Federal Register / Vol. 69, No. 241 / Thursday, December 16, 2004 / Rules and Regulations 75233

California 90846, Attention: Data and Service 

Management, Dept. C1-L5A (D800–0024). 

Copies may be inspected at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; or at the 

FAA, Los Angeles Aircraft Certification 

Office, 3960 Paramount Boulevard, 

Lakewood, California; 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.

Effective Date 

(e) This amendment becomes effective on 

January 20, 2005.

Issued in Renton, Washington, on 

December 1, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–27332 Filed 12–15–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–18661; Directorate 

Identifier 2003–NM–273–AD; Amendment 

39–13901; AD 2004–25–13] 

RIN 2120–AA64

Airworthiness Directives; Short 

Brothers Model SD3–60, SD3–

SHERPA, and SD3–60 SHERPA Series 

Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Short Brothers 

Model SD3–60 and SD3–SHERPA series 

airplanes. That AD currently requires a 

one-time inspection to detect cracks 

and/or corrosion of the gland nut on the 

shock absorber of the main landing gear 

(MLG), and follow-on actions. That AD 

also requires repair or replacement of 

any cracked/corroded gland nut with a 

new nut. This new AD adds airplanes to 

the applicability; adds repetitive 

inspections and corrective actions; and 

provides an optional action that ends 

the repetitive inspections. This AD is 

prompted by reports of cracked 

aluminum alloy gland nuts that had 

been inspected previously using the 

existing AD. We are issuing this AD to 

prevent failure of the aluminum alloy 

gland nut on the MLG shock absorber, 

which could cause the MLG to collapse.

DATES: This AD becomes effective 

January 20, 2005. 

The incorporation by reference of 

certain publications listed in the AD is 

approved by the Director of the Federal 

Register as of January 20, 2005. 

On December 11, 1996 (61 FR 57311, 

November 6, 1996), the Director of the 

Federal Register approved the 

incorporation by reference of certain 

other publications, as listed in the 

regulations.

ADDRESSES: For service information 

identified in this AD, contact Short 

Brothers, Airworthiness & Engineering 

Quality, P.O. Box 241, Airport Road, 

Belfast BT3 9DZ, Northern Ireland. 

You can examine this information 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.

You can examine the contents of this 

AD docket on the Internet at http://

dms.dot.gov, or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., room PL–401, on the plaza level of 

the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT: 

Technical information: Todd 

Thompson, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1175; 

fax (425) 227–1149. 

Plain language information: Marcia 

Walters, marcia.walters@faa.gov.

Examining the Docket 

The AD docket contains the proposed 

AD, comments, and any final 

disposition. You can examine the AD 

docket on the Internet at http://

dms.dot.gov, or in person at the Docket 

Management Facility office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The 

Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the DOT street address stated in the 

ADDRESSES section.

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend part 39 of the 

Federal Aviation Regulations (14 CFR 

part 39) with an AD to supersede AD 

96–22–09, amendment 39–9797 (61 FR 

57311, November 6, 1996). The existing 

AD applies to certain Short Brothers 

Model SD3–60 and SD3–SHERPA series 

airplanes. The proposed AD was 

published in the Federal Register on 

July 22, 2004 (69 FR 43779). The 

proposed AD continued to require a 

one-time inspection to detect cracks 

and/or corrosion of the gland nut on the 

shock absorber of the main landing gear 

(MLG), and follow-on actions. The 

proposed AD also continued to require 

repair or replacement of any cracked/

corroded gland nut with a new nut. The 

proposed AD added airplanes to the 

applicability; added repetitive 

inspections and corrective actions; and 

provided an optional action that would 

end the repetitive inspections. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. No comments 

have been submitted on the proposed 

AD or on the determination of the cost 

to the public. 

Editorial Changes to AD 

Minor editorial changes have been 

incorporated into this AD. These 

include changes in the following areas: 

• Summary section, accurately 

identifying the airplanes affected by the 

AD being superseded. 

• Note 2 of the body, updating text for 

the definition of a detailed inspection. 

• Table 3, correcting the dates of 

certain service bulletins and correcting 

the service bulletin reference for certain 

other service bulletins.

• Changing all service bulletin 

references from ‘‘Short Brothers’’ service 

bulletin(s) to ‘‘Shorts’’ service 

bulletin(s). This change was made to 

comply with the Office of the Federal 

Register’s guidelines for material 

incorporated by reference. 

• Paragraph (l), correcting the 

document number of the British 

airworthiness directive. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD with the changes 

described previously. We have 

determined that these changes will not 

increase the economic burden on any 

operator or increase the scope of the AD. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD.

