[Federal Register Volume 69, Number 198 (Thursday, October 14, 2004)]
[Rules and Regulations]
[Pages 60952-60954]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-22728]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 86-ANE-7; Amendment 39-13822; AD 2004-21-01]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is superseding an existing AD for certain Hartzell 
Propeller Inc. (formerly Hartzell Propeller Products Division) Model 
HC-B5MP-3( )/M10282A( )+6 five bladed propellers. That AD currently 
requires initial and repetitive torque check inspections on the attach 
bolts on certain model Hartzell HC-B5MP-3 five bladed propellers, and 
replacement of attach bolts if necessary. This AD requires the same 
inspections, but reduces compliance time 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. This AD also requires 
repetitive torque check inspections at reduced intervals on SD3-30 
airplanes, and requires additional visual inspections of mounting 
flanges, and threads in hub bolt holes, and replacement of attach bolts 
and hubs, if necessary. This AD results from four reports in the last 
12 months of eleven cracked or failed propeller attach bolts on Short 
Brothers Model SD3-30 airplanes. We are issuing this AD to prevent 
propeller separation from the airplane.

DATES: Effective October 19, 2004. The Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulations as of October 19, 2004.
    We must receive any comments on this AD by December 13, 2004.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
    <bullet> By mail: Federal Aviation Administration (FAA), New 
England Region, Office of the Regional Counsel, Attention: Rules Docket 
No. 86-ANE-7, 12 New England Executive Park, Burlington, MA 01803-5299.
    <bullet> By fax: (781) 238-7055.
    <bullet> By e-mail: <a href="/cdn-cgi/l/email-protection" class="__cf_email__" data-cfemail="8ab3a7ebe4efa7ebeee9e5e7e7efe4fecaecebeba4ede5fc">[email protected]</a>.
    You can get the service information referenced in this AD from 
Hartzell Propeller Inc. Technical Publications Department, One 
Propeller Place, Piqua, OH 45356; telephone (937) 778-4200; fax (937) 
778-4391.
    You may examine the AD docket, by appointment, at the FAA, New 
England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA. You may examine the service 
information, by appointment, 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/code--of--
federal--regulations/ibr--locations.html.

FOR FURTHER INFORMATION CONTACT: Tomaso DiPaolo, Aerospace Engineer, 
Chicago Aircraft Certification Office, FAA, Small Airplane Directorate, 
2300 East Devon Avenue, Des Plaines, IL 60018; telephone: (847) 294-
7031; fax: (847) 294-7834.

SUPPLEMENTARY INFORMATION: On March 7, 1986, the FAA issued AD 86-06-
02, Amendment 39-5259 (51 FR 10613, March 28, 1986). That AD requires 
initial and repetitive torque check inspections on the attach bolts on 
certain model Hartzell HC-B5MP-3 five bladed propellers installed on 
Aerospatiale (Nord) Model 262A airplanes modified by Supplemental Type 
Certificate (STC) SA2369SW, and Short Brothers Ltd. Model SD3-30 
airplanes. Some SD3-30 airplanes are military surplus C23-A Sherpas 
airplanes. That AD was the result of investigations that revealed 
fretting wear between the engine and propeller mating flanges. The 
fretting wear results in loss of attach bolt preload, causing failure 
of the attach bolts. That condition, if not corrected, could result in 
propeller separation from the airplane.

Actions Since AD 86-06-02 Was Issued

    Since February 2004, we received four reports of failed propeller 
attach bolts, part number (P/N) B-3339:
    <bullet> In February 2004, an operator reported a cracked Hartzell 
propeller attach bolt. The operator discarded the bolt and we could not 
perform a metallurgical investigation on the bolt.
    <bullet> In June of 2004, another operator reported two broken 
propeller attach bolts. Both bolts were examined and one was selected 
for metallurgical investigation. This bolt was found to meet type 
design.
    <bullet> In September of 2004, the Milwaukee Flight Standards 
District Office informed us that they received an operator's report of 
seven cracked or failed propeller attach bolts. All seven bolts were 
installed on the same propeller, and were found after a pilot reported 
problems with engine controls. We contacted Hartzell for assistance in 
investigating the bolt failure. The propeller hub and engine flange are 
being investigated for fretting, flatness, and thread damage.
    <bullet> In late September of 2004, during the review of the 
maintenance history of one of the above propellers, we found a fourth 
event of a cracked propeller attach bolt.

