60952 Federal Register / Vol. 69, No. 198 / Thursday, October 14, 2004 / Rules and Regulations 

Does This AD Incorporate Any Material by 

Reference? 

(g) You must do the actions required by 

this AD following the instructions in Korff + 

CO.KG Service Bulletin SB–KOCO 03/818, 

dated December 12, 2002 (German LBA 

approved December 20, 2002). 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 may get a copy from 

KORFF + CO.KG, Dieselstrasse 5, D–63128 

Dietzenbach, Germany. You may review 

copies at FAA, Central Region, Office of the 

Regional Counsel, 901 Locust, Room 506, 

Kansas City, Missouri 64106; 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.

Is There Other Information That Relates to 

This Subject? 

(h) LBA airworthiness directive 2003–051, 

dated January 29, 2003; and 

Korff + CO.KG Service Bulletin SB–KOCO 

03/818, dated December 20, 2002, also 

address the subject of this AD.

Issued in Kansas City, Missouri, on 

September 29, 2004. 

Dorenda D. Baker, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service.

[FR Doc. 04–22715 Filed 10–13–04; 8:45 am] 

BILLING CODE 4910–13–P

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. 

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: 9-aneadcomment@faa.gov. 

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. 

Federal Register / Vol. 69, No. 198 / Thursday, October 14, 2004 / Rules and Regulations 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 datestamp 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

■ 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

■ 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 39–5259 (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–

60954 Federal Register / Vol. 69, No. 198 / Thursday, October 14, 2004 / Rules and Regulations 

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] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–CE–68–AD; Amendment 

39–13823; AD 2004–21–02] 

RIN 2120–AA64 

Airworthiness Directives; 

Przedsiebiorstwo DoswiadczalnoProdukcyjne Szybownictwa ‘‘PZLBielsko’’ Model SZD–50–3 ‘‘Puchacz’’

Sailplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for all 

Przedsiebiorstwo DoswiadczalnoProdukcyjne Szybownictwa ‘‘PZLBielsko’’ (PZL-Bielsko) Model SZD–50–

3 ‘‘Puchacz’’ sailplanes. This AD 

requires you to repetitively inspect the 

front and back of the fuselage front 

bulkhead attachment fitting for cracks 

and replace the attachment fitting if any 

cracks are found. This AD is the result 

of mandatory continuing airworthiness 

information (MCAI) issued by the 

airworthiness authority for Poland. We 

are issuing this AD to detect and correct 

cracks in the fuselage front bulkhead 

attachment fitting, which could result in 

structural failure of the bulkhead. This 

failure could lead to loss of control of 

the sailplane.

DATES: This AD becomes effective on 

November 29, 2004. 

As of November 29, 2004, the Director 

of the Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulation.

ADDRESSES: You may get the service 

information identified in this AD from 

Przedsiebiorstwo Dos ́wiadczalnoProdukcyjne Szybownictwa PZLBielsko, ul. Cieszyn ́ ska 325, 43–300 

Bielsko-Biala: telephone: +48 033 812 

50 21; facsimile: +48 033 812 37 39. 

You may view the AD docket at FAA, 

Central Region, Office of the Regional 

Counsel, Attention: Rules Docket No. 

2003–CE–68–AD, 901 Locust, Room 

506, Kansas City, Missouri 64106. Office 

hours are 8 a.m. to 4 p.m., Monday 

through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Greg 

Davison, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4130; facsimile: 

(816) 329–4090.

SUPPLEMENTARY INFORMATION: