would also require removal from service of all the propeller blades and the propeller hub if one or more propeller blades have been found cracked on a propeller assembly. This proposed AD would also require removing from service all C–5963 split retainers at time of next inspection. The proposed AD would require that you do these actions using the service information described previously. Interim Action These actions are interim actions and we may take further rulemaking actions in the future. Costs of Compliance We estimate that this proposed AD would affect 8 propeller assemblies installed on airplanes of U.S. registry. We estimate that it would take about 44 work-hours per propeller to perform the proposed required actions, and that the average labor rate is $80 per work-hour. Required parts would cost about $260 per propeller, if no cracks are found. We estimate that one propeller will fail the blade inspection required by this proposed AD, and the propeller replacement cost would be about $67,067. Prorated life lost for the propeller assembly would cost about $39,043 per propeller. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $370,608. 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. PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 3463 Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed AD: 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. Would 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 regulatory evaluation of the estimated costs to comply with this proposed AD. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Under the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–15453 (73 FR 19971, April 14, 2008) and by adding a new airworthiness directive to read as follows: McCauley Propeller Systems : Docket No. FAA–2006–25173; Directorate Identifier 2006–NE–24–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by March 23, 2009. Affected ADs (b) This AD supersedes AD 2008–08–01, Amendment 39–15453. Applicability (c) This AD applies to McCauley Propeller Systems propeller models B5JFR36C1101/ 114GCA–0, C5JFR36C1102/L114GCA–0, E:\FR\FM\21JAP1.SGM 21JAP1 3464 Federal Register / Vol. 74, No. 12 / Wednesday, January 21, 2009 / Proposed Rules date of this AD, remove the propeller blades upon reaching 3,500 operating hours TSN. 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). Removal From Service of Propeller Blades and Hubs From Propeller Assemblies That Already Had One or More Cracked Propeller Blades Unsafe Condition (d) This AD results from 8 reports of propeller blades found cracked since May of 2006. 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. 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 Reduction (f) For propeller blades with more than 10,000 operating hours time-since-new (TSN) on the effective date of this AD, remove the propeller blades before further flight. (g) For propeller blades with more than 3,000 operating hours TSN on the effective date of this AD, remove the propeller blades within the next 500 operating hours. (h) For propeller blades with 3,000 or fewer operating hours TSN on the effective (i) Remove the serial number (SN) propeller blades and the hubs listed in Table 1 of this AD from service, using the inspection compliance schedule in Table 2 of this AD. These blades and hubs were installed on propeller assemblies that already had one or more propeller blades removed due to cracking, but at that time those blades and hubs were not required to be removed from service. Table 1 only represents propeller assemblies that were reported to have cracked blades. There may be other propeller assemblies affected that we have not received reports on. TABLE 1—PROPELLER BLADE AND HUB SNS REQUIRING REMOVAL FROM SERVICE AT NEXT INSPECTION— Continued Hub SN Blade SNs 040296 ..... YA31058, YA31055, YB31084, YB31088, YB31090. XB31009, XB31073, XA31071, XA31063, WK31013. XH31018, XH31077, XH31081, XL31008, XL31043. XG31015, XG31016, XH31113, XH31117, XI31017. XI31049, XH31140, XH31129, XH31084, XH31074. WF31010, WD31032, WF31002, WF31029, WF31078. 041016 ..... 051193 ..... 040282 ..... 051204 ..... 