[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 [www.gpo.gov]
[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.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Fax: (202) 493-2251.
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 http://dms.dot.gov, 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
http://dms.dot.gov.
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
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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
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(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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
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