Federal Register / Vol. 69, No. 188 / Wednesday, September 29, 2004 / Proposed Rules 58103

Bulletin 747–54A2219, dated September 4, 

2003: Perform a detailed inspection of the 

midspar web of the outboard struts for 

cracking, disbonding, or buckling; a detailed 

inspection of the midspar stiffeners for any 

crack or fracture; related investigative 

actions; and any applicable corrective 

actions; in accordance with ‘‘Part 2’’ of the 

Work Instructions of Boeing Alert Service 

Bulletin 747–54A2219, dated September 4, 

2003; except as required by paragraph (i) of 

this AD. Perform any related investigative 

actions and any applicable corrective actions 

before further flight. 

Contact the FAA/Designated Engineering 

Representative 

(i) Where Boeing Alert Service Bulletin 

747–54A2219, dated September 4, 2003, 

specifies to contact Boeing for appropriate 

action: Before further flight, repair per a 

method approved by the Manager, Seattle 

Aircraft Certification Office (ACO), FAA; or 

per data meeting the type certification basis 

of the airplane approved by a Boeing 

Company Designated Engineering 

Representative who has been authorized by 

the Manager, Seattle ACO, to make such 

findings. For a repair method to be approved, 

the approval must specifically reference this 

AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Seattle ACO, FAA, 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 Designated Engineering 

Representative 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 21, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–21821 Filed 9–28–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–19201; Directorate 

Identifier 2003–NM–100–AD] 

RIN 2120–AA64

Airworthiness Directives; Boeing 

Model 767–200, –300, and –300F 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) for all Boeing Model 767–

200, –300, and –300F series airplanes. 

That AD currently requires examination 

of maintenance records to determine if 

Titanine JC5A (also known as Desoto 

823E508) corrosion inhibiting 

compound (‘‘C.I.C.’’) was ever used; 

inspection for cracks or corrosion and 

corrective action, if applicable; 

repetitive inspections and C.I.C. 

applications; and modification of the aft 

trunnion area of the outer cylinder, 

which terminates the need for the 

repetitive inspections and C.I.C. 

applications. This proposed AD would 

also require, for certain other airplanes, 

repetitive inspections for cracks or 

corrosion, corrective action if necessary, 

and repetitive C.I.C. applications. This 

proposed AD is prompted by a report 

that JC5A was used on more airplanes 

during production than previously 

identified. We are proposing this AD to 

prevent severe corrosion in the main 

landing gear (MLG) outer cylinder at the 

aft trunnion, which could develop into 

stress corrosion cracking and 

consequent collapse of the MLG.

DATES: We must receive comments on 

this proposed AD by November 15, 

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. 

• 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: 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. 

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 relevant 

written data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2004–19201; Directorate Identifier 

2003–NM–100–AD’’ at the beginning 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 received 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. 

Using the search function of our docket 

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 the 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 

58104 Federal Register / Vol. 69, No. 188 / Wednesday, September 29, 2004 / Proposed Rules 

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 

On April 11, 2002, we issued AD 

2002–08–07, amendment 39–12715 (67 

FR 19322, April 19, 2002), for all Boeing 

Model 767–200, –300, and –300F series 

airplanes. That AD requires examination 

of maintenance records to determine if 

Titanine JC5A (also known as Desoto 

823E508, and hereafter collectively 

referred to as JC5A) corrosion inhibiting 

compound (‘‘C.I.C.’’) was ever used; 

inspection for cracks or corrosion and 

corrective action, if applicable; 

repetitive inspections and C.I.C. 

applications; and modification of the aft 

trunnion area of the outer cylinder, 

which terminates the need for the 

repetitive inspections and C.I.C. 

applications. That AD was prompted by 

reports of an approved C.I.C. causing 

severe corrosion in the MLG at the outer 

cylinder aft trunnion on Boeing Model 

767 series airplanes. We issued that AD 

to prevent severe corrosion in the MLG 

outer cylinder at the aft trunnion, which 

could develop into stress corrosion 

cracking and consequent collapse of the 

MLG. 

