Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 5769

fuselage and consequent reduced structural 

integrity of the airplane, accomplish the 

following: 

Inspection and Test of Flight Compartment 

Window Frames 

(a) Do an inspection and test for stress 

corrosion and cracking as specified in 

paragraphs (a)(1) and (a)(2) of this AD, at the 

applicable time specified in paragraph (b) of 

this AD. 

(1) Do a detailed inspection (using an 

endoscope) to detect stress corrosion and 

cracking of the window frames in the flight 

compartment, including the pilot, co-pilot, 

and front windows. Do the inspection in 

accordance with Dassault Aviation Work 

Card 53–30–12, titled ‘‘Endoscopic 

Inspection of the Frames of Pilot, Co-Pilot, 

and Front Glass Panels (Aircraft Not Changed 

Per SB No. 701),’’ of the Dassault Aviation 

Fan Jet Falcon Maintenance Manual, dated 

November 2001. 

(2) Do an ultrasonic test for cracking in the 

posts of the window frames, including the 

right side window, left and right rear 

windows, front window, and pilot and copilot windows. Do the test in accordance 

with Dassault Aviation Work Card 53–30–07, 

titled ‘‘Non-Destructive Ultrasonic Testing of 

Vertical Posts on Screw-Mounted Windows,’’

of the Dassault Aviation Fan Jet Falcon 

Maintenance Manual, dated November 2001.

Note 1: For the purposes of this AD, a 

detailed inspection is defined as: ‘‘An 

intensive visual examination of a specific 

structural area, system, installation, or 

assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at intensity deemed appropriate by 

the inspector. Inspection aids such as mirror, 

magnifying lenses, etc., may be used. Surface 

cleaning and elaborate access procedures 

may be required.’’

(b) Do the inspection and test required by 

paragraph (a) of this AD, at the times 

specified in paragraph (b)(1) or (b)(2) of this 

AD, as applicable. 

(1) For airplanes having 35 or more years 

since the date of issuance of the original 

Airworthiness Certificate or the date of 

issuance of the Export Certificate of 

Airworthiness, whichever is first; or having 

accumulated 20,000 or more total flight 

cycles; as of the effective date of this AD: 

Within 7 months after the effective date of 

this AD. 

(2) For airplanes not identified in 

paragraph (b)(1) of this AD: Within 25 

months or 2,500 flight cycles after the 

effective date of this AD, whichever is first. 

Repair 

(c) If any stress corrosion or cracking is 

found during any inspection or test required 

by paragraph (a) of this AD: Before further 

flight, repair per a method approved by either 

the Manager, International Branch, ANM–

116, FAA, Transport Airplane Directorate; or 

the Direction Ge ́ne ́rale de l’Aviation Civile 

(or its delegated agent). 

Reporting Requirement 

(d) At the applicable time specified in 

paragraph (d)(1) or (d)(2) of this AD: Submit 

a report of the findings (positive and 

negative) of the inspection required by 

paragraph (a) of this AD to: Dassault Falcon 

Jet, Attn: Service Engineering/Falcon 20, fax: 

(201) 541–4706, at the applicable time 

specified in paragraph (d)(1) or (d)(2) of this 

AD. The report must include the airplane 

serial number, number of landings, number 

of flight hours, airplane age, and the number 

and length of any cracks found. Submission 

of the Charts of Records (part of French 

airworthiness directive 2001–600–028(B), 

dated December 12, 2001), is an acceptable 

method of complying with this requirement. 

Under the provisions of the Paperwork 

Reduction Act of 1980 (44 U.S.C. 3501 et 

seq.), the Office of Management and Budget 

(OMB) has approved the information 

collection requirements contained in this AD 

and has assigned OMB Control Number 

2120–0056. 

(1) If the inspection was done after the 

effective date of this AD: Submit the report 

within 5 days after the inspection. 

(2) If the inspection was done prior to the 

effective date of this AD: Submit the report 

within 5 days after the effective date of this 

AD. 

Alternative Methods of Compliance 

(e) In accordance with 14 CFR 39.19, the 

Manager, International Branch, ANM–116, is 

authorized to approve alternative methods of 

compliance for this AD.

Note 2: The subject of this AD is addressed 

in French airworthiness directive 2001–600–

028(B), dated December 12, 2001.

