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: 

Federal Register / Vol. 69, No. 198 / Thursday, October 14, 2004 / Rules and Regulations 60955

Discussion 

What events have caused this AD?

The General Inspectorate of Civil 

Aviation (GICA), which is the 

airworthiness authority for Poland, 

recently notified FAA that an unsafe 

condition may exist on all PZL-Bielsko 

Model SZD–50–3 ‘‘Puchacz’’ sailplanes. 

The GICA reports that cracks were 

detected in the front bracket console 

mounted on the fuselage front bulkhead. 

What is the potential impact if FAA 

took no action? This condition, if not 

detected and corrected, could cause the 

fuselage front bulkhead to fail. Failure 

of the fuselage front bulkhead could 

result in loss of control of the sailplane. 

Has FAA taken any action to this 

point? We issued a proposal to amend 

part 39 of the Federal Aviation 

Regulations (14 CFR part 39) to include 

an AD that would apply to all PZLBielsko Model SZD–50–3 ‘‘Puchacz’’

sailplanes. This proposal was published 

in the Federal Register as a notice of 

proposed rulemaking (NPRM) on April 

21, 2004 (69 FR 21444). The NPRM 

proposed to require you to repetitively 

inspect the front and back of the 

fuselage front bulkhead attachment 

fitting for cracks, and replace any 

cracked attachment fitting found. 

Is there a modification I can 

incorporate instead of repetitively 

inspecting the front and back of the 

fuselage front bulkhead attachment 

fitting for cracks? The FAA has 

determined that long-term continued 

operational safety would be better 

assured by design changes that remove 

the source of the problem rather than by 

repetitive inspections or other special 

procedures. With this in mind, FAA 

will continue to work with PZL-Bielsko 

in performing further tests to determine 

the cause of the cracking and to provide 

a corrective action that would terminate 

the need for repetitive inspections. 

What is the difference between this 

AD and the service information? The 

manufacturer’s service information 

allows continued flight if cracks are 

found in the fuselage front bulkhead 

attachment fitting that do not exceed 

certain limits. The applicable service 

bulletin specifies replacement of the 

fuselage front bulkhead attachment 

fitting only if cracks are found 

exceeding this limit. This AD will not 

allow continued flight if any crack is 

found. FAA policy is to disallow 

sailplane operation when known cracks 

exist in primary structure, unless the 

ability to sustain ultimate load with 

these cracks is proven. The fuselage 

front bulkhead is considered primary 

structure, and the FAA has not received 

any analysis to prove that ultimate load 

can be sustained with cracks in this 

area. 

Comments 

Was the public invited to comment?

We provided the public the opportunity 

to participate in developing this AD. We 

received no comments on the proposal 

or on the determination of the cost to 

the public. 

Conclusion 

What is FAA’s final determination on 

this issue? We have carefully reviewed 

the available data and determined that 

air safety and the public interest require 

adopting the AD as proposed except for 

minor editorial corrections. We have 

determined that these minor 

corrections:

—Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

—Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Changes to 14 CFR Part 39—Effect on 

the AD 

How does the revision to 14 CFR part 

39 affect this AD? On July 10, 2002, the 

FAA published a new version of 14 CFR 

part 39 (67 FR 47997, July 22, 2002), 

which governs the FAA’s AD system. 

This regulation now includes material 

that relates to altered products, special 

flight permits, and alternative methods 

of compliance. This material previously 

was included in each individual AD. 

Since this material is included in 14 

CFR part 39, we will not include it in 

future AD actions. 

Costs of Compliance 

How many sailplanes does this AD 

impact? We estimate that this AD affects 

8 sailplanes in the U.S. registry. 

What is the cost impact of this AD on 

owners/operators of the affected 

sailplanes? We estimate the following 

costs to accomplish the inspection:

Labor cost Parts cost Total cost per 

sailplane 

Total cost on U.S.

operators 

2 workhours × $65 per hour = $130 ............................................................... Not applicable ........... $130 $130 × 8 = $1,040. 

We estimate the following costs to 

accomplish any necessary replacement 

that will be required based on the 

results of this inspection. We have no 

way of determining the number of 

sailplanes that may need such a 

replacement:

Labor cost Parts cost Total cost per sailplane 

10 workhours × $65 per hour = $650 ............................................................................................ $680 $650 + $680 = $1,330. 

Regulatory Findings 

Will this AD impact various entities?

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. 

Will this AD involve a significant rule 

or regulatory action? For the reasons 

discussed above, I certify that this AD: 

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. 2003–CE–68–

AD’’ in your request.

60956 Federal Register / Vol. 69, No. 198 / Thursday, October 14, 2004 / Rules and Regulations 

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. FAA amends § 39.13 by adding a 

new AD to read as follows:

2004–21–02 Przedsiebiorstwo 

Doswiadczalno-Produkcyjne 

Szybownictwa ‘‘PZL-Bielsko’’:

Amendment 39–13823; Docket No. 

