Federal Register / Vol. 70, No. 5 / Friday, January 7, 2005 / Rules and Regulations 1329

Washington 98055–4056; telephone 

(425) 917–6478; fax (425) 917–6590.

SUPPLEMENTARY INFORMATION:

Airworthiness Directive AD 2004–23–

06, amendment 39–13861 (69 FR 

67047), applicable to certain Boeing 

Model 757–200, –200PF, –200CB, and 

–300 series airplanes, was published in 

the Federal Register on November 16, 

2004. The AD requires inspection for 

damage of the W2800 wire bundle 

insulation, wire conductor, the wire 

bundle clamp bracket, and the

BACC10GU( ) clamp, and repair or 

replacement with new or serviceable 

parts, if necessary. The AD also requires 

installation of spacers between the 

clamp and the bracket. 

In ‘‘PART 39—AIRWORTHINESS 

DIRECTIVES’’ of the regulatory text of 

AD 2004–23–06, an incorrect citation of 

the amendment number appears. The 

reference should read, ‘‘2004–23–06 

Boeing: Amendment 39–13861.’’

Additionally, as published, the 

applicability of the regulatory text of the 

AD specifies: ‘‘Applicability: Model 

757–200, –200PF, –200CB, as listed in 

Boeing Special Attention Service 

Bulletin 757–27–0089, Revision 1; and 

Model 757–300 series airplanes, as 

listed in Boeing Special Attention 

Service Bulletin 757–24–0090, Revision 

1; both service bulletin revisions dated 

February 27, 2003; certificated in any 

category.’’ The correct reference for 

Model 757–200, –200PF, –200CB 

airplanes is Boeing Special Attention 

Service Bulletin 757–24–0089, Revision 

1, dated February 27, 2003. In all other 

places, the AD references the correct 

service bulletin number. 

No other parts of the regulatory 

information have been changed; 

therefore, the final rule is not 

republished in the Federal Register. 

The effective date of this AD remains 

December 21, 2004.

§ 39.13 [Corrected]

On page 67049, in the first column, 

reference to ‘‘2004–23–06 Boeing:

Amendment 39–2004–23–06. Docket 2001–

NM–74–AD’’ is corrected to read as follows:

* * * * *

2004–23–06 Boeing: Amendment 39–13861. 

Docket 2001–NM–74–AD.

* * * * *

■ On page 67049, in the first column, the 

‘‘Applicability’’ paragraph of AD 2004–

23–06 is corrected to read as follows:

* * * * *

Applicability: Model 757–200, 

–200PF, –200CB, as listed in Boeing 

Special Attention Service Bulletin 757–

24–0089, Revision 1; and Model 757–

300 series airplanes, as listed in Boeing 

Special Attention Service Bulletin 757–

24–0090, Revision 1; both service 

bulletin revisions dated February 27, 

2003; certificated in any category.

* * * * *

Issued in Renton, Washington, on 

December 27, 2004. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 05–285 Filed 1–6–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–19221; Directorate 

Identifier 2004–CE–28–AD; Amendment 39–

13935; AD 2005–01–11] 

RIN 2120–AA64

Airworthiness Directives; Pilatus 

Aircraft Ltd. Models PC–12 and PC–12/

45 Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for all 

Pilatus Aircraft Ltd. (Pilatus) Models 

PC–12 and PC–12/45 airplanes. This AD 

requires you to check the airplane 

logbook to determine whether any main 

landing gear (MLG) actuator (part 

number (P/N) 960.30.01.103) with serial 

numbers (SNs) 830E through 881E is 

installed. If any MLG actuator with one 

of these SNs is installed, you are 

required to replace the MLG actuator 

with a P/N 960.30.01.103 actuator that 

has a SN other than 830E through 881E. 

The pilot is allowed to do the logbook 

check. If the pilot can positively 

determine that no MLG actuator with 

one of these SNs is installed, then no 

further action is required. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

issued by the airworthiness authority for 

Switzerland. We are issuing this AD to 

prevent failure of the MLG actuator 

caused by an incorrect heat treating 

process, which could result in loss of 

hydraulic extension/retraction of the 

MLG. This failure could lead to loss of 

control during ground operations.

DATES: This AD becomes effective on 

February 22, 2005. 

As of February 22, 2005, the Director 

of the Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulation.