Issued in Renton, Washington, on January 

29, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2470 Filed 2–5–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–127–AD] 

RIN 2120–AA64 

Airworthiness Directives; Short 

Brothers Model SD3–60 Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes the 

adoption of a new airworthiness 

directive (AD) that is applicable to all 

Short Brothers Model SD3–60 series 

airplanes. This proposal would require 

performing an inspection of the shear 

attachment fitting for the fin-to-fuselage 

front spar, and of the shear cleat for the 

fin root rib at the aft spar location for 

corrosion; reporting inspection results; 

and performing corrective action, if 

necessary. This action is necessary to 

detect and correct corrosion in the area 

of the main spar web fittings of the 

vertical stabilizer, which could result in 

reduced structural integrity of the 

vertical stabilizer. This action is 

intended to address the identified 

unsafe condition.

DATES: Comments must be received by 

March 8, 2004.

ADDRESSES: Submit comments in 

triplicate to the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, ANM–114, 

Attention: Rules Docket No. 2003–NM–

127–AD, 1601 Lind Avenue, SW., 

Renton, Washington 98055–4056. 

Comments may be inspected at this 

location between 9 a.m. and 3 p.m., 

Monday through Friday, except Federal 

holidays. Comments may be submitted 

via fax to (425) 227–1232. Comments 

may also be sent via the Internet using 

the following address: 9-anmnprmcomment@faa.gov. Comments sent 

via fax or the Internet must contain 

‘‘Docket No. 2003–NM–127–AD’’ in the 

subject line and need not be submitted 

in triplicate. Comments sent via the 

Internet as attached electronic files must 

be formatted in Microsoft Word 97 for 

Windows or ASCII text. 

The service information referenced in 

the proposed rule may be obtained from 

Short Brothers, Airworthiness & 

Engineering Quality, P.O. Box 241, 

Airport Road, Belfast BT3 9DZ, 

Northern Ireland. This information may 

be examined at the FAA, Transport 

Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

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.

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested persons are invited to 

participate in the making of the 

proposed rule by submitting such 

written data, views, or arguments as 

they may desire. Communications shall 

identify the Rules Docket number and 

be submitted in triplicate to the address 

specified above. All communications 

received on or before the closing date 

for comments, specified above, will be 

considered before taking action on the 

proposed rule. The proposals contained 

in this action may be changed in light 

of the comments received. 

5770 Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 

Submit comments using the following 

format: 

• Organize comments issue-by-issue. 

For example, discuss a request to 

change the compliance time and a 

request to change the service bulletin 

reference as two separate issues. 

• For each issue, state what specific 

change to the proposed AD is being 

requested. 

• Include justification (e.g., reasons or 

data) for each request. 

Comments are specifically invited on 

the overall regulatory, economic, 

environmental, and energy aspects of 

the proposed rule. All comments 

submitted will be available, both before 

and after the closing date for comments, 

in the Rules Docket for examination by 

interested persons. A report 

summarizing each FAA-public contact 

concerned with the substance of this 

proposal will be filed in the Rules 

Docket. 

Commenters wishing the FAA to 

acknowledge receipt of their comments 

submitted in response to this action 

must submit a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket Number 2003–NM–127–AD.’’

The postcard will be date stamped and 

returned to the commenter. 

Availability of NPRMs 

Any person may obtain a copy of this 

NPRM by submitting a request to the 

FAA, Transport Airplane Directorate, 

ANM–114, Attention: Rules Docket No. 

2003–NM–127–AD, 1601 Lind Avenue, 

SW., Renton, Washington 98055–4056. 

Discussion 

The Civil Aviation Authority (CAA), 

which is the airworthiness authority for 

the United Kingdom, notified the FAA 

that an unsafe condition may exist on 

all Short Brothers Model SD3–60 series 

airplanes. The CAA advises that 

operators have reported corrosion in the 

area of the main spar web fittings, 

which act as shear attachments for the 

vertical stabilizer. This condition, if not 

detected and corrected, could result in 

reduced structural integrity of the 

vertical stabilizer. 

Explanation of Relevant Service 

Information 

Shorts has issued Short Brothers 

Service Bulletin SD360–53–44, Revision 

1, dated January 24, 2003, which 

describes procedures for performing an 

inspection of the shear attachment 

fitting for the fin-to-fuselage front spar, 

and of the shear cleat for the fin root rib 

at the aft spar location for corrosion, and 

submitting an inspection report. The 

CAA classified this service bulletin as 

mandatory and issued British 

airworthiness directive 004–11–2002, in 

order to assure the continued 

airworthiness of these airplanes in the 

United Kingdom.