051194 ..... Propeller Blade Inspection (j) Perform a TABLE 1—PROPELLER BLADE AND HUB inspection and fluorescent penetrant of the eddy current inspection SNS REQUIRING REMOVAL FROM propeller blades, and a visual inspection for SERVICE AT NEXT INSPECTION ‘‘step condition’’ of the blade shank. Use the Equipment Required and Accomplishment Instructions of McCauley Propellers Alert Hub SN Blade SNs Service Bulletin (ASB) No. ASB255A, dated 023062 ..... XH31043, XH31131, XE31002, October 6, 2008, and the compliance XH31025, XI31014. schedule in Table 2 of this AD: TABLE 2—INSPECTION COMPLIANCE SCHEDULE If on the effective date of this AD, the propeller blade: Then inspect the propeller blade: (1) Has more than 2,400 operating hours TSN, time-since-last inspection (TSLI), or time-since-overhaul (TSO) and has been inspected using AD 2008–08–01 or McCauley Propellers ASB No. ASB255, dated January 8, 2007 within the past 2,400 operating hours. (2) Has more than 2,400 operating hours TSN, TSLI, or TSO and has not been inspected using AD 2008–08–01 or McCauley Propellers ASB No. ASB255, dated January 8, 2007 within the past 2,400 operating hours. (3) Has 2,400 or fewer operating hours TSN, TSLI, or TSO ................... Upon reaching 2,500 operating hours TSLI. See TSLI definition paragraph (o) of this AD. Propellers Failing Blade Inspection mstockstill on PROD1PC66 with PROPOSALS (k) Remove from service all of the propeller blades, and the propeller hub, if one or more propeller blades are found cracked on a propeller assembly. Propeller blades and the propeller hub of a propeller assembly that has one or more cracked propeller blades, are no longer eligible for installation in any configuration. Do not install them in any configuration on any airframe. (l) Remove from service all propeller blades that exhibit a blade shank ‘‘step condition’’ of 0.005-inch or greater. Blades removed from service are no longer eligible for installation in any configuration. Do not install them in any configuration on any airframe. Removal of C–5963 Split Retainers From Service (m) Remove from service all C–5963 split retainers at the time of blade inspection specified in paragraph (i) of this AD. C–5963 split retainers removed from service are no longer eligible for installation in any configuration. Do not install them in any configuration on any airframe. VerDate Nov<24>2008 16:26 Jan 16, 2009 Jkt 217001 Within the next 100 operating hours time-in-service. Upon reaching 2,500 operating hours TSN, TSLI, or TSO. (n) After the effective date of this AD, propeller assemblies with C–5963 split retainers, are prohibited from installation on any airframe. Definition (o) For the purpose of this AD, TSLI refers only to inspections performed using AD 2008–08–01 or McCauley ASB No. ASB255, dated January 8, 2007. Reporting Requirements (p) Within 10 calendar days of the inspection, use the Reporting Form in McCauley ASB No. ASB255A, to report all inspection findings to the FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, KS 67209, Attention: Jeff Janusz; telephone (316) 946– 4148; fax (316) 946–4107; e-mail: jeff.janusz@faa.gov. (q) Include any photographs, and any other information related to the means of detection of the crack, and the history of the propeller and blades. (r) The Office of Management and Budget (OMB) has approved the reporting PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 requirements and assigned OMB control number 2120–0056. Alternative Methods of Compliance (s) 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 (t) 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. E:\FR\FM\21JAP1.SGM 21JAP1 Federal Register / Vol. 74, No. 12 / Wednesday, January 21, 2009 / Proposed Rules Related Information (u) 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. Issued in Burlington, Massachusetts, on January 12, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–1028 Filed 1–16–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2008–1170; Airspace Docket No. 08–AEA–27] Proposed Amendment of the Atlantic Low Offshore Airspace Area; East Coast United States mstockstill on PROD1PC66 with PROPOSALS AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: This action proposes to amend the altitude floor of the Atlantic Low Offshore Airspace Area, located off the east coast of the United States (U.S.). The FAA is proposing to lower the floor of the area from 5,500 feet above mean sea level (MSL) to 1,700 feet MSL. This action would provide additional altitudes for air traffic control to vector aircraft on arrival to Atlantic City, NJ, ensuring the safety of aircraft and the efficient use of airspace within the National Airspace System. DATES: Comments must be received on or before March 9, 2009. ADDRESSES: Send comments on the proposal to the U.S. Department of Transportation, Docket Operations, M– 30, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001; telephone: (202) 366–9826. You must identify the docket number FAA–2008–1170 and Airspace Docket No. 08–AEA–27 at the beginning of your comments. You may also submit comments on the Internet at https://www.regulations.gov. FOR FURTHER INFORMATION CONTACT: Paul Gallant, Airspace and Rules Group, Office of System Operations Airspace and AIM, Federal Aviation Administration, 800 Independence Avenue, SW., Washington, DC 20591; telephone: (202) 267–8783. SUPPLEMENTARY INFORMATION: VerDate Nov<24>2008 16:26 Jan 16, 2009 Jkt 217001 Comments Invited Interested parties are invited to participate in this proposed rulemaking by submitting such written data, views, or arguments as they may desire. Comments that provide the factual basis supporting the views and suggestions presented are particularly helpful in developing reasoned regulatory decisions on the proposal. Comments are specifically invited on the overall regulatory, aeronautical, economic, environmental, and energy-related aspects of the proposal. Communications should identify both docket numbers (FAA Docket No. FAA– 2008–1170 and Airspace Docket No. 08– AEA–27) and be submitted in triplicate to the Docket Management Facility (see ADDRESSES section for address and phone number). You may also submit comments through the Internet at https://www.regulations.gov. Commenter’s wishing the FAA to acknowledge receipt of their comments on this action must submit with those comments a self-addressed, stamped postcard on which the following statement is made: ‘‘Comments to FAA Docket No. FAA–2008–1170 and Airspace Docket No. 08–AEA–27.’’ The postcard will be date/time stamped and returned to the commenter. All communications received on or before the specified closing date for comments will be considered before taking action on the proposed rule. The proposal contained in this action may be changed in light of comments received. All comments submitted will be available for examination in the public docket both before and after the closing date for comments. A report summarizing each substantive public contact with FAA personnel concerned with this rulemaking will be filed in the docket. Availability of NPRMs An electronic copy of this document may be downloaded through the Internet at https://www.regulations.gov. Recently published rulemaking documents can also be accessed through the FAA’s Web page at https:// www.faa.gov/airports_airtraffic/ air_traffic/publications/ airspace_amendments/. You may review the public docket containing the proposal, any comments received and any final disposition in person in the Dockets Office (see ADDRESSES section for address and phone number) between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. An informal docket may also be examined during normal business hours at the office of the PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 3465 Eastern Service Center, Federal Aviation Administration, Room 210, 1701 Columbia Avenue, College Park, Georgia 30337. Persons interested in being placed on a mailing list for future NPRM’s should contact the FAA’s Office of Rulemaking, (202) 267–9677, for a copy of Advisory Circular No. 11–2A, Notice of Proposed Rulemaking Distribution System, which describes the application procedure. The Proposal The FAA is proposing an amendment to Title 14 Code of Federal Regulations (14 CFR) part 71 to modify the designated altitude floor of the Atlantic Low Offshore Airspace Area. The proposed change would lower the floor of the area from 5,500 feet MSL to 1,700 feet MSL. Currently, Air Traffic Control (ATC) cannot vector arriving aircraft below 5,500 feet MSL while operating within the Atlantic Low Offshore Airspace Area. The proposed change would provide additional controlled airspace so that ATC could use lower altitudes while vectoring aircraft on arrival to Atlantic City, NJ. The change would increase ATC system efficiency and reduce complexity at Atlantic City. Offshore airspace areas are published in paragraph 6007, of FAA Order 7400.9S signed October 3, 2008, and effective October 31, 2008, which is incorporated by reference in 14 CFR 71.1. The offshore airspace area listed in this document will be published subsequently in the Order. The FAA has determined that this proposed regulation only involves an established body of technical regulations for which frequent and routine amendments are necessary to keep them operationally current. Therefore, this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) is not a ‘‘significant rule’’ under Department of Transportation (DOT) Regulatory Policies and Procedures (44 FR 11034; February 26, 1979); and (3) does not warrant preparation of a regulatory evaluation as the anticipated impact is so minimal. Since this is a routine matter that will only affect air traffic procedures and air navigation, it is certified that this proposed rule, when promulgated, will not have a significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. The FAA’s authority to issue rules regarding aviation safety is found in Title 49 of the United States Code. Subtitle I, Section 106 describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, E:\FR\FM\21JAP1.SGM 21JAP1