ADDRESSES: To get the service 

information identified in this AD, 

contact Pilatus Aircraft Ltd., Customer 

Liaison Manager, CH–6371 Stans, 

Switzerland; telephone: +41 41 619 

6208; facsimile: +41 41 619 7311; email: SupportPC12@pilatus-aircraft.com

or from Pilatus Business Aircraft Ltd., 

Product Support Department, 11755 

Airport Way, Broomfield, Colorado 

80021; telephone: (303) 465–9099; 

facsimile: (303) 465–6040. To review 

this service information, go to the 

National Archives and Records 

Administration (NARA). For 

information on the availability of this 

material at NARA, go to: http://

www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html or call (202) 741–

6030. 

To view the AD docket, go to the 

Docket Management Facility; U.S. 

Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

001 or on the Internet at http://

dms.dot.gov. The docket number is 

FAA–2004–19221.

FOR FURTHER INFORMATION CONTACT:

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329–

4059; facsimile: (816) 329–4090.

SUPPLEMENTARY INFORMATION: 

Discussion 

What events have caused this AD?

The Federal Office for Civil Aviation 

(FOCA), which is the airworthiness 

authority for Switzerland, recently 

notified FAA that an unsafe condition 

may exist on all Pilatus Aircraft Ltd. 

(Pilatus) Models PC–12 and PC–12/45 

airplanes. The FOCA reports that some 

components of main landing gear (MLG) 

actuators (part number (P/N) 

960.30.01.103 with serial numbers (SNs) 

830E through 881E) were incorrectly 

heat treated during manufacture. 

Components in this condition can 

decrease the specified fatigue life of the 

actuators. 

It is possible that these components 

could have been removed and then 

installed in other Pilatus Models PC–12 

and PC–12/45 airplanes. 

What is the potential impact if FAA 

took no action? Failure of the MLG 

actuator could result in loss of hydraulic 

extension/retraction of the MLG. This 

failure could lead to loss of control 

during ground operations. 

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 Pilatus 

Aircraft Ltd. (Pilatus) Models PC–12 and 

1330 Federal Register / Vol. 70, No. 5 / Friday, January 7, 2005 / Rules and Regulations 

PC–12/45 airplanes. This proposal was 

published in the Federal Register as a 

notice of proposed rulemaking (NPRM) 

on November 1, 2004 (69 FR 63336). 

The NPRM proposed to require you to 

check the airplane logbook to determine 

whether any MLG actuator (P/N 

960.30.01.103) with SNs 830E through 

881E is installed. If any MLG actuator 

with one of these SNs is installed, the 

NPRM would require you to replace the 

MLG actuator with a P/N 960.30.01.103 

actuator that has a SN other than 830E 

through 881E. The pilot would be 

allowed to do the logbook check. If the 

pilot can positively determine that no 

MLG actuator with one of these SNs is 

installed, no further action would be 

required. 

Comments 

Was the public invited to comment?

We provided the public the opportunity 

to participate in developing this AD. 

The following presents the comment 

received on the proposal and FAA’s 

response to the comment: 

Comment Issue: Limit AD Serial 

Number Effectivity 

What is the commenter’s concern?

The commenter states that it would be 

more appropriate to have the AD 

address only the serial number airplanes 

on which the parts were installed. 

Further, the commenter states that the 

AD should not apply to airplanes that 

Pilatus has not yet produced.

What is FAA’s response to the 

concern? As FAA explained in the 

NPRM, there is a possibility that these 

parts might have been removed from the 

affected serial number aircraft and 

installed on other serial numbers not 

included in the FOCA AD or Pilatus 

service bulletin. Therefore, we are 

including all serial numbers in the 

effectivity of this AD. To relieve the 

burden, FAA has included in the AD a 

logbook check for the affected S/N main 

landing gear actuators. 

The manufacturer should ensure that 

any MLG actuator P/N 960.30.01.103 

with SNs 830E through 881E is not 

installed at the factory and include a 

statement of compliance with this FAA 

AD in the logbook of any new 

manufactured aircraft. 

Also, the only assurance that FAA has 

that the suspect parts are not installed 

in the future on Pilatus Models PC–12 

and PC–12/45 airplanes is through AD 

action. 

We are not changing the final rule AD 

action based on these comments. 

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 

the changes discussed above and minor 

editorial corrections. We have 

determined that these changes and 

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. 

Docket Information 

Where can I go to view the docket 

information? You may view the AD 

docket that contains information 

relating to this subject in person at the 

DMS Docket Offices between 9 a.m. and 

5 p.m. (eastern standard time), Monday 

through Friday, except Federal holidays. 

The Docket Office (telephone 1–800–

647–5227) is located on the plaza level 

of the Department of Transportation 

NASSIF Building at the street address 

stated in ADDRESSES. You may also view 

the AD docket on the Internet at

http://dms.dot.gov.

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 airplanes does this AD 

impact? We estimate that this AD affects 

260 airplanes in the U.S. registry. 

What is the cost impact of this AD on 

owners/operators of the affected 

airplanes? We estimate the following 

costs to do the inspection:

Labor cost Parts cost Total cost 

per airplane 

Total cost

on U.S. operators 

1 work hour × $65 per hour = $65 .............................................. Not Applicable ....................................... $65 260 × $65 = $16,900. 

We estimate the following costs to do 

any necessary replacement that would 

be required based on the results of this 

inspection. We have no way of 

determining the number of airplanes 

that may need this replacement:

Labor cost Parts cost Total cost 

per airplane 

3 work hours × $65 per hour = $195 per MLG actuator ...................................... Not Applicable ...................................................... $195. 

Pilatus will provide replacement parts 

free of charge if any MLG actuator with 

a SN 830E through 881E is returned to 

Pilatus. If purchased, the cost of a new 

actuator is $14,000. The cost of an 

overhauled actuator is $5,000. 

Authority for this Rulemaking 

What authority does FAA have for 

issuing this rulemaking action? 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 AD. 

Regulatory Findings 

Will this AD impact various entities?

We have determined that this AD will 

not have federalism implications under 

Federal Register / Vol. 70, No. 5 / Friday, January 7, 2005 / Rules and Regulations 1331

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 ‘‘Docket No. FAA–2004–19221; 

Directorate Identifier 2004–CE–28–AD’’

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. FAA amends § 39.13 by adding a 

new AD to read as follows:

2005–01–11 Pilatus Aircraft Ltd.:

Amendment 39–13935; Docket No. 

FAA–2004–19221; Directorate Identifier 

2004–CE–28–AD. 

When Does This AD Become Effective? 

(a) This AD becomes effective on February 

22, 2005. 

What Other ADs Are Affected by This 

Action? 

(b) None. 

What Airplanes Are Affected by This AD? 

(c) This AD affects Models PC–12 and PC–

12/45 airplanes, 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 

Switzerland. The actions specified in this AD 

are intended to prevent failure of the MLG 

actuator caused by an incorrect heat treating 

process, which could result in loss of 

hydraulic extension/retraction of the MLG. 

This failure could lead to loss of control 

during ground operations. 

What Must I Do To Address This Problem? 

(e) To address this problem, you must do 

the following:

Actions Compliance Procedures 

(1) Check the airplane logbook to ensure that 

no main landing gear (MLG) actuator (part 

number (P/N) 960.30.01.103) with serial 

numbers (SN) 830E through 881E is installed.

Within 90 days after February 22, 2005 (the 

effective date of this AD), unless already 

done.

The owner/operator holding at least a private 

pilot certificate as authorized by section 

43.7 of the Federal Aviation Regulations 

(14 CFR 43.7) may do this check. 

(2) If you can positively determine that no MLG 

actuator (P/N 960.30.01.103) with SN 830E 

through 881E is installed, then no further action is required.

Not Applicable .................................................. Make an entry in the aircraft records showing 

compliance with paragraphs (e)(1) and 

(e)(2) of this AD per section 43.9 of the 

Federal Aviation Regulations (14 CFR 

43.9). 

(3) If you cannot positively determine that no 

MLG actuator (P/N 960.30.01.103) with SN 

830E through 881E is installed, then inspect 

any MLG actuator (P/N 960.30.01.103) for 

SN 830E through 881E.

Within 90 days after February 22, 2005 (the 

effective date of this AD), unless already 

done.

Follow the Accomplishment Instructions—Aircraft section in Pilatus PC–12 Service Bulletin No. 32–017, dated August 3, 2004. 

(4) If any MLG actuator (P/N 960.30.01.103) 

with SN 830E through 881E is found during 

the inspection required by paragraph (e)(3) of 

this AD, replace the MLG actuator with a P/N 

960.30.01.103 actuator that has a SN other 

than 830E through 881E.

Before further flight after the inspection required by paragraph (e)(3) of this AD in 

which any actuator with SN 830E through 

881E is found.

Follow the Accomplishment Instructions—Aircraft section in Pilatus PC–12 Service Bulletin No. 32–017, dated August 3, 2004. 

(5) Do not install any MLG actuator (P/N 

960.30.01.103) with SN 830E through 881E.

As of February 22, 2005 (the effective date of 

this AD).

Not Applicable. 

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 Doug Rudolph, 

Aerospace Engineer, FAA, Small Airplane 

Directorate, 901 Locust, Room 301, Kansas 

City, Missouri 64106; telephone: (816) 329–

4059; facsimile: (816) 329–4090. 

Is There Other Information That Relates to 

This Subject? 

(g) Swiss AD Number HB 2004–330, dated 

August 18, 2004, also addresses the subject 

of this AD. 

Does This AD Incorporate Any Material by 

Reference? 

(h) You must do the actions required by 

this AD following the instructions in Pilatus 

PC–12 Service Bulletin No. 32–017, dated 

August 3, 2004. 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. To get a copy of this service 

information, contact Pilatus Aircraft Ltd., 

Customer Liaison Manager, CH–6371 Stans, 

Switzerland; telephone: +41 41 619 6208; 

facsimile: +41 41 619 7311; e-mail: 

SupportPC12@pilatus-aircraft.com or from 

Pilatus Business Aircraft Ltd., Product 

Support Department, 11755 Airport Way, 

Broomfield, Colorado 80021; telephone: (303) 

465–9099; facsimile: (303) 465–6040. To 

review copies of this service information, go 

to the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, go 

to: http://www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html or call (202) 741–6030. To 

view the AD docket, go to the Docket 

Management Facility; U.S. Department of 

Transportation, 400 Seventh Street, SW., 

1332 Federal Register / Vol. 70, No. 5 / Friday, January 7, 2005 / Rules and Regulations 

Nassif Building, Room PL–401, Washington, 

DC 20590–001 or on the Internet at http://

dms.dot.gov. The docket number is FAA–

2004–19221.

Issued in Kansas City, Missouri, on 

December 28, 2004. 

David A. Downey, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 05–185 Filed 1–6–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–18597; Directorate 

Identifier 2004–CE–21–AD; Amendment 39–

13934; AD 2005–01–10] 

RIN 2120–AA64 

Airworthiness Directives; The New 

Piper Aircraft, Inc. Models PA–23–235, 

PA–23–250, and PA–E23–250 Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) that 

supersedes Airworthiness Directive 

(AD) 74–06–01, which applies to certain 

The New Piper Aircraft, Inc. (Piper) 

Models PA–23–235, PA–23–250, and 

PA–E23–250 airplanes equipped with 

Garrett Aviation Services (Garrett) 

(formerly AiResearch) 

turbosuperchargers installed under 

supplemental type certificate (STC) 

SA852WE, SA909WE, or SA978WE; or 

installed under Piper Aircraft Drawing 

Number 32016. AD 74–06–01 currently 

requires you to replace 

turbosupercharger oil tanks, install fire 

shrouds, seal all openings in the fire 

shrouds, and add drainage provisions in 

the oil tank fairings for airplane serial 

numbers 27–1 through 27–2504; and 

add drainage provisions in the air 

scoops on serial numbers 27–2505 and 

higher. This AD requires you to replace 

the oil reservoir and related hoses with 

a fireproof oil tank and fire-shielded 

hoses. This AD results from a report of 

a fatal accident related to the breakdown 

of the turbocharger oil reservoir 

following a fire in the engine nacelle. 

We are issuing this AD to prevent 

turbosupercharger oil reservoirs with 

inadequate fire resistance from failing 

when exposed to flame or exhaust gases. 

This failure could lead to an in-flight 

fire within the nacelle area penetrating 

the firewall and subsequent failure of 

the wing spar.

DATES: This AD becomes effective on 

February 22, 2005. 