FAA’s Conclusions 

This airplane model is manufactured 

in the United Kingdom and is type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Pursuant to this bilateral 

airworthiness agreement, the CAA has 

kept the FAA informed of the situation 

described above. The FAA has 

examined the findings of the CAA, 

reviewed all available information, and 

determined that AD action is necessary 

for products of this type design that are 

certificated for operation in the United 

States. 

Explanation of Requirements of 

Proposed Rule 

Since an unsafe condition has been 

identified that is likely to exist or 

develop on other airplanes of the same 

type design registered in the United 

States, the proposed AD would require 

accomplishment of the actions specified 

in the service bulletin described 

previously, except as described below. 

Differences Between Proposed Rule and 

Service Bulletin 

Although the service bulletin 

specifies that operators may contact the 

manufacturer for disposition of repairs, 

this proposal would require operators to 

repair those conditions per a method 

approved by either the FAA or the CAA 

(or its delegated agent). In light of the 

type of repair that would be required to 

address the unsafe condition, and 

consistent with existing bilateral 

airworthiness agreements, we have 

determined that, for this proposed AD, 

a repair approved by either the FAA or 

the CAA would be acceptable for 

compliance with this proposed AD. 

Interim Action 

This proposed AD is considered to be 

interim action. The inspection reports 

required by this proposed AD will 

enable the manufacturer to obtain better 

insight into the nature, cause, and 

extent of the corrosion, and eventually 

to develop final action to address the 

unsafe condition. Once final action has 

been identified, we may consider 

further rulemaking. 

Cost Impact 

The FAA estimates that 46 airplanes 

of U.S. registry would be affected by this 

proposed AD, that it would take 

approximately 3 work hours per 

airplane to accomplish the proposed 

inspection, and that the average labor 

rate is $65 per work hour. Based on 

these figures, the cost impact of the 

proposed AD on U.S. operators is 

estimated to be $8,970, or $195 per 

airplane. 

The cost impact figure discussed 

above is based on assumptions that no 

operator has yet accomplished any of 

the proposed requirements of this AD 

action, and that no operator would 

accomplish those actions in the future if 

this proposed AD were not adopted. The 

cost impact figures discussed in AD 

rulemaking actions represent only the 

time necessary to perform the specific 

actions actually required by the AD. 

These figures typically do not include 

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

Regulatory Impact 

The regulations proposed herein 

would 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. Therefore, 

it is determined that this proposal 

would not have federalism implications 

under Executive Order 13132. 

For the reasons discussed above, I 

certify that this proposed 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) if 

promulgated, 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. A copy of the draft 

regulatory evaluation prepared for this 

action is contained in the Rules Docket. 

A copy of it may be obtained by 

contacting the Rules Docket at the 

location provided under the caption 

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation 

safety, Safety.

The Proposed Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration proposes to amend part 

39 of the Federal Aviation Regulations 

(14 CFR part 39) as follows:

Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 5771

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. Section 39.13 is amended by 

adding the following new airworthiness 

directive:

Short Brothers plc: Docket 2003–NM–127–

AD.

Applicability: All Model SD3–60 series 

airplanes, certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To detect and correct corrosion in the area 

of the main spar web fittings of the vertical 

stabilizer, which could result in reduced 

structural integrity of the vertical stabilizer, 

accomplish the following: 

Inspection 

(a) Within 6 months after the effective date 

of this AD, perform a detailed inspection to 

detect corrosion of the shear attachment 

fitting for the fin-to-fuselage front spar and of 

the shear cleat for the fin root rib at the aft 

spar location, in accordance with the 

Accomplishment Instruction of Short 

Brothers Service Bulletin SD360–53–44, 

Revision 1, dated January 24, 2003.

Note 1: For the purposes of this AD, a 

detailed inspection is defined as: ‘‘An 

intensive visual examination of a specific 

structural area, system, installation, or 

assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at intensity deemed appropriate by 

the inspector. Inspection aids such as mirror, 

magnifying lenses, etc., may be used. Surface 

cleaning and elaborate access procedures 

may be required.’’

Disposition of Repairs 

(b) If any corrosion is detected during the 

inspection required by paragraph (a) of this 

AD, before further flight, repair per a method 

approved by either the Manager, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate; or the Civil 

Aviation Authority (or its delegated agent). 

Inspection Report 

(c) Submit a report of the findings (both 

positive and negative) of the inspection 

required by paragraph (a) of this AD to Short 

Brothers, Airworthiness & Engineering 

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

BT3 9DZ, Northern Ireland, or as specified in 

the Shorts service bulletin, at the applicable 

time specified in paragraph (c)(1) or (c)(2) of 

this AD. The report must include the 

inspection results, a description of any 

discrepancies found, the airplane serial 

number, and the number of landings and 

flight hours on the airplane. Under the 

provisions of the Paperwork Reduction Act of 

1980 (44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements contained in this AD and has 

assigned OMB Control Number 2120–0056. 

(1) If the inspection was done after the 

effective date of this AD: Submit the report 

within 10 days after the inspection. 

(2) If the inspection was accomplished 

prior to the effective date of this AD: Submit 

the report within 10 days after the effective 

date of this AD. 

Alternative Methods of Compliance 

(d) In accordance with 14 CFR 39.19, the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, is 

authorized to approve alternative methods of 

compliance (AMOCs) for this AD.

Note 2: The subject of this AD is addressed 

in British airworthiness directive 004–11–

2002.

Issued in Renton, Washington, on January 

29, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2471 Filed 2–5–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–109–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 767 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes the 

adoption of a new airworthiness 

directive (AD) that is applicable to all 

Boeing Model 767 series airplanes. This 

proposal would require repetitive 

detailed inspections of the aft pressure 

bulkhead for indications of ‘‘oil cans’’

and previous ‘‘oil can’’ repairs, and 

corrective actions, if necessary. An ‘‘oil 

can’’ is an area on a pressure dome web 

that moves when pushed from the 

forward side. This action is necessary to 

detect and correct the propagation of 

fatigue cracks in the vicinity of ‘‘oil 

cans’’ on the web of the aft pressure 

bulkhead, which could result in rapid 

decompression of the passenger cabin, 

possible damage or interference with the 

airplane control systems that pass 

through the bulkhead, and consequent 

loss of control of the airplane. This 

action is intended to address the 

identified unsafe condition.

DATES: Comments must be received by 

March 22, 2004.

ADDRESSES: Submit comments in 

triplicate to the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, ANM–114, 

Attention: Rules Docket No. 2003–NM–

109–AD, 1601 Lind Avenue, SW., 

Renton, Washington 98055–4056. 

Comments may be inspected at this 

location between 9 a.m. and 3 p.m., 

Monday through Friday, except Federal 

holidays. Comments may be submitted 

via fax to (425) 227–1232. Comments 

may also be sent via the Internet using 

the following address: 9-anmnprmcomment@faa.gov. Comments sent 

via fax or the Internet must contain 

‘‘Docket No. 2003–NM–109–AD’’ in the 

subject line and need not be submitted 

in triplicate. Comments sent via the 

Internet as attached electronic files must 

be formatted in Microsoft Word 97 or 

2000 or ASCII text. 

The service information referenced in 

the proposed rule may be obtained from 

Boeing Commercial Airplanes, PO Box 

3707, Seattle, Washington 98124–2207. 

This information may be examined at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., 

Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Suzanne Masterson, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6441; fax (425) 917–6590.

SUPPLEMENTARY INFORMATION:

Comments Invited 

Interested persons are invited to 

participate in the making of the 

proposed rule by submitting such 

written data, views, or arguments as 

they may desire. Communications shall 

identify the Rules Docket number and 

be submitted in triplicate to the address 

specified above. All communications 

received on or before the closing date 

for comments, specified above, will be 

considered before taking action on the 

proposed rule. The proposals contained 

in this action may be changed in light 

of the comments received. 

Submit comments using the following 

format: 

• Organize comments issue-by-issue. 

For example, discuss a request to 

change the compliance time and a 

request to change the service bulletin 

reference as two separate issues. 

• For each issue, state what specific 

change to the proposed AD is being 

requested. 

• Include justification (e.g., reasons or 

data) for each request. 

Comments are specifically invited on 

the overall regulatory, economic, 

environmental, and energy aspects of 

the proposed rule. All comments