Agencies

[Federal Register Volume 74, Number 12 (Wednesday, January 21, 2009)]
[Proposed Rules]
[Pages 3462-3465]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-1028]


=======================================================================
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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]
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: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) for McCauley Propeller Systems propeller models 
B5JFR36C1101/114GCA-0, C5JFR36C1102/L114GCA-0, B5JFR36C1103/114HCA-0, 
and C5JFR36C1104/L114HCA-0. That AD currently requires initial and 
repetitive 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. That AD also 
mandates a life limit for the blades. This proposed AD would require 
the same inspections, add a visual inspection, and would further reduce 
the propeller blade life limit. This proposed AD would also require 
removing blades with more than 10,000 operating hours time-since-new 
(TSN), before further flight. This proposed AD would also require 
removal from service of all the propeller blades and the propeller hub 
if one or more propeller blades have been found cracked on a propeller 
assembly. This proposed AD would also require removing from service all 
C-5963 split retainers. This proposed AD results from 8 reports of 
propeller blades found cracked since May of 2006. We are proposing 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.

DATES: We must receive any comments on this proposed AD by March 23, 
2009.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.
     Federal eRulemaking Portal: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue, SE., West Building Ground 
Floor, Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: (202) 493-2251.
    Contact McCauley Propeller Systems, 5800 E. Pawnee, Wichita, KS 
67218, telephone (800) 621-7767, for the service information identified 
in this proposed AD.

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:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2006-25173; 
Directorate Identifier 2006-NE-24-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact 
with FAA personnel concerning this proposed AD. Using the search 
function of the Web site, anyone can find and read the comments in any 
of our dockets, including, if provided, the name of the individual who 
sent the comment (or signed the comment on behalf of an association, 
business, labor union, etc.). You may review the DOT's complete Privacy 
Act Statement in the Federal Register published on April 11, 2000 (65 
FR 19477-78).

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
the same as the Mail address provided in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

Discussion

    The FAA proposes to amend 14 CFR part 39 by superseding AD 2008-08-
01, Amendment 39-15453 (73 FR 19971, April 14, 2008). That AD requires 
initial and repetitive FPI and ECI of propeller blades for cracks, and 
if any crack indications are found, removing the blade from service. 
That AD also

[[Page 3463]]

mandates a life limit for the blades. That condition, if not corrected, 
could result in failure and separation of the propeller blade and loss 
of control of the airplane.

Actions Since AD 2008-08-01 Was Issued

    Since that AD was issued, propeller blades have cracked below the 
current 10,000 hour TSN life limit of the propeller blade. The cracks 
have all been found in the blade retention groove, near the ledge where 
the split retainers seat, on or near the shot peened area of the 
propeller blade retention groove. All cracked propeller blades have 
been found on propeller assemblies that are installed on Jetstream 41 
airplanes operated by South African Airlink. All propeller blades that 
have been found cracked are part number L114HCA, which are installed in 
the propeller assembly on the No. 2 (right-side) engine. This propeller 
rotates counter-clockwise when viewed from the rear, on the Jetstream 
41 airplane. To date, there have been no other field reports of the 
same condition as described above, or occurrences of propeller blade 
failure and separation attributed to this particular unsafe condition. 
We have not yet determined if the blade cracking is the result of a 
design issue, an operational issue, or a combination of the two.