75234 Federal Register / Vol. 69, No. 241 / Thursday, December 16, 2004 / Rules and Regulations 

ESTIMATED COSTS

Action Work hours 

Average

labor rate

per hour 

Parts Cost per

airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspections required by AD 96–22–09 .... 5 $65 N/A $325 58 $18,850

Proposed inspections (per inspection 

cycle) .................................................... 5 65 N/A 325 85 26,625

Authority for This Rulemaking 

The FAA’s authority to issue rules 

regarding aviation safety is found in 

Title 49 of the United States Code. 

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. 

This rulemaking is promulgated 

under the authority described in 

Subtitle VII, Part A, Subpart III, Section 

44701, ‘‘General requirements.’’ Under 

that section, the FAA is charged 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 

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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

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 regulatory evaluation 

of the estimated costs to comply with 

this AD. See the ADDRESSES section for 

a location to examine the regulatory 

evaluation.

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 FAA amends 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 39–9797 (61 FR 

57311, November 6, 1996) and adding 

the following new airworthiness 

directive (AD):

2004–25–13 Short Brothers PLC:

Amendment 39–13901. Docket No. 

FAA–2004–18661; Directorate Identifier 

2003–NM–273–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective January 20, 2005. 

Affected ADs 

(b) This AD supersedes AD 96–22–09, 

amendment 39–9797. 

Applicability 

(c) This AD applies to Short Brothers 

Model SD3–60, SD3–SHERPA, and SD3–60 

SHERPA series airplanes; certificated in any 

category; that are equipped with aluminum 

alloy gland nuts, part number (P/N) 

200920604, on the main landing gear (MLG) 

shock absorber. 

Unsafe Condition 

(d) This AD was prompted by reports of 

cracked aluminum alloy gland nuts on the 

MLG shock absorber that had been 

previously inspected using AD 96–22–09. We 

are issuing this AD to prevent failure of the 

aluminum alloy gland nut on the MLG shock 

absorber, which could cause the MLG to 

collapse.

Compliance 

(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. 

Service Bulletin Reference 

(f) The term ‘‘service bulletin,’’ as used in 

this AD, means the Accomplishment 

Instructions of the applicable service bulletin 

or service bulletins listed in the following 

paragraphs: 

(1) For the requirements specified in 

paragraphs (g) and (h) of this AD, which are 

restated from AD 96–22–09, use the 

applicable service bulletins in Table 1 of this 

AD.

TABLE 1.—SHORTS SERVICE BULLETINS FOR RESTATED REQUIREMENTS

Model Service bulletin Revision Date 

SD3–SHERPA series airplanes ............................. SD3 SHERPA–32–2 .............................................. Original ............. September 22, 1995. 

SD3–SHERPA series airplanes ............................. SD3 SHERPA–32–2 .............................................. 1 ....................... June 30, 2003. 

SD3–60 series airplanes ........................................ SD360–32–34 ........................................................ Original ............. September 22, 1995. 

SD3–60 series airplanes ........................................ SD360–32–34 ........................................................ 1 ....................... June 30, 2003. 

(2) For the new requirements specified in paragraphs (i) and (j) of this AD, use the applicable service bulletin in Table 2 of this AD.

TABLE 2.—SHORTS SERVICE BULLETINS FOR NEW REQUIREMENTS

Model Service bulletin Revision Date 

SD3–SHERPA series airplanes ............................. SD3 SHERPA–32–2 .............................................. 1 ....................... June 30, 2003. 

SD3–60 SHERPA series airplanes ........................ SD360 SHERPA–32–1 .......................................... Original ............. June 30, 2003. 

Federal Register / Vol. 69, No. 241 / Thursday, December 16, 2004 / Rules and Regulations 75235

TABLE 2.—SHORTS SERVICE BULLETINS FOR NEW REQUIREMENTS—Continued

Model Service bulletin Revision Date 

SD3–60 series airplanes ........................................ SD360–32–34 ........................................................ 1 ....................... June 30, 2003. 

Note 1: The Messier-Dowty service bulletins listed in Table 3 of this AD are additional sources of service information for certain actions 

in the Shorts service bulletins.

TABLE 3.—ADDITIONAL SOURCES OF SERVICE INFORMATION

This Messier-Dowty service bulletin— Is an additional source of service information for these shorts service bulletins—

32–78SD, dated July 19, 1995 ........................... SD3 SHERPA–32–2, dated September 22, 1995; and SD360–32–34, dated September 22, 

1995. 

32–78SD, Revision 1, dated December 9, 2002 SD360 SHERPA–32–1, dated June 30, 2003; and SD360–32–34, Revision 1, dated June 30, 

2003. 

32–80SD, dated August 31, 2000 ...................... SD360 SHERPA–32–1, dated June 30, 2003; SD3 SHERPA–32–2, Revision 1, dated June 

30, 2003; and SD360–32–34, Revision 1, dated June 30, 2003. 