Relevant Service Information

    We have reviewed and approved the technical contents of Hartzell 
Alert Service Bulletin (ASB) A203A, dated January 5, 1995, that 
describes procedures for performing initial and repetitive inspections 
of attach bolts and if necessary, visual inspections of propeller 
mounting flanges.

[[Page 60953]]

Differences Between This AD and the Service Information

    Although Hartzell ASB A203A, dated January 5, 1995, requires an 
initial torque check inspection within the next 100 hours TIS from the 
effective date of the original bulletin (dated September 2, 1994) for 
Short Brothers Ltd. Model SD3-30 airplanes, this AD requires an initial 
torque check inspection before further flight for SD3-30 airplanes. 
Also, although that ASB requires an initial torque check inspection 
within the next 120 hours TIS from the effective date of the original 
bulletin (September 2, 1994) for Aerospatiale (Nord) Model 262A 
airplanes, this AD requires an initial torque check inspection within 
100 hours TIS for 262A airplanes.

FAA's Determination and Requirements of This AD

    The unsafe condition described previously is likely to exist or 
develop on other Model HC-B5MP-3( )/M10282A( )+6 five bladed propellers 
of the same type design installed on Aerospatiale (Nord) Model 262A 
airplanes modified by STC SA2369SW, and Short Brothers Ltd. Model SD3-
30 airplanes. We are issuing this AD to prevent propeller separation 
from the airplane. This AD requires the following:
    <bullet> Before further flight, performing an initial torque check 
inspection of the propeller attach bolts on Short Brothers Ltd. Model 
SD3-30 airplanes unless already done within the last 120 hours TIS 
before the effective date of this AD; and
    <bullet> Repetitive torque check inspections of the propeller 
attach bolts within 120 hours TIS from the last inspection.
    <bullet> Within 100 hours TIS after the effective date of this AD, 
performing an initial torque check inspection of the propeller attach 
bolts on Aerospatiale (Nord) Model 262A airplanes; and
    <bullet> Repetitive torque check inspections of the propeller 
attach bolts within 100 hours TIS from the last inspection.
    <bullet> If the bolts fail the torque check, then visually inspect 
threads in hub bolt holes, and replace attach bolts and hub 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.

Interim Action

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

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to submit any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. 86-ANE-7'' in the 
subject line of your comments. If you want us to acknowledge receipt of 
your mailed comments, send us a self-addressed, stamped postcard with 
the docket number written on it; we will date-stamp your postcard and 
mail it back to you. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the rule 
that might suggest a need to modify it. If a person contacts us 
verbally, and that contact relates to a substantive part of this AD, we 
will summarize the contact and place the summary in the docket. We will 
consider all comments received by the closing date and may amend the AD 
in light of those comments.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications with you. You may get more information about plain 
language at http://www.faa.gov/language and http://
www.plainlanguage.gov/.

Examining the AD Docket

    You may examine the AD Docket (including any comments and service 
information), by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. See ADDRESSES for the 
location.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national Government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket No. 86-ANE-7'' in your request.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends part 39 of the Federal 
Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Amendment 39-5259 (51 FR 
10613, March 28, 1986), and by adding a new airworthiness directive, 
Amendment 39-XXXXX, to read as follows:

2004-21-01 Hartzell Propeller Inc. (formerly Hartzell Propeller 
Products Division): Amendment 39-13822. Docket No. 86-ANE-7. 
Supersedes AD 86-06-02, Amendment 39-5259.

Effective Date

    (a) This airworthiness directive (AD) becomes effective October 
19, 2004.

Affected ADs

    (b) This AD supersedes AD 86-06-02.

Applicability

    (c) This AD applies to Hartzell Propeller Inc. (formerly 
Hartzell Propeller Products Division) Model HC-B5MP-3( )/M10282A( 
)+6 five-bladed propellers installed on, Aerospatiale (Nord) Model 
262A airplanes modified by Supplemental Type Certificate (STC) 
SA2369SW, and Short Brothers Ltd. Model SD3-30 airplanes.

Unsafe Condition

    (d) This AD results from four reports in the last 8 months of 
eleven cracked or failed Hartzell propeller attach bolts, part 
number (P/N) B-3339, on Short Brothers Model SD3-

[[Page 60954]]

30 airplanes. The actions specified in this AD are intended to 
prevent propeller separation from the airplane.
    (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.