As of February 22, 2005, 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:

—For any installation under 

supplemental type certificate (STC) 

SA852WE, SA909WE, or SA978WE:

The Nordam Group, Nacelle/Thrust 

Reverser Division, 6911 N. Whirlpool 

Drive, Tulsa, OK 74117; telephone: 

(918) 878–4000; facsimile: (918) 878–

4808; and 

—For any installation under Piper 

Aircraft Drawing Number 32016: The 

New Piper Aircraft, Inc., 2926 Piper 

Drive, Vero Beach, Florida, 32960; 

and The Nordam Group, Nacelle/

Thrust Reverser Division, 6911 N. 

Whirlpool Drive, Tulsa, OK 74117; 

telephone: (918) 878–4000; facsimile: 

(918) 878–4808.

To review this service information, go 

to the National Archives and Records 

Administration (NARA). For 

information on the availability of this 

material at NARA, go to: http://

www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html or call (202) 741–

6030. 

To view the AD docket, go to the 

Docket Management Facility; U.S. 

Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

001 or on the Internet at http://

dms.dot.gov. The docket number is 

FAA–2004–18597.

FOR FURTHER INFORMATION CONTACT:

Roger Pesuit, Aerospace Engineer, FAA, 

Los Angeles Aircraft Certification 

Office, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; telephone: 

(562) 627–5251; facsimile: (562) 627–

5210.

SUPPLEMENTARY INFORMATION: 

Discussion 

What events have caused this AD?

The need to minimize fire hazards in 

the engine compartment on The New 

Piper Aircraft, Inc. (Piper) Models PA–

23–235, PA–23–250, and PA–E23–250 

airplanes equipped with AiResearch 

turbosuperchargers installed under 

supplemental type certificate (STC) 

SA852WE, SA909WE, or SA978WE; or 

installed under Piper Aircraft Drawing 

32016 caused FAA to issue AD 74–06–

01, Amendment 39–1977. AD 74–06–01 

currently requires the following on any 

Piper Models PA–23–235, PA–23–250, 

and PA–E23–250 airplanes equipped 

with AiResearch turbosuperchargers 

installed under STC SA852WE, 

SA909WE, or SA978WE; or installed 

under Piper Aircraft Drawing Number 

32016:

—Replacing the existing 

turbosupercharger oil tanks; 

—installing fire shrouds; 

—sealing all openings in the fire 

shrouds; 

—(for airplane serial numbers 27–1 

through 27–2504) adding drainage 

provisions in the oil tank fairings; and 

—(for airplane serial numbers 27–2505 

and higher) adding drainage 

provisions in the air scoops.

What has happened since AD 74–06–

01 to initiate this action? The FAA has 

received a report of a fatal accident 

related to the breakdown of the 

turbosupercharger oil reservoir. A Piper 

Model PA 23–250 airplane equipped 

with the STC turbocharger installation 

was involved in a fatal accident. The 

accident investigation revealed a 

breakdown of the turbosupercharger oil 

reservoir. Examination of the aircraft 

wreckage revealed evidence of an inflight fire where the turbosupercharger 

oil reservoir was burned to include the 

rear firewall portion of the reservoir 

allowing fire to move aft, softening the 

wing spar. 

What is the potential impact if FAA 

took no action? Failure of the 

turbosupercharger oil reservoir when 

exposed to flame or exhaust gases could 

lead to an in-flight fire and failure of the 

wing spar. 

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 certain Piper 

Models PA–23–235, PA–23–250, and 

PA–E23–250 airplanes equipped with 

Garrett Aviation Services (Garrett) 

(formerly AiResearch) 

turbosuperchargers installed under STC 

SA852WE, SA909WE, or SA978WE; or 

installed under Piper Aircraft Drawing 

Number 32016. This proposal was 

published in the Federal Register as a 

notice of proposed rulemaking (NPRM) 

on September 22, 2004 (69 FR 56733). 

The NPRM proposed to supersede AD 

74–06–01, which applies to certain 

Piper Models PA–23–235, PA–23–250, 

and PA–E23–250 airplanes equipped 

with Garrett Aviation Services (Garrett) 

(formerly AiResearch) 

turbosuperchargers installed under STC 

SA852WE, SA909WE, or SA978WE; or 

installed under Piper Aircraft Drawing 

Number 32016. AD 74–06–01 currently 

requires you to replace 

turbosupercharger oil tanks, install fire 

shrouds, seal all openings in the fire 

shrouds, and add drainage provisions in