Restatement of the Requirements of AD 96–

22–09

(g) For Model SD3–60 series airplanes and 

Model SD3–SHERPA series airplanes: Within 

90 days after December 11, 1996 (the 

effective date AD 96–22–09), perform a onetime visual and fluorescent dye penetrant 

inspection to detect cracks and/or corrosion 

of the gland nut on the shock absorber of the 

MLG, in accordance with the applicable 

service bulletin. 

(1) If no crack and/or corrosion is detected, 

no further action is required by paragraph (g) 

of this AD. 

(2) If no crack is detected, but corrosion is 

detected that is within the limits specified in 

the service bulletin, prior to further flight, 

repair the gland nut in accordance with the 

applicable service bulletin. 

(3) If any crack is detected, or if any 

corrosion is detected that is outside the limits 

specified in the applicable service bulletin, 

prior to further flight, replace the gland nut 

with a new gland nut, in accordance with the 

applicable service bulletin. 

(h) Following accomplishment of 

paragraph (g) of this AD, prior to further 

flight, apply grease to the threads of the 

cylinder, and apply sealant to the inner 

radius of the gland nut, in accordance with 

the applicable service bulletin. 

New Requirements of This AD 

Detailed Inspection and Corrective Action 

(i) For all airplanes: Within 4 months after 

the effective date of this AD, do a detailed 

inspection of the P/N 200920604 gland nut 

on the MLG shock absorber for corrosion 

and/or cracking, and do any applicable 

corrective action before further flight, in 

accordance with the applicable service 

bulletin. Repeat the inspection at intervals 

not to exceed 12 months.

Note 2: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

Optional Terminating Action 

(j) Replacing the aluminum alloy gland 

nut, P/N 200920604, with a new steel gland 

nut, P/N 200920639, in accordance with the 

applicable service bulletin, terminates the 

requirements of this AD. 

Alternative Methods of Compliance (AMOCs) 

(k) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

Related Information 

(l) British airworthiness directive 008–06–

2003 also addresses the subject of this AD. 

Material Incorporated by Reference 

(m) You must use the service information 

that is specified in Table 4 of this AD to 

perform the actions that are required by this 

AD, unless the AD specifies otherwise. For 

copies of the service information, contact 

Short Brothers, Airworthiness & Engineering 

Quality, P.O. Box 241, Airport Road, Belfast 

BT3 9DZ, Northern Ireland. For information 

on the availability of this material at the 

National Archives and Records 

Administration (NARA), call (202) 741–6030, 

or go to http://www.archives.gov/

federal_register/code_of_federal_regulations/

ibr_locations.html. You may view the AD 

docket at the Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., room PL–401, Nassif 

Building, Washington, DC.

TABLE 4.—MATERIAL INCORPORATED BY REFERENCE

Shorts service bulletin Revision level Date 

SD3 SHERPA–32–2 ............................................................................................................................ Original .................... September 22, 1995. 

SD3 SHERPA–32–2 ............................................................................................................................ 1 ............................... June 30, 2003. 

SD360 SHERPA–32–1 ........................................................................................................................ Original .................... June 30, 2003. 

SD360–32–34 ...................................................................................................................................... Original .................... September 22, 1995. 

SD360–32–34 ...................................................................................................................................... 1 ............................... June 30, 2003. 

(1) The incorporation by reference of the service information listed in Table 5 of this AD is approved by the Director of the Federal 

Register, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.

TABLE 5.—MATERIAL NEWLY INCORPORATED BY REFERENCE

Shorts service bulletin Revision level Date 

SD3 SHERPA–32–2 ............................................................................................................................ 1 ............................... June 30, 2003. 

SD360 SHERPA–32–1 ........................................................................................................................ Original .................... June 30, 2003. 

SD360–32–34 ...................................................................................................................................... 1 ............................... June 30, 2003. 

75236 Federal Register / Vol. 69, No. 241 / Thursday, December 16, 2004 / Rules and Regulations 

(2) The incorporation by reference of the service information listed in Table 6 of this AD was approved previously by the Director of 

the Federal Register as of December 11, 1996 (61 FR 57311, November 6, 1996).

TABLE 6.—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE

Shorts service bulletin Revision level Date 

SD3 SHERPA–32–2 ............................................................................................................................ Original .................... September 22, 1995. 

SD360–32–34 ...................................................................................................................................... Original .................... September 22, 1995. 

Issued in Renton, Washington, on 

December 1, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–27331 Filed 12–15–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2003–CE–40–AD; Amendment 

39–13795; AD 2004–19–01] 

RIN 2120–AA64

Airworthiness Directives; Cessna 

Aircraft Company 120, 140, 140A, 150, 

F150, 170, 172, F172, FR172, P172D, 

175, 177, 180, 182, 185, A185E, 190, 

195, 206, P206, U206, TP206, TU206, 

207, T207, 210, T210, 336, 337, and 

T337 Series Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule; correction.