Relevant Service Information

    We have reviewed and approved the technical contents of McCauley 
Propellers Alert Service Bulletin (ASB) No. ASB255A, dated October 6, 
2008. That ASB:
     Describes procedures for an FPI and ECI of propeller 
blades for cracks;
     Describes procedures for a visual inspection of the blade 
shank for a step condition;
     Reduces the propeller blade life limit to 3,500 hours TSN;
     Removes from service all the propeller blades and the 
propeller hub if one or more propeller blades have been found cracked 
on a propeller assembly; and
     Removes from service all C-5963 split retainers.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other products 
of this same type design. For that reason, we are proposing this AD, 
which would require an FPI and ECI of propeller blades for cracks, 
would visually inspect the blade shank for a step condition, and would 
reduce the propeller blade life limit to 3,500 hours TSN. This proposed 
AD would also require removing blades with more than 10,000 operating 
hours TSN, before further flight. This proposed AD would also require 
removal from service of all the propeller blades and the propeller hub 
if one or more propeller blades have been found cracked on a propeller 
assembly. This proposed AD would also require removing from service all 
C-5963 split retainers at time of next inspection. The proposed AD 
would require that you do these actions using the service information 
described previously.

Interim Action

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

Costs of Compliance

    We estimate that this proposed AD would affect 8 propeller 
assemblies installed on airplanes of U.S. registry. We estimate that it 
would take about 44 work-hours per propeller to perform the proposed 
required actions, and that the average labor rate is $80 per work-hour. 
Required parts would cost about $260 per propeller, if no cracks are 
found. We estimate that one propeller will fail the blade inspection 
required by this proposed AD, and the propeller replacement cost would 
be about $67,067. Prorated life lost for the propeller assembly would 
cost about $39,043 per propeller. Based on these figures, we estimate 
the total cost of the proposed AD to U.S. operators to be $370,608.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed AD:
    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. Would 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 regulatory evaluation of the estimated costs to 
comply with this proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Under the authority delegated to me by the Administrator, the 
Federal Aviation Administration proposes to amend 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. The FAA amends Sec.  39.13 by removing Amendment 39-15453 (73 FR 
19971, April 14, 2008) and by adding a new airworthiness directive to 
read as follows:

McCauley Propeller Systems : Docket No. FAA-2006-25173; Directorate 
Identifier 2006-NE-24-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by March 23, 
2009.

Affected ADs

    (b) This AD supersedes AD 2008-08-01, Amendment 39-15453.

Applicability

    (c) This AD applies to McCauley Propeller Systems propeller 
models B5JFR36C1101/114GCA-0, C5JFR36C1102/L114GCA-0,

[[Page 3464]]

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 8 reports of propeller blades found 
cracked since May of 2006. 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.

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 Reduction

    (f) For propeller blades with more than 10,000 operating hours 
time-since-new (TSN) on the effective date of this AD, remove the 
propeller blades before further flight.
    (g) For propeller blades with more than 3,000 operating hours 
TSN on the effective date of this AD, remove the propeller blades 
within the next 500 operating hours.
    (h) For propeller blades with 3,000 or fewer operating hours TSN 
on the effective date of this AD, remove the propeller blades upon 
reaching 3,500 operating hours TSN.

Removal From Service of Propeller Blades and Hubs From Propeller 
Assemblies That Already Had One or More Cracked Propeller Blades

    (i) Remove the serial number (SN) propeller blades and the hubs 
listed in Table 1 of this AD from service, using the inspection 
compliance schedule in Table 2 of this AD. These blades and hubs 
were installed on propeller assemblies that already had one or more 
propeller blades removed due to cracking, but at that time those 
blades and hubs were not required to be removed from service. Table 
1 only represents propeller assemblies that were reported to have 
cracked blades. There may be other propeller assemblies affected 
that we have not received reports on.

 Table 1--Propeller Blade and Hub SNs Requiring Removal From Service at
                             Next Inspection
------------------------------------------------------------------------
              Hub SN                              Blade SNs
------------------------------------------------------------------------
023062............................  XH31043, XH31131, XE31002, XH31025,
                                     XI31014.
040296............................  YA31058, YA31055, YB31084, YB31088,
                                     YB31090.
041016............................  XB31009, XB31073, XA31071, XA31063,
                                     WK31013.
051193............................  XH31018, XH31077, XH31081, XL31008,
                                     XL31043.
040282............................  XG31015, XG31016, XH31113, XH31117,
                                     XI31017.
051204............................  XI31049, XH31140, XH31129, XH31084,
                                     XH31074.
051194............................  WF31010, WD31032, WF31002, WF31029,
                                     WF31078.
------------------------------------------------------------------------

Propeller Blade Inspection

    (j) Perform a fluorescent penetrant inspection and eddy current 
inspection of the propeller blades, and a visual inspection for 
``step condition'' of the blade shank. Use the Equipment Required 
and Accomplishment Instructions of McCauley Propellers Alert Service 
Bulletin (ASB) No. ASB255A, dated October 6, 2008, and the 
compliance schedule in Table 2 of this AD:

                 Table 2--Inspection Compliance Schedule
------------------------------------------------------------------------
  If on the effective date of this AD,      Then inspect the propeller
          the propeller blade:                        blade:
------------------------------------------------------------------------
(1) Has more than 2,400 operating hours  Upon reaching 2,500 operating
 TSN, time-since-last inspection          hours TSLI. See TSLI
 (TSLI), or time-since-overhaul (TSO)     definition paragraph (o) of
 and has been inspected using AD 2008-    this AD.
 08-01 or McCauley Propellers ASB No.
 ASB255, dated January 8, 2007 within
 the past 2,400 operating hours.
(2) Has more than 2,400 operating hours  Within the next 100 operating
 TSN, TSLI, or TSO and has not been       hours time-in-service.
 inspected using AD 2008-08-01 or
 McCauley Propellers ASB No. ASB255,
 dated January 8, 2007 within the past
 2,400 operating hours.
(3) Has 2,400 or fewer operating hours   Upon reaching 2,500 operating
 TSN, TSLI, or TSO.                       hours TSN, TSLI, or TSO.
------------------------------------------------------------------------

Propellers Failing Blade Inspection

    (k) Remove from service all of the propeller blades, and the 
propeller hub, if one or more propeller blades are found cracked on 
a propeller assembly. Propeller blades and the propeller hub of a 
propeller assembly that has one or more cracked propeller blades, 
are no longer eligible for installation in any configuration. Do not 
install them in any configuration on any airframe.
    (l) Remove from service all propeller blades that exhibit a 
blade shank ``step condition'' of 0.005-inch or greater. Blades 
removed from service are no longer eligible for installation in any 
configuration. Do not install them in any configuration on any 
airframe.

Removal of C-5963 Split Retainers From Service

    (m) Remove from service all C-5963 split retainers at the time 
of blade inspection specified in paragraph (i) of this AD. C-5963 
split retainers removed from service are no longer eligible for 
installation in any configuration. Do not install them in any 
configuration on any airframe.
    (n) After the effective date of this AD, propeller assemblies 
with C-5963 split retainers, are prohibited from installation on any 
airframe.

Definition

    (o) For the purpose of this AD, TSLI refers only to inspections 
performed using AD 2008-08-01 or McCauley ASB No. ASB255, dated 
January 8, 2007.

Reporting Requirements

    (p) Within 10 calendar days of the inspection, use the Reporting 
Form in McCauley ASB No. ASB255A, to report all inspection findings 
to the FAA, Wichita Aircraft Certification Office, 1801 Airport 
Road, Room 100, Wichita, KS 67209, Attention: Jeff Janusz; telephone 
(316) 946-4148; fax (316) 946-4107; e-mail: jeff.janusz@faa.gov.
    (q) Include any photographs, and any other information related 
to the means of detection of the crack, and the history of the 
propeller and blades.
    (r) The Office of Management and Budget (OMB) has approved the 
reporting requirements and assigned OMB control number 2120-0056.

Alternative Methods of Compliance

    (s) 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

    (t) 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.

[[Page 3465]]

Related Information

    (u) 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.

    Issued in Burlington, Massachusetts, on January 12, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-1028 Filed 1-16-09; 8:45 am]
BILLING CODE 4910-13-P
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