Torque Check Requirements for Short Brothers Ltd. Model SD3-30 
Airplanes

    (f) Before further flight, for propellers installed on Short 
Brothers Ltd. Model SD3-30 airplanes, do the following:
    (1) Perform an initial torque check inspection of the Hartzell 
propeller attach bolts, P/N B-3339, unless already done within 120 
hours time-in-service (TIS) before the effective date of this AD, 
and thereafter, within 120 hour TIS intervals since the last 
inspection. Use Procedure <greek-i>1 ``Mounting Bolt Torque Check'' 
of Hartzell Alert Service Bulletin (ASB) A203A, dated January 5, 
1995, to do the inspections.
    (2) If the torque check fails, remove the propeller and go to 
paragraph (h) of this AD.

Torque Check Requirements for Aerospatiale (Nord) Model 262A Airplanes 
Modified by STC SA2369SW

    (g) For propellers installed on Aerospatiale (Nord) Model 262A 
airplanes modified by STC SA2369SW, do the following:
    (1) Perform an initial torque check inspection of the Hartzell 
propeller attach bolts, P/N B-3339, within 100 hours TIS after the 
effective date of this AD, and thereafter, within 100 hour TIS 
intervals since the last inspection. Use Procedure <greek-i>1 
``Mounting Bolt Torque Check'' of Hartzell Alert Service Bulletin 
(ASB) A203A, dated January 5, 1995, to do the inspections.
    (2) If the torque check fails, remove the propeller and go to 
paragraph (h) of this AD.

Inspection and Rework of Engine and Propeller Mounting Flange Surfaces 
and Hub Mounting Bolt Holes

    (h) When the propeller is removed due to failing the torque 
check in Procedure <greek-i>1 of Hartzell ASB A203A, dated January 
5, 1995, inspect and rework if necessary, the engine and propeller 
mounting flange surfaces. Use Procedure <greek-i>2 ``Engine/
Propeller Mounting Flanges'' of Hartzell ASB A203A, dated January 5, 
1995, to do the inspections and rework. Also inspect the hub 
mounting bolt holes as follows:
    (1) Clean bolt holes using Stoddard solvent or equivalent and a 
soft bristle brush.
    (2) Visually inspect the area around the bolt holes. No 
deformations, evidence of rework, depressions, or protrusions around 
bolt holes are permitted, except for an edge chamfer of the bolt 
hole up to 0.030 inch.
    (3) Using a 10X magnification, and an appropriate light source, 
visually inspect threads for chipping, missing material, 
deformation, and scratches. No damage is permitted.
    (4) Using a new P/N B-3339 bolt, check threads by threading bolt 
by hand into the bolt hole. The bolt must thread in easily with no 
binding.
    (5) Any hub with a bolt hole showing one or more of the 
prohibited conditions specified in paragraphs (h)(2) through (h(4) 
must be removed from service.

Preparation of Propeller Attach Bolts

    (i) Before installing any Hartzell propeller attach bolt P/N B-
3339, apply anti-seize compound MIL-PRF-83483, to the threaded 
surfaces of the attach bolt. Do not use any other anti-seize 
compound on attach bolts.

Preparation of Propeller Mounting and Engine Flanges

    (j) Before installing a Hartzell HC-B5MP-3( )/M10282A( )+6 
propeller, the propeller mounting flange and engine flange must be 
clean and dry. Do not use anti-fretting compounds on the flanges. 
You may install an FAA-approved Pratt & Whitney shim between the 
propeller mount flange and engine flange.

Alternative Methods of Compliance

    (k) 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.

Special Flight Permits

    (l) Under 14 CFR part 39.23, special flight permits are 
prohibited.

Material Incorporated by Reference

    (m) You must use Hartzell Alert Service Bulletin A203A, dated 
January 5, 1995, to perform the procedures referenced 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. You can get a copy from Hartzell Propeller 
Inc. Technical Publications Department, One Propeller Place, Piqua, 
OH 45356; telephone (937) 778-4200; fax (937) 778-4391. 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/code--of--federal--
regulations/ibr--locations.html.

Related Information

    (n) Information on propeller removal and installation procedures 
can be found in Hartzell Propeller Inc. Service Instruction 140A.

    Issued in Burlington, Massachusetts, on October 4, 2004.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
FR Doc. 04-22728 Filed 10-13-04; 8:45 am]
BILLING CODE 4910-13-P


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