SUMMARY: This document makes a 

correction to Airworthiness Directive 

(AD) 2004–19–01, which was published 

in the Federal Register on September 

17, 2004 (69 FR 55943), and applies to 

certain Cessna Aircraft Company 

(Cessna) 120, 140, 140A, 150, F150, 170, 

172, F172, FR172, P172D, 175, 177, 180, 

182, 185, A185E, 190, 195, 205, 205A, 

206, P206, P206E, TP206A, TU206, 

TU206E, U206, U206E, 207, T207, 210, 

T210, 336, 337, and T337 series 

airplanes. We incorrectly referenced a 

serial number for the affected Model 

T337B airplanes in the applicability 

section as 37–0570. The correct serial 

number is 337–0570. This action 

corrects the applicability section of AD 

2004–19–01, Amendment 39–13795.

DATES: The effective date of this AD 

remains November 1, 2004.

FOR FURTHER INFORMATION CONTACT: Gary 

D. Park, Aerospace Engineer, FAA, 

Wichita Aircraft Certification Office, 

1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas 

67209; telephone: (316) 946–4123; 

facsimile: (316) 946–4107.

SUPPLEMENTARY INFORMATION: 

Discussion 

On September 8, 2004, FAA issued 

AD 2004–19–01, Amendment 39–13795 

(69 FR 55943, September 17, 2004) (as 

corrected in the publication of October 

7, 2004 (69 FR 60081), which applies to 

certain Cessna 120, 140, 140A, 150, 

F150, 170, 172, F172, FR172, P172D, 

175, 177, 180, 182, 185, A185E, 190, 

195, 205, 205A, 206, P206, P206E, 

TP206A, TU206, TU206E, U206, U206E, 

207, T207, 210, T210, 336, 337, and 

T337 series airplanes. This AD 

supersedes AD 86–26–04 with a new 

AD that requires you to inspect and, if 

necessary, modify the pilot/co-pilot 

upper shoulder harness adjusters that 

have certain Cessna accessory kits 

incorporated. 

Need for the Correction 

The FAA incorrectly referenced a 

serial number for Model T337B 

airplanes in the applicability section of 

AD 2004–19–01. The correct serial 

number range for the affected Model 

T337B airplanes is 337–0001, 337–0470, 

337–0526 through 337–0568, and 337–

0570 through 337–0755. This correction 

is needed to prevent confusion in the 

field regarding the FAA’s intent of the 

AD applicability. 

Correction of Publication 

Accordingly, the publication of 

September 17, 2004 (69 FR 55943), of 

AD 2004–19–01; Amendment 39–13795; 

which was the subject of FR Doc. 04–

20774 (as corrected in the publication of 

October 7, 2004 (69 FR 60081), which 

was the subject of FR Doc. 04–21814), 

is corrected as follows:

§ 39.13 [Corrected]

■ On page 55946, in § 39.13 [Amended], 

2., replace paragraph (c)(129) with the 

following text:

‘‘(129) T337B 337–0001, 337–0470, 337–

0526 through 337–0568, and 337–0570 

through 337–0755’’.

Action is taken herein to correct this 

reference in AD 2004–19–01 and to add 

this AD correction to § 39.13 of the 

Federal Aviation Regulations (14 CFR 

39.13). 

The effective date remains November 

1, 2004.

Issued in Kansas City, Missouri, on 

December 7, 2004. 

Sandra J. Campbell, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–27513 Filed 12–15–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–18744; Directorate 

Identifier 2004–CE–24–AD; Amendment 39–

13910; AD 2004–25–22] 

RIN 2120–AA64

Airworthiness Directives; Great Lakes 

Aircraft Company, LLC, Models 2T–

1A–1 and 2T–1A–2 Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA supersedes 

Airworthiness Directive (AD) 79–20–08, 

which applies to all Great Lakes Aircraft 

Company, LLC, (Great Lakes) Models 

2T–1A–1 and 2T–1A–2 airplanes with a 

Lycoming IO–360–B1F6 or AIO–360–

B1G6 engine installed. AD 79–20–08 

currently requires you to inspect the 

engine induction system and the 

alternate air door for any signs of 

damage and repairing or replacing any 

damaged components. AD 79–20–08 

also requires you to inspect the 

induction system for the presence of a 

drain fitting. If the drain fitting is 

blocked, restricted, or does not exist, AD 

79–20–08 requires you to clear the 

fitting or drill a hole in the elbow at the 

fitting location. This AD is the result of 

the FAA inadvertently omitting 

Lycoming engine AEIO–360–B1G6 from 

the applicability section of AD 79–20–

08. Consequently, this AD retains the 

actions required in AD 79–20–08 and 

adds Lycoming engine AEIO–360–B1G6 

to the applicability section. We are 

issuing this AD to prevent the aircraft 

induction system from becoming 

blocked or restricted, which could result