Actions Since Existing AD Was Issued 

Since we issued AD 2002–08–07, we 

have determined that the identified 

unsafe condition (i.e., corrosion in the 

aft trunnion caused by the use of JC5A, 

a C.I.C. that deteriorates over time and 

degrades primer and cadmium plating 

when it comes into contact with 

moisture) addressed in that AD could 

still exist on 15 Model 767–200, –300, 

and –300F series airplanes of U.S. 

registry (within the group of line 

numbers (L/N) 834 through 874 

inclusive). We have been advised that 

JC5A was used on more airplanes 

during production than those previously 

identified in the original issue of Boeing 

Alert Service Bulletin 767–32A0192. 

Based on previous information and the 

records examination required by AD 

2002–08–07, an operator could have 

incorrectly determined that JC5A had 

not been used on certain airplanes and 

consequently not corrected the unsafe 

condition. Therefore, we have 

determined that these airplanes are 

subject to the inspections, C.I.C 

applications, and modification required 

by AD 2002–08–07. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 767–32A0192, Revision 

1, dated March 13, 2003. The 

procedures specified in Revision 1 of 

the service bulletin are essentially the 

same as the procedures specified in the 

original issue of the service bulletin, as 

cited in AD 2002–08–07. Revision 1 of 

the service bulletin identifies affected 

airplanes, L/Ns 834 through 874, as 

assembled new with JC5A in the outer 

cylinder aft trunnion. 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 products of this same 

type design. Therefore, we are 

proposing this AD, which would 

supersede AD 2002–08–07. This 

proposed AD would continue to require, 

for certain airplanes, examination of 

maintenance records to determine if 

JC5A C.I.C. was ever used; inspection 

for cracks or corrosion and corrective 

action, if applicable; repetitive 

inspections and C.I.C. applications; and 

modification of the aft trunnion area of 

the outer cylinder, which terminates the 

need for the repetitive inspections and 

C.I.C. applications. This proposed AD 

would also require, for certain other 

airplanes, repetitive inspections for 

cracks or corrosion, corrective action if 

necessary, and repetitive C.I.C. 

applications. This 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 the Service 

Bulletins.’’

Differences Between the Proposed AD 

and the Service Bulletins 

Operators should note that, although 

the Accomplishment Instructions of the 

referenced service bulletins require 

reporting all corrosion found in the aft 

trunnions of certain airplanes, this 

proposed AD would not require that 

action. 

Change to Existing AD 

This proposed AD would retain all 

requirements of AD 2002–08–07. Since 

AD 2002–08–07 was issued, the AD 

format has been revised, and certain 

paragraphs have been rearranged. As a 

result, the corresponding paragraph 

identifiers have changed in this 

proposed AD, as listed in the following 

table:

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

2002–08–07 

Corresponding

requirement in this

proposed AD 

Paragraph (a) ............ Paragraph (g). 

Paragraph (b) ............ Paragraph (h). 

Paragraph (c) ............ Paragraph (i). 

Paragraph (d) ............ Paragraph (j). 

Paragraph (e) ............ Paragraph (k). 

Paragraph (f) ............. Paragraph (l). 

Paragraph (g) ............ Paragraph (m). 

Paragraph (h) ............ Paragraph (n). 

Paragraph (i) ............. Paragraph (q). 

Paragraph (j) ............. Paragraph (r). 

Paragraph (k) ............ Paragraph (o). 

Paragraph (l) ............. Paragraph (p). 

We have also changed all references 

to the ambiguous time of ‘‘years ago’’ in 

paragraphs (j)(2), (j)(3), (k)(2)(i)(A), 

(k)(2)(i)(B), and (m)(2) of this proposed 

AD to ‘‘years before May 6, 2002.’’

Costs of Compliance 

There are about 848 airplanes of the 

affected design in the worldwide fleet. 

This proposed AD would affect about 

357 airplanes of U.S. registry. The new 

requirements of this proposed AD add 

no additional economic burden for 

operators affected by AD 2002–08–07. 

The current costs for this AD are 

repeated for the convenience of affected 

operators, as follows:

ESTIMATED COSTS

Action Work 

hours 

Average 

labor rate 

per hour 

Parts Cost per airplane Fleet cost 

C.I.C. Application ......................... 1 $65 (1) $65, per application cycle ........... $23,205 per application cycle. 

Federal Register / Vol. 69, No. 188 / Wednesday, September 29, 2004 / Proposed Rules 58105

ESTIMATED COSTS—Continued

Action Work 

hours 

Average 

labor rate 

per hour 

Parts Cost per airplane Fleet cost 

Cross Bolt Hole Inspection—

Bushings Removed.

2 65 (1) 130 .............................................. 46,410. 

Restoration for Bushings Removed.6 65 (1) 390 .............................................. 139,230. 

Cross Bolt Inner Chamfer Inspection—Bushings Not Removed.2 65 (1) 130, per inspection cycle ............ 46,410, per inspection cycle. 

Restoration for Bushings Not Removed.6 65 (1) 390 .............................................. 139,230. 

Terminating Action ....................... 64 65 6,356 10,581 ......................................... 3,777,417. 

1 None. 

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. 

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 

removing amendment 39–12715 (67 FR 

19322, April 19, 2002) and adding the 

following new airworthiness directive 

(AD):

Boeing: Docket No. FAA–2004–19201; 

Directorate Identifier 2003–NM–100–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

must receive comments on this airworthiness 

directive (AD) action by November 15, 2004. 

Affected ADs 

(b) This AD supersedes AD 2002–08–07, 

amendment 39–12715 (67 FR 19322, April 

19, 2002). 

Applicability: (c) This AD applies to all 

Boeing Model 767–200, –300, and –300F 

series airplanes, certificated in any category. 

Unsafe Condition 

(d) This AD was prompted by a report that 

Titanine JC5A (also known as Desoto 

823E508) was used on more airplanes during 

production than previously identified. We 

are issuing this AD to prevent severe 

corrosion in the main landing gear (MLG) 

outer cylinder at the aft trunnion, which 

could develop into stress corrosion cracking 

and consequent 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.

Requirements of AD 2002–08–07, 

Amendment 39–9783: Line Numbers (L/N) 1 

Through 833 Inclusive, and 875 and 

Subsequent 

(f) For airplanes with L/Ns 1 through 833 

inclusive, and 875 and subsequent: 

Do the actions specified in paragraphs (g) 

through (q) of this AD, as applicable. 

Records Examination 

(g) Within 90 days after May 6, 2002 (the 

effective date of AD 2002–08–07, amendment 

39–9783), examine airplane records to 

determine if Titanine JC5A or Desoto 

823E508 (hereafter collectively referred to as 

‘‘JC5A’’) corrosion inhibiting compound 

(‘‘C.I.C.’’) was used in the aft trunnion area 

of the MLG outer cylinder during general 

maintenance, overhaul, or incorporation of 

Boeing Alert Service Bulletin 767–32A0148, 

dated December 21, 1995; Revision 1, dated 

October 10, 1996 (required by paragraph (e) 

of AD 96–21–06, amendment 39–9783); or 

Revision 2, dated November 30, 2000; in 

accordance with Boeing Alert Service 

Bulletin 767–32A0192, dated May 31, 2001; 

or Revision 1, dated March 13, 2003. If 

records do not show conclusively which 

compound was used, assume JC5A was used. 

Refer to Boeing Alert Service Bulletin 767–

32A0192, dated May 31, 2001, for the line 

numbers of airplanes that were assembled 

new using JC5A.

Note 1: Prior to January 31, 2001, if BMS 

3–27 was ordered from Boeing, Boeing 

shipped JC5A as a substitute.

MLGs on Which JC5A Was Not Used 

(h) Except as provided by paragraph (p) 

(‘‘Use of JC5A Prohibited’’) of this AD, if, 

according to the criteria of paragraph (g) of 

this AD, JC5A was never used, no further 

action is required by this AD. 

C.I.C. Applications, Inspections, and 

Corrective Actions if Necessary 

(i) For Category 1 MLG outer cylinders as 

identified in Boeing Alert Service Bulletin 

767–32A0192, dated May 31, 2001: If, 

according to the criteria of paragraph (g) of 

this AD, JC5A may have been used, perform 

the actions specified in both paragraphs (j) 

and (k) of this AD, as applicable, in 

accordance with Boeing Alert Service 

Bulletin 767–32A0192, dated May 31, 2001; 

or Revision 1, dated March 13, 2003. 