2003–CE–68–AD. 

When Does This AD Become Effective? 

(a) This AD becomes effective on 

November 29, 2004. 

What Other ADs Are Affected by This 

Action? 

(b) None. 

What Sailplanes Are Affected by This AD? 

(c) This AD affects Model SZD–50–3 

‘‘Puchacz’’ sailplanes, all serial numbers, that 

are certificated in any category. 

What Is the Unsafe Condition Presented in 

This AD? 

(d) 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. 

What Must I Do To Address This Problem? 

(e) To address this problem, you must do 

the following:

Actions Compliance Procedures 

(1) Using a flouorescent dye-penetrant or dyecheck method, inspect the front and back of 

the fuselage front bulkhead attachment fitting 

for cracks.

Within the next 25 hours time-in-service (TIS) 

after November 29, 2004 (the effective date 

of this AD). Repetitively inspect thereafter 

at intervals not to exceed 12 calendar 

months.

Follow Przedsiebiorstwo Dos ́wiadczalnoProdukcyjne Szybownictwa PZL-Bielsko 

(PDPS ‘‘PZL-Bielsko’’) Mandatory Bulletin 

No. BE–048/SZD–50–3/2000 ‘‘Puchacz’’, 

dated June 6, 2000. 

(2) If cracks are found during any inspection required in paragraph (e)(1) of this AD, replace 

the fuselage front bulkhead attachment fitting.

Prior to further flight after any inspection required in paragraph (e)(1) of this AD in 

which cracks are found. After replacing the 

fuselage front bulkhead attachment fitting, 

continue with the repetitive inspections required in paragraph (e)(1) of this AD.

Follow Przedsiebiorstwo Dos ́wiadczalnoProdukcyjne Szybownictwa PZL-Bielsko 

(PDPS ‘‘PZL-Bielsko’’) Mandatory Bulletin 

No. BE–049/SZD–50–3/2000 Puchacz’’, 

dated September 14, 2000. 

May I Request an Alternative Method of 

Compliance? 

(f) You may request a different method of 

compliance or a different compliance time 

for this AD by following the procedures in 14 

CFR 39.19. Unless FAA authorizes otherwise, 

send your request to your principal 

inspector. The principal inspector may add 

comments and will send your request to the 

Manager, Standards Office, Small Airplane 

Directorate, FAA. For information on any 

already approved alternative methods of 

compliance, 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. 

Does This AD Incorporate Any Material by 

Reference? 

(g) You must do the actions required by 

this AD following the instructions in 

Przedsiebiorstwo Dos ́wiadczalnoProdukcyjne Szybownictwa PZL-Bielsko 

(PDPS ‘‘PZL-Bielsko’’) Mandatory Bulletin 

No. BE–048/SZD–50–3/2000 ‘‘Puchacz’’, 

dated June 6, 2000; and Przedsiebiorstwo 

Dos ́wiadczalno-Produkcyjne Szybownictwa 

PZL-Bielsko (PDPS ‘‘PZL-Bielsko’’) 

Mandatory Bulletin No. BE–049/SZD–50–3/

2000 ‘‘Puchacz’’, dated September 14, 2000. 

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 

Przedsiebiorstwo Dos ́wiadczalnoProdukcyjne Szybownictwa PZL-Bielsko, ul. 

Cieszyn ́ ska 325, 43–300 Bielsko-Biala: 

telephone: +48 033 812 50 21; facsimile: +48 

033 812 37 39. 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) Republic of Poland AD Number SP–

0059–2000–A, dated June 5, 2000, and AD 

Number SP–0094–2000–A, dated September 

18, 2000, also address the subject of this AD.

Issued in Kansas City, Missouri, on 

October 5, 2004. 

Dorenda D. Baker, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service.

[FR Doc. 04–22812 Filed 10–13–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 71

[Docket No. FAA–2004–18736; Airspace 

Docket No. 04–AEA–10] 

Establishment of Class E Airspace; 

Jonesville, VA

AGENCY: Federal Aviation 

Administration (FAA) DOT.

ACTION: Final rule.

SUMMARY: This action establishes Class 

E airspace at Jonesville, VA. Controlled 

airspace extending upward from 700 

feet Above Ground Level (AGL) is 

needed to contain aircraft operating into 

Lee County Airport, Jonesville, VA, 

under Instrument Flight Rules (IFR).

DATES: Effective 0901 UTC January 20, 

2005.

FOR FURTHER INFORMATION CONTACT: Mr. 

Francis Jordan, airspace Specialist, 

Airspace Branch, Eastern Terminal 

Service Unit, Federal Aviation 

Administration, 1 Aviation Plaza, 

Jamaica, New York 11434–4809, 

telephone: (718) 553–4521.

SUPPLEMENTARY INFORMATION: