AD 2006-22-12

[Federal Register Volume 71, Number 208 (Friday, October 27, 2006)]
[Rules and Regulations]
[Pages 62899-62902]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: E6-17925]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25841; Directorate Identifier 86-ANE-7; Amendment 
39-14809; AD 2006-22-12]
RIN 2120-AA64


Airworthiness Directives; Hartzell Propeller Inc. Model HC-B5MP-
3( )/M10282A( )+6 and HC-B5MP-3( )/M10876( )( )( )( ) Five-Bladed 
Propellers.

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

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for Hartzell Propeller Inc. model HC-B5MP-3( )/M10282A( )+6 five-
bladed propellers. That AD currently requires initial and repetitive 
torque check inspections on the mounting bolts on certain model 
Hartzell Propeller Inc. HC-B5MP-3( )/M10282A( )+6 five-bladed 
propellers, replacement of mounting bolts if necessary, and inspection 
and resurfacing of the engine and propeller mounting flanges if 
necessary. This AD requires the same actions but requires more detailed 
overhaul inspections and maintenance than the previous AD, AD 2004-21-
01. This AD also adds Hartzell Propeller Inc. HC-B5MP-3( )/M10876( )( 
)( )( ) five-bladed propellers to the applicability. This AD results 
from reports of fretting wear still occurring between the engine and 
propeller mounting flanges. The fretting wear results in loss of 
mounting bolt preload, causing failure of the mounting bolts. We are 
issuing this AD to prevent propeller separation from the airplane.

DATES: Effective November 13, 2006. The Director of the Federal 
Register approved the incorporation by reference of certain 
publications listed in the regulations as of November 13, 2006.
    We must receive any comments on this AD by December 26, 2006.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.
    <bullet> DOT Docket Web site: Go to <a href="http://dms.dot.gov">http://dms.dot.gov</a> and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide rulemaking Web site: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a> and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
    <bullet> Fax: (202) 493-2251.
    <bullet> Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Hartzell Propeller Inc. Technical Publications Department, 
One Propeller Place, Piqua, OH 45356; telephone (937) 778-4200; fax 
(937) 778-4391, for the service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Tim Smyth, Aerospace Engineer, Chicago 
Aircraft Certification Office, FAA, Small Airplane Directorate, 2300 
East Devon Avenue, Des Plaines, IL 60018; telephone: (847) 294-7132; 
fax: (847) 294-7834.

SUPPLEMENTARY INFORMATION: On October 4, 2004, the FAA issued AD 2004-
21-01, Amendment 39-13822 (69 FR 62179, October 25, 2004). That AD 
requires initial and repetitive torque check inspections on the 
mounting bolts on certain model Hartzell Propeller Inc. model HC-B5MP-
3( )/M10282A( )+6 five-bladed propellers, and replacement of mounting 
bolts if necessary. That AD also reduces compliance time from the 
previous AD, for the initial inspection on certain Short Brothers Ltd. 
Model SD3-30 airplanes to before further flight and within 100 hours 
time-in-service for propellers installed on certain Aerospatiale (Nord) 
Model 262A airplanes. That AD also requires repetitive torque check 
inspections of

[[Page 62900]]

mounting bolts at reduced intervals from the previous AD, on Model SD3-
30 airplanes, and requires additional visual inspections of mounting 
flanges, threads in hub bolt holes, and replacement of mounting bolts 
and hubs, if necessary. That AD resulted from four reports in the 
previous 12 months of eleven cracked or failed propeller mounting bolts 
on Short Brothers Model SD3-30 airplanes. That condition, if not 
corrected, could result in propeller separation from the airplane.

Actions Since AD 2004-21-01 Was Issued

    Since AD 2004-21-01 was issued, Hartzell Propeller Inc. reviewed 
the propeller mounting flange loads for all similar installations, 
including airplanes listed in Hartzell Propeller Inc. Alert Service 
Bulletin (SB) No. A203A, which is incorporated by reference in the 
previous AD, AD 2004-21-01. Hartzell Propeller Inc. has now addressed 
all of the propeller models on affected airplanes in a later service 
bulletin, including those airplanes that generate higher propeller 
loads during normal flight operations.

Relevant Service Information

    We have reviewed and approved the technical contents of Hartzell 
Propeller Inc. SB No. HC-SB-61-275, dated June 2, 2005. That SB 
describes procedures for performing initial and repetitive torque 
inspections of propeller mounting bolts, initial and repetitive 
inspections of the propeller mounting flange and engine mounting 
flange, and resurfacing of the flanges if necessary.

FAA's Determination and Requirements of This AD

    The unsafe condition described previously is likely to exist or 
develop on other Hartzell Propeller Inc. model HC-B5MP-3( )/M10282A( 
)+6 and HC-B5MP-3( )/M10876( )( )( )( ) five-bladed propellers of the 
same type design. We are issuing this AD to prevent propeller 
separation from the airplane. This AD requires more detailed overhaul 
inspections and maintenance than the previous AD, AD 2004-21-01, for 
the airplane installations listed under paragraph (c) of this AD. This 
AD requires initial and repetitive torque inspections of propeller 
mounting bolts, and initial and repetitive inspections of the propeller 
mounting flange and engine mounting flange, and resurfacing the flanges 
if necessary. You must use the service information described previously 
to perform the actions required by this AD.

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.

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 send us any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. FAA-2006-25841; 
Directorate Identifier 86-ANE-7'' in the subject line of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of the rule that might suggest a need 
to modify it.
    We will post all comments we receive, without change, to <a href="http://dms.dot.gov">http://dms.dot.gov</a>, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. Using the search function of the DMS Web 
site, anyone can find and read the comments in any of our dockets, 
including 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) or you may visit 
<a href="http://dms.dot.gov">http://dms.dot.gov</a>.

Docket Number Change

    We are transferring the docket for this AD to the Docket Management 
System as part of our on going docket management consolidation efforts. 
The new Docket No. is FAA-2006-25841. The old Docket No. became the 
Directorate Identifier, which is 86-ANE-7. This final rule might get 
logged into the DMS docket, ahead of the previously collected documents 
from the old docket file, as we are in the process of sending those 
items to the DMS.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the Docket Management 
Facility Docket Office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Office (telephone (800) 
647-5227) is located on the plaza level of the Department of 
Transportation Nassif Building at the street address stated in 
ADDRESSES. Comments will be available in the AD docket shortly after 
the DMS receives them.

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 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.

List of Subjects in 14 CFR Part 39

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

[[Page 62901]]

Adoption of the Amendment

    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 removing Amendment 39-13822 (69 FR 
62179, October 25, 2004), and by adding a new airworthiness directive, 
Amendment 39-14809, to read as follows:
2006-22-12 Hartzell Propeller Inc. (formerly Hartzell Propeller 
Products Division): Amendment 39-14809. Docket No. FAA-2006-25841; 
Directorate Identifier 86-ANE-7.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
13, 2006.

Affected ADs

    (b) This AD supersedes AD 2004-21-01.

Applicability

    (c) This AD applies to Hartzell Propeller Inc. model HC-B5MP-3( 
)/M10282A( )+6 and HC-B5MP-3( )/M10876( )( )( )( ) five-bladed 
propellers. These propellers are installed on the following:

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                                                                                            Supplemental type
        Airplane manufacturer                  Model               Propeller/blade             certificate
----------------------------------------------------------------------------------------------------------------
Nord................................  262(A) Frakes (Mohawk).  HC-B5MP-3(A)/            SA2369SW
                                                                M10282A(B)+6.
Short Brothers......................  SD3-30 (Sherpa)........  HC-B5MP-3A/M10282AB+6..
Short Brothers......................  SD3-60.................  HC-B5MP-3C/M10876ASK...
Short Brothers......................  SD3-60-200 (Sherpa)....  HC-B5MP-3C/M10876ANSK..
PZL Mielec..........................  PZL-M18( ) (Dromader)..  HC-B5MP-3C/M10876(A)( )  SA1014GL
----------------------------------------------------------------------------------------------------------------

    (d) The parentheses appearing in the propeller model number 
indicates the presence or absence of an additional letter(s) that 
varies the basic propeller model. This AD still applies regardless 
of whether these letters are present or absent in the propeller 
model designation.

Unsafe Condition

    (e) This AD results from reports of fretting wear still 
occurring between the engine and propeller mounting flanges. The 
fretting wear results in loss of mounting bolt preload, causing 
failure of the mounting bolts. The actions specified in this AD are 
intended to prevent propeller separation from the airplane.

Compliance

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

Bolt Torque Inspections on Mounting Flanges Not Resurfaced

    (g) If on the effective date of this AD, either the propeller 
mounting flange or the engine mounting flange has not been 
resurfaced using either Hartzell Propeller Inc. Alert Service 
Bulletin (SB) No. A203A, dated January 5, 1995, or SB No. HC-SB-61-
275, dated June 2, 2005; and either flange:
    (1) Has 3,000 or more operating hours time-since-new (TSN), 
then:
    (i) Perform a torque inspection of the propeller mounting bolts 
before further flight, if the bolt torque inspection has never been 
done.
    (ii) For bolts last inspected using AD 2004-21-01, perform a 
torque inspection of the propeller mounting bolts within 120 
operating hours from the last inspection, or from the effective date 
of this AD, whichever occurs first, unless already done.
    (2) Has fewer than 3,000 operating hours TSN, then perform a 
torque inspection of the propeller mounting bolts upon reaching 
3,000 operating hours TSN.
    (h) Thereafter, repeat the torque inspections within every 120 
operating hours.
    (i) Use paragraphs 3.A. through 3.A.(4) of the Accomplishment 
Instructions of Hartzell Propeller Inc. SB No. HC-SB-61-275, dated 
June 2, 2005 to do the inspections.
    (j) If the torque of any one bolt is found to be less than 90 
ft-lbs, remove and inspect the propeller, and resurface the flanges 
as necessary.
    (k) Use paragraphs 3.B. through 3.B.(5) of the Accomplishment 
Instructions of Hartzell Propeller Inc. SB No. HC-SB-61-275, dated 
June 2, 2005, to do the inspection and resurfacing. Replace all 
mounting bolts with new mounting bolts.

Bolt Torque Inspections on Mounting Flanges Resurfaced

    (l) If the propeller and engine mounting flanges have been 
resurfaced using either Hartzell Propeller Inc. Alert SB No. A203A, 
dated January 5, 1995, or SB No. HC-SB-61-275, dated June 2, 2005, 
and a fretting disk was not installed, then:
    (1) Within 120 operating hours after reaching 1,500 operating 
hours from the time the flanges were last resurfaced, perform a 
torque inspection of the propeller mounting bolts.
    (2) Thereafter, repeat the torque inspection within every 120 
operating hours.
    (3) Use paragraphs 3.A. through 3.A.(4) of the Accomplishment 
Instructions of Hartzell Propeller Inc. SB No. HC-SB-61-275, dated 
June 2, 2005 to do the inspections.
    (m) If the torque of any one bolt is found to be less than 90 
ft-lbs, remove and inspect the propeller, and resurface the flanges 
as necessary.
    (n) Use paragraphs 3.B. through 3.B.(5) of the Accomplishment 
Instructions of Hartzell Propeller Inc. SB No. HC-SB-61-275, dated 
June 2, 2005 to do the inspection and resurfacing. Replace all 
mounting bolts with new mounting bolts.

Inspection of Propeller and Engine Mounting Flanges

    (o) If the propeller and engine mounting flanges have been 
resurfaced, using either Hartzell Propeller Inc. Alert SB No. A203A, 
dated January 5, 1995, or SB No. HC-SB-61-275, dated June 2, 2005, 
and a fretting disk was installed, then:
    (1) Within 120 operating hours after reaching 1,500 operating 
hours from the time the flanges were last resurfaced, remove the 
propeller, and inspect the propeller and engine mounting flanges. 
Resurface the flanges if necessary and replace the fretting disk.
    (2) Thereafter, remove the propeller and repeat the flange 
inspections within every 1,500 operating hours and replace the 
fretting disk.
    (3) Use paragraphs 3.B. through 3.B.(5) of the Accomplishment 
Instructions of Hartzell Propeller Inc. SB No. HC-SB-61-275, dated 
June 2, 2005 to do the inspection and resurfacing. Replace all 
mounting bolts with new mounting bolts.
    (p) Whenever the propeller is removed from the engine:
    (1) Inspect the propeller and engine mounting flanges and 
resurface the flanges if necessary.
    (2) Use paragraphs 3.B. through 3.B.(5) of the Accomplishment 
Instructions of Hartzell Propeller Inc. SB No. HC-SB-61-275, dated 
June 2, 2005 to do the inspection and resurfacing. Replace all 
mounting bolts with new mounting bolts.
    (q) Whenever a propeller is removed from an engine to be 
installed on an airplane model not listed in this AD:
    (1) Inspect the propeller and engine mounting flanges before 
installation and resurface the flanges if necessary.
    (2) Use paragraphs 3.B. through 3.B.(5) of the Accomplishment 
Instructions of Hartzell Propeller Inc. SB No. HC-SB-61-275, dated 
June 2, 2005 to do the inspection and resurfacing. Replace all 
mounting bolts with new mounting bolts.

[[Page 62902]]

Alternative Methods of Compliance

    (r) The Manager, Chicago 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.

Material Incorporated by Reference

    (s) You must use Hartzell Propeller Inc. SB No. HC-SB-61-275, 
dated June 2, 2005 to perform the actions 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 Hartzell Propeller Inc. Technical 
Publications Department, One Propeller Place, Piqua, OH 45356; 
telephone (937) 778-4200; fax (937) 778-4391, for a copy of this 
service information. 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 National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Burlington, Massachusetts, on October 20, 2006.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E6-17925 Filed 10-26-06; 8:45 am]
BILLING CODE 4910-13-P