(j) For MLGs and MLG outer cylinders 

identified in paragraphs (j)(1), (j)(2), and (j)(3) 

of this AD: Within 90 days after May 6, 2002, 

perform the C.I.C. application on the MLG in 

accordance with ‘‘Part 3—C.I.C. Application’’

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 767–32A0192, 

dated May 31, 2001; or Revision 1, dated 

March 13, 2003. Thereafter, repeat at 

intervals not to exceed 180 days until the 

terminating action required by paragraph (q) 

of this AD has been accomplished. 

(1) MLG outer cylinders that are less than 

3 years old since new. 

(2) MLGs that have been overhauled less 

than 3 years before May 6, 2002. 

(3) MLGs on which rework per Boeing 

Alert Service Bulletin 767–32A0148, dated 

December 21, 1995; Revision 1, dated 

October 10, 1996; or Revision 2, dated 

November 30, 2000, was accomplished less 

than 3 years before May 6, 2002. 

(k) Before the MLG outer cylinder is 3 

years old since new, since last overhaul, or 

since rework per Boeing Alert Service 

Bulletin 767–32A0148, dated December 21, 

1995; Revision 1, dated October 10, 1996; or 

58106 Federal Register / Vol. 69, No. 188 / Wednesday, September 29, 2004 / Proposed Rules 

Revision 2, dated November 30, 2000; or 

within 90 days after May 6, 2002; whichever 

is later; perform a detailed inspection for 

cracks and corrosion of the cross bolt bushing 

holes and chamfers in accordance with ‘‘Part 

1—Cross Bolt Hole Inspection—Bushings 

Removed’’ of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–32A0192, dated May 31, 2001; or 

Revision 1, dated March 13, 2003.

Note 2: For the purposes of this AD, a 

detailed inspection is defined as: ‘‘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.’’

(1) If no crack or corrosion is found during 

the detailed inspection required by paragraph 

(k) of this AD, perform the actions in 

paragraphs (k)(1)(i), (k)(1)(ii), and (k)(1)(iii) of 

this AD, at the applicable times indicated. 

(i) Before further flight, perform the 

restoration steps shown in Figure 2 of the 

service bulletin; and thereafter at intervals 

not to exceed 180 days, perform the C.I.C. 

application on the landing gear in accordance 

with ‘‘Part 3—C.I.C. Application’’ of the 

Accomplishment Instructions of the service 

bulletin. 

(ii) Within 18 months after performing the 

detailed inspection required by paragraph (k) 

of this AD, and thereafter at intervals not to 

exceed 18 months, perform the detailed 

inspection for cracks and corrosion of the 

cross bolt hole inner chamfer, in accordance 

with ‘‘Part 2—Cross Bolt Hole Inner Chamfer 

Inspection—Bushings Not Removed’’ of the 

Accomplishment Instructions of the service 

bulletin, until the terminating action required 

by paragraph (q) of this AD has been 

accomplished. 

(iii) Before the MLG cylinder is 61⁄2 years 

old since new, since last overhaul, or since 

rework per Boeing Alert Service Bulletin 

767–32A0148, dated December 21, 1995; 

Revision 1, dated October 10, 1996; or 

Revision 2, dated November 30, 2000; 

whichever is later; perform the terminating 

action described in paragraph (q) of this AD. 

(2) If any corrosion is found on the cross 

bolt holes or outer chamfers during the 

detailed inspection required by paragraph (k) 

of this AD, before further flight, remove the 

corrosion per Figure 2 of the service bulletin. 

(i) If all of the corrosion can be removed: 

Before further flight, perform the restoration 

steps shown in Figure 2 of the service 

bulletin; thereafter at intervals not to exceed 

180 days, perform the C.I.C. application on 

the MLG in accordance with ‘‘Part 3—C.I.C. 

Application’’ of the Accomplishment 

Instructions of the service bulletin; and 

perform the terminating action described in 

paragraph (q) of this AD, at the applicable 

time specified in paragraph (k)(2)(i)(A) or 

(k)(2)(i)(B) of this AD.

