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

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:

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.

By fax: (781) 238-7055.

By e-mail: [email protected].

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:

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.

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.

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.

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:

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

Repetitive torque check inspections of the propeller

attach bolts within 120 hours TIS from the last inspection.

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

Repetitive torque check inspections of the propeller

attach bolts within 100 hours TIS from the last inspection.

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 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 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 1 of Hartzell ASB A203A, dated January

5, 1995, inspect and rework if necessary, the engine and propeller

mounting flange surfaces. Use Procedure 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]

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