Federal Register / Vol. 69, No. 191 / Monday, October 4, 2004 / Proposed Rules 59151

TABLE 2.—VISUAL INSPECTION CRITERIA—Continued

Inspection limits Disposition 

(4) If spline wear is less than 0.03 inch ................................................... Inspect HPC shaft and HPT shaft using the intervals in paragraph 

(h)(2) of this AD. 

Repetitive Visual Inspection of the HPC 

Shaft and HPT Shaft Splines 

(h) Perform repetitive inspections of the 

HPC shaft splines and HPT shaft splines of 

RRD Tay 650–15 series turbofan engines. Use 

paragraph 3.A. of Accomplishment 

Instructions with Appendix 1 of RRD SB No. 

TAY–72–1485, Revision 2, dated March 21, 

2003, to do the inspections. Calculate spline 

wear using Appendix 1, paragraph 4.K., of 

RRD SB No. TAY–72–1485, Revision 2, dated 

March 21, 2003. 

(1) If wear measured in paragraph (f) of this 

AD was greater than or equal to 0.03 inch but 

less than 0.06 inch, repetitively inspect HPC 

shaft and HPT shaft within 1,000 cyclessince-last visual inspection (CSLI). 

(2) If wear measured in paragraph (f) of this 

AD was less than 0.03 inch, repetitively 

inspect HPC shaft and HPT shaft within 

5,500 CSLI. 

(i) Disposition the HPC shaft, HPT shaft, or 

engine as specified in Table 2 of this AD. 

Previous Credit 

(j) Previous credit is allowed for 

performing the initial inspections in 

paragraph (f) of this AD, that were done using 

the Accomplishment Instructions of one of 

the following, before the effective date of this 

AD: 

(1) SB No. TAY–72–1485, dated January 

11, 2002; 

(2) SB No. TAY–72–1485, Revision 1, 

dated January 29, 2003; and 

(3) SB No. TAY–72–1485, Revision 2, 

dated March 21, 2003. 

Material Incorporated by Reference 

(k) None. 

Related Information 

(l) Civil Aviation Authority (CAA) 

airworthiness directive 001–01–2002, dated 

January 11, 2002, also addresses the subject 

of this AD.

Issued in Burlington, Massachusetts, on 

September 24, 2004. 

Francis A. Favara, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service.

[FR Doc. 04–22192 Filed 10–1–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19228; Directorate 

Identifier 2004–NM–77–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 707 Airplanes and Model 720 

and 720B Series Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for all 

Boeing Model 707 airplanes and Model 

720 and 720B series airplanes. This 

proposed AD would require repetitive 

inspections of the left and right support 

ribs for the main landing gear (MLG) 

trunnion, related investigative/

corrective actions if necessary, and 

other specified actions. This proposed 

AD is prompted by reports of in-service 

cracking of the support ribs for the MLG 

trunnion. We are proposing this AD to 

detect and correct corrosion and 

cracking of the support ribs for the MLG 

trunnion, which could result in collapse 

of the MLG.

DATES: We must receive comments on 

this proposed AD by November 18, 

2004.

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street SW., Nassif Building, 

Room PL–401, Washington, DC 20590. 

• By fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. 

You can examine the contents of this 

AD docket on the Internet at http://

dms.dot.gov, or 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: Candice 

Gerretsen, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6428; fax (425) 917–6590. 

Plain language information: Marcia 

Walters, marcia.walters@faa.gov.

SUPPLEMENTARY INFORMATION: 

Docket Management System (DMS) 

The FAA has implemented new 

procedures for maintaining AD dockets 

electronically. As of May 17, 2004, new 

AD actions are posted on DMS and 

assigned a docket number. We track 

each action and assign a corresponding 

directorate identifier. The DMS AD 

docket number is in the form ‘‘Docket 

No. FAA–2004–99999.’’ The Transport 

Airplane Directorate identifier is in the 

form ‘‘Directorate Identifier 2004–NM–

999–AD.’’ Each DMS AD docket also 

lists the directorate identifier (‘‘Old 

Docket Number’’) as a cross-reference 

for searching purposes. 

Comments Invited 

We invite you to submit any written 

relevant data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2004–19228; Directorate Identifier 

2004–NM–77–AD’’ in the subject line of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments submitted by the 

closing date and may amend the 

proposed AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http://

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed AD. 

59152 Federal Register / Vol. 69, No. 191 / Monday, October 4, 2004 / Proposed Rules 

Using the search function of that Web 

site, anyone can find and read the 

comments in any of our dockets, 

including the name of the individual 

who sent the comment (or signed the 

comment on behalf of an association, 

business, labor union, etc.). You can 

review DOT’s complete Privacy Act 

Statement in the Federal Register

published on April 11, 2000 (65 FR 

19477–78), or you can visit http://

dms.dot.gov.

We are reviewing the writing style we 

currently use in regulatory documents. 

We are interested in your comments on 

whether the style of this document is 

clear, and your suggestions to improve 

the clarity of our communications that 

affect you. You can get more 

information about plain language at 

http://www.faa.gov/language and http://

www.plainlanguage.gov.

Examining the Docket 

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. Comments will be available in 

the AD docket shortly after the DMS 

receives them. 

Discussion 

We have received reports of in-service 

cracking of the support ribs for the main 

landing gear (MLG) trunnion on Boeing 

Model 707 airplanes and Model 720 and 

720B series airplanes. Investigation 

revealed that the cracking was caused 

by stress corrosion. This condition, if 

not corrected, could result in collapse of 

the MLG. 

Relevant Service Information 

We have reviewed Boeing 707 Alert 

Service Bulletin A3510, dated January 

15, 2004. Part I of the Accomplishment 

Instructions of the alert service bulletin 

describes procedures for doing a 

repetitive detailed inspection of the left 

and right support ribs for the MLG 

trunnion and related investigative/

corrective and other specified actions. 

The inspection areas include both sides 

of the rib flanges, the web, the flange 

radius, and the support rib. The 

procedures include: 

• Removing all corrosion inhibiting 

compound and sealant from the 

inspection areas. 

• Removing the finish and blending 

the area smooth if deterioration, 

discoloration, blistering, wear, 

scratches, or raised rough/cracked areas 

in the surface finish are found. 

• Contacting Boeing if blending into 

the base metal is necessary. 

• Mechanically removing any 

corrosion. 

• Contacting Boeing for repair 

information if any cracking is found. 

• Applying cadmium plating to all 

areas where the surface finish was 

removed. 

• Applying corrosion inhibitor to all 

exposed surfaces of the support fitting 

for the MLG trunnion.

Part II of the Accomplishment 

Instructions of the alert service bulletin 

includes procedures for doing a 

repetitive HFEC inspection of the left 

and right support ribs for the MLG 

trunnion, and corrective and other 

specified actions. The inspection areas 

include both sides of the web flange, the 

flange radius, the area around all bolt 

heads/nuts and fastener heads/collars 

for the upper and lower chords, and the 

rib around the edge of the support 

fitting for the MLG trunnion. The 

corrective and other specified actions 

include: 

• Removing all corrosion inhibiting 

compound and sealant from the 

inspection areas. 

• Contacting Boeing for repair 

information if any cracking is found. 

• Applying cadmium plate to all 

areas where the surface finish was 

removed. 

• Applying corrosion inhibitor to all 

exposed surfaces of the support fitting 

for the MLG trunnion, both sides of the 

flange radius of the upper and lower 

chords, and the rib supports. 

Accomplishing the actions specified 

in the service information is intended to 

adequately address the unsafe 

condition. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to exist or 

develop on other airplanes of this same 

type design. Therefore, we are 

proposing this AD, which would require 

repetitive inspections for corrosion and 

cracking of the left and right support 

ribs for the main landing gear (MLG) 

trunnion, related investigative/

corrective actions if necessary, and 

other specified actions. The proposed 

AD would require you to use the service 

information described previously to 

perform these actions, except as 

discussed under ‘‘Differences Between 

the Proposed AD and Service 

Information.’’

Differences Between the Proposed AD 

and Service Information 

The alert service bulletin specifies 

that the manufacturer may be contacted 

for disposition of certain repair 

conditions. This proposed AD would 

require the repair of those conditions in 

accordance with a method that we have 

approved or in accordance with data 

meeting the type certification basis of 

the airplane approved by a Boeing 

Company Designated Engineering 

Representative whom we have 

authorized to make such findings. 

Costs of Compliance 

This proposed AD would affect about 

227 airplanes worldwide. The following 

table provides the estimated costs for 

U.S. operators to comply with this 

proposed AD.

ESTIMATED COSTS

Action Work

hours 

Average

labor

rate per

hour 

Parts Cost per

airplane 

Number

of U.S.-

registered

airplanes 

Fleet cost 

Inspection, per inspection cycle 6 $65 None $390, per inspection cycle ....... 32 $12,480, per inspection 

cycle. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD 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. 

Federal Register / Vol. 69, No. 191 / Monday, October 4, 2004 / Proposed Rules 59153

For the reasons discussed above, I 

certify that the 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) 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 proposed 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, Safety.

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 adding 

the following new airworthiness 

directive (AD):

Boeing: Docket No. FAA–2004–19228; 

Directorate Identifier 2004–NM–77–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this AD 

action by November 18, 2004. 

Affected ADs 

(b) None.

Applicability 

(c) This AD applies to all Boeing Model 

707–100 long body, –200, –100B long body, 

and –100B short body series airplanes; and 

Model 707–300, –300B, –300C, and –400 

airplanes; and Model 720 and 720B series 

airplanes; certificated in any category. 

Unsafe Condition 

(d) This AD was prompted by reports of inservice cracking of the support ribs for the 

main landing gear (MLG) trunnion. We are 

proposing this AD to detect and correct 

corrosion and cracking of the support ribs for 

the MLG trunnion, which could result in 

collapse of the MLG. 

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 References 

(f) The term ‘‘alert service bulletin,’’ as 

used in this AD, means the Accomplishment 

Instructions of Boeing 707 Alert Service 

Bulletin A3510, dated January 15, 2004. 

Repetitive Detailed Inspection and 

Corrective Action 

(g) Within 6 months after the effective date 

of this AD: Do a detailed inspection for 

corrosion and cracking of the left and right 

support ribs of the MLG trunnion. Do the 

inspection in accordance with all of the 

actions in Part I of the alert service bulletin. 

Repeat the inspection thereafter at intervals 

not to exceed 6 months. 

(h) If any corrosion or cracking is found 

during any inspection required by paragraph 

(g) of this AD: Before further flight, do all 

applicable related investigative and 

corrective actions, and the other specified 

actions, in accordance with the alert service 

bulletin; except, where the alert service 

bulletin specifies to contact Boeing, before 

further flight, repair in accordance with a 

method approved by the Manager, Seattle 

Aircraft Certification Office (ACO), FAA; or 

in accordance with data meeting the type 

certification basis of the airplane approved 

by a Boeing Designated Engineering 

Representative (DER) who has been 

authorized by the Manager, Seattle ACO, to 

make such findings. For a repair method to 

be approved by the Manager, Seattle ACO, as 

required by this paragraph, the approval 

letter must specifically reference this AD. 

Repetitive High Frequency Eddy Current 

(HFEC) Inspection and Corrective Action 

(i) Within 12 months after the effective 

date of this AD: Do a HFEC inspection for 

cracking of the left and right support ribs of 

the MLG trunnion. Do the inspection in 

accordance with all of the actions in Part II 

of the alert service bulletin. Repeat the 

inspection thereafter at intervals not to 

exceed 12 months. 

(j) If cracking is found during any 

inspection required by paragraph (i) of this 

AD: Before further flight, repair the cracked 

area in accordance with a method approved 

by the Manager, Seattle ACO; or in 

accordance with data meeting the type 

certification basis of the airplane approved 

by a Boeing DER who has been authorized by 

the Manager, Seattle ACO, to make such 

findings. For a repair method to be approved, 

the approval must specifically refer to this 

AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Seattle ACO, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(2) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by a 

Boeing Company DER who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the approval must specifically 

refer to this AD.

Issued in Renton, Washington, on 

September 27, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–22268 Filed 10–1–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19227; Directorate 

Identifier 2003–NM–95–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B2 and B4 Series Airplanes; 

Model A300 B4–600, A300 B4–600R, 

C4–605R Variant F, and A300 F4–600R 

(Collectively Called A300–600) Series 

Airplanes; and Model A310 Series 

Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to certain 

Airbus Model A300 B2 and B4 series 

airplanes; Model A300 B4–600, A300 

B4–600R, C4–605R Variant F, and A300 

F4–600R (collectively called A300–600) 

series airplanes; and Model A310 series 

airplanes. The existing AD currently 

requires replacement of the transformer 

rectifier units (TRUs) in the avionics 

compartment with new, improved 

TRUs. This proposed AD would require 

replacement of the TRUs installed 

according to the existing AD with 

different TRUs that are improved. This 

proposed AD is prompted by analysis 

that has revealed that certain diodes 

installed in the TRUs are the main factor 

contributing to the continuing TRU 

failures. We are proposing this AD to 

prevent failure of the TRUs. Failure of 

multiple TRUs could result in loss of 

the thrust reversers, autothrottle, flaps, 

and various systems (wing/cockpit 

window anti-ice, trim tank pumps, and 

windshield wipers) on the airplane; or 

display of incorrect information to the 

flightcrew.

DATES: We must receive comments on 

this proposed AD by November 3, 2004.

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD. 

• DOT Docket Web site: Go to http:/

/dms.dot.gov and follow the instructions