(A) If the MLG outer cylinder is less than 

5 years old since new, if the MLG was last 

overhauled less than 5 years before May 6, 

2002, or if rework per Boeing Alert Service 

Bulletin 767–32A0148, dated December 21, 

1995; Revision 1, dated October 10, 1996; or 

Revision 2, dated November 30, 2000; was 

accomplished less than 5 years before May 6, 

2002: Within 18 months after performing the 

detailed inspection required by paragraph (k) 

of this AD. 

(B) If the MLG outer cylinder is 5 years old 

or more since new, if the MLG was last 

overhauled 5 years or more before May 6, 

2002, or if rework per Boeing Alert Service 

Bulletin 767–32A0148, dated December 21, 

1995; Revision 1, dated October 10, 1996; or 

Revision 2, dated November 30, 2000; was 

accomplished 5 years or more before May 6, 

2002: Before the MLG outer cylinder is 61⁄2

years old since new, since last overhaul, or 

since rework per Boeing Alert Service 

Bulletin 767–32A0148, dated December 21, 

1995; Revision 1, dated October 10, 1996; or 

Revision 2, dated November 30, 2000; 

whichever is later. 

(ii) If any corrosion cannot be removed, 

before further flight, perform the terminating 

action described in paragraph (q) of this AD. 

(3) If any crack is found anywhere during 

the detailed inspection required in paragraph 

(k) of this AD, or if corrosion in the inner 

cross bolt hole chamfers is found, before 

further flight, perform the terminating action 

described in paragraph (q) of this AD. 

(l) For Category 2 MLG outer cylinders as 

identified in Boeing Alert Service Bulletin 

767–32A0192, dated May 31, 2001: If, 

according to the criteria of paragraph (g) of 

this AD, JC5A may have been used, perform 

the actions specified in both paragraphs (m) 

and (n) of this AD, as applicable, in 

accordance with Boeing Alert Service 

Bulletin 767–32A0192, dated May 31, 2001; 

or Revision 1, dated March 13, 2003. 

(m) For MLGs and MLG outer cylinders 

identified in paragraphs (m)(1) and (m)(2) of 

this AD: Within 90 days after May 6, 2002, 

perform the C.I.C. application on the MLG in 

accordance with ‘‘Part 3—C.I.C. Application’’

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 767–32A0192, 

dated May 31, 2001; or Revision 1, dated 

March 13, 2003. Thereafter, repeat the 

application at intervals not to exceed 180 

days until the terminating action required by 

paragraph (q) of this AD has been 

accomplished. 

(1) MLG outer cylinders that are less than 

3 years old since new. 

(2) MLGs that have been overhauled less 

than 3 years before May 6, 2002. 

(n) Before the MLG outer cylinder is 3 

years old since new or since the last 

overhaul, or within 90 days after May 6, 

2002, whichever is later, perform a detailed 

inspection for cracks and corrosion of the 

cross bolt hole inner chamfer, in accordance 

with ‘‘Part 2—Cross Bolt Hole Inner Chamfer 

Inspection—Bushings Not Removed’’ of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–32A0192, dated May 

31, 2001; or Revision 1, dated March 13, 

2003. 

(1) If no crack or corrosion is found during 

the inspection required by paragraph (n) of 

this AD, before further flight, and thereafter 

at intervals not to exceed 180 days, perform 

the C.I.C. application on the MLG in 

accordance with ‘‘Part 3—C.I.C. Application’’

of the Accomplishment Instructions of the 

service bulletin, until the next MLG 

overhaul. After the next MLG overhaul has 

been completed, no further action is required 

by this AD. 

(2) If any corrosion is found during the 

detailed inspection required by paragraph (n) 

of this AD, before further flight, remove the 

cross bolt bushings and perform the detailed 

inspection specified in paragraph (k) of this 

AD, and remove the corrosion per Figure 2 

of the service bulletin.

(i) If all of the corrosion can be removed, 

perform the actions specified in paragraph 

(n)(2)(i)(A) and (n)(2)(i)(B) of this AD, at the 

applicable times indicated. 

(A) Prior to further flight, perform the 

restoration steps shown in Figure 2 of the 

service bulletin; and thereafter at intervals 

not to exceed 180 days, perform the C.I.C. 

application on the MLG in accordance with 

‘‘Part 3—C.I.C. Application’’ of the 

Accomplishment Instructions of the service 

bulletin. 

(B) Within 18 months after the corrosion 

removal required by paragraph (n)(2) of this 

AD, perform the terminating action described 

in paragraph (q) of this AD. 

(ii) If all the corrosion cannot be removed, 

before further flight, perform the terminating 

action required by paragraph (q) of this AD. 

(3) If any crack is found during the detailed 

inspection required by paragraph (n) of this 

AD, before further flight, perform the 

terminating action described in paragraph (q) 

of this AD. 

Parts Installation 

(o) As of May 6, 2002, no person shall 

install on any airplane an MLG outer 

cylinder unless maintenance records 

conclusively show that JC5A has never been 

used on that MLG outer cylinder, or unless 

it complies with paragraph (q) of this AD. 

Use of JC5A Prohibited 

(p) As of May 6, 2002, no person shall use 

the C.I.C. JC5A in the aft trunnion area of the 

MLG outer cylinder on any airplane. 

Terminating Action 

(q) Perform the terminating action 

(including removal of the existing bushings, 

repair of the aft trunnion area of the outer 

cylinder, and machining and installation of 

new bushings) in accordance with ‘‘Part 4—

Terminating Action’’ of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–32A0192, dated May 31, 2001; or 

Revision 1, dated March 13, 2003. 

Completion of the terminating action 

terminates the requirements for the repetitive 

inspections and C.I.C. applications of this 

AD. 

Credit for Terminating Action 

(r) For all airplanes, accomplishment of the 

actions specified in paragraph (q) of this AD 

is considered acceptable for compliance with 

the requirements of paragraph (e) of AD 

2002–01–13, amendment 39–12607. 

New Requirements of This AD: L/Ns 834 

Through 874 Inclusive 

(s) For airplanes with L/Ns 834 through 

874 inclusive: Do the actions specified in 

paragraphs (s)(1), (s)(2), and (s)(3) of this AD. 

Federal Register / Vol. 69, No. 188 / Wednesday, September 29, 2004 / Proposed Rules 58107

(1) Within 90 days after the effective date 

of this AD, and thereafter at intervals not to 

exceed 180 days: Do the actions specified in 

paragraph (m) of this AD until the 

terminating action required by paragraph (q) 

of this AD has been accomplished. 

(2) Before the MLG outer cylinder is 3 

years old since new or since last overhaul, or 

within 90 days after the effective date of this 

AD, whichever is later: Do the actions as 

specified in paragraph (n) of this AD. 

(3) As of the effective date of this AD, the 

actions specified in paragraphs (o) and (p) of 

this AD must be complied with. 

Reporting Requirement 

(t) Although the service bulletins 

referenced in this AD specify to submit 

certain information to the manufacturer, this 

AD does not include such a requirement. 

Alternative Methods of Compliance 

(AMOCs) 

(u)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, 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 Designated Engineering 

Representative 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 20, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–21820 Filed 9–28–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19202; Directorate 

Identifier 2004–NM–95–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 757 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 

certain Boeing Model 757 series 

airplanes. This proposed AD would 

require identification of the part number 

for the cable assembly for the lower 

anti-collision light, and related 

investigative/corrective actions if 

necessary. This proposed AD is 

prompted by a report of damage caused 

by an electrical arc in a connector on the 

cable assembly for the lower anticollision light. We are proposing this 

AD to prevent an electrical arc in the 

cable assembly for the lower anticollision light, which could result in a 

fire in a flammable leakage zone of the 

airplane.

DATES: We must receive comments on 

this proposed AD by November 15, 

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 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: Marcia Smith, 

Aerospace Engineer, Cabin Safety and 

Environmental Systems Branch, ANM–

150S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6484; 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 relevant 

written data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2004–19202; Directorate Identifier 

2004–NM–95–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. 

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 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 a report of damage 

caused by an electrical arc in a