Federal Register / Vol. 70, No. 23 / Friday, February 4, 2005 / Rules and Regulations 5917

List of Subjects in 7 CFR Part 905 

Grapefruit, Marketing agreements, 

Oranges, Reporting and recordkeeping 

requirements, Tangelos, Tangerines.

■ For the reasons discussed in the 

preamble, 7 CFR Part 905 is amended as 

follows:

PART 905—ORANGES, GRAPEFRUIT, 

TANGERINES, AND TANGELOS 

GROWN IN FLORIDA

■ 1. The authority citation for part 905 

continues to read as follows:

Authority: 7 U.S.C. 601–674.

§ 905.350 [Removed and reserved]

■ 2. Section 905.350 is removed and 

reserved.

Dated: January 31, 2005. 

Kenneth C. Clayton, 

Acting Administrator, Agricultural Marketing 

Service.

[FR Doc. 05–2154 Filed 2–3–05; 8:45 am] 

BILLING CODE 3410–02–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19201; Directorate 

Identifier 2003–NM–100–AD; Amendment 

39–13959; AD 2005–03–03] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

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

Airplanes

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT).

ACTION: Final rule.

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to 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 new AD also requires, 

for certain other airplanes, repetitive 

inspections for cracks or corrosion, 

corrective action if necessary, and 

repetitive C.I.C. applications. This AD is 

prompted by a report that JC5A 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.

DATES: This AD becomes effective 

March 11, 2005. 

The incorporation by reference of a 

certain publication listed in the AD is 

approved by the Director of the Federal 

Register as of March 11, 2005. 

On May 6, 2002 (67 FR 19322, April 

19, 2002), the Director of the Federal 

Register approved the incorporation by 

reference of a certain other publication.

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. 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.

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 U.S. Department of Transportation, 

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

Washington, DC. This docket number is 

FAA–2004–19201; the directorate 

identifier for this docket is 2003–NM–

100–AD.

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: The FAA 

proposed to amend part 39 of the 

Federal Aviation Regulations (14 CFR 

part 39) with an AD to supersede AD 

2002–08–07, amendment 39–12715, (67 

FR 19322, April 19, 2002). The existing 

AD applies to all Boeing Model 767–

200, –300, and –00F series airplanes. 

The proposed AD was published in the 

Federal Register on September 29, 2004 

(69 FR 58103). That action proposed to 

continue to require 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. The action also proposed 

to require, for certain other airplanes, 

repetitive inspections for cracks or 

corrosion, corrective action if necessary, 

and repetitive C.I.C. applications. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been submitted on the proposed AD. 

Support for the Proposed AD 

One commenter supports the 

proposed AD. 

Request To Add Compliance Statement 

One commenter requests that we add 

the verbiage, ‘‘required as indicated, 

unless accomplished previously,’’ to the 

compliance section of the proposed AD. 

The commenter believes this statement 

is needed to obtain credit for the 

inspections and repetitive C.I.C 

applications it accomplished, prior to 

issuance of the proposed AD, on its 

airplanes in accordance with Boeing 

Alert Service Bulletin 767–32A0192, 

Revision 1, dated March 13, 2003. 

We partially agree, since similar 

language to that suggested by the 

commenter is found in paragraph (e) of 

this AD. As part of our effort to use 

plain language in ADs, we have 

rewritten the compliance statement as 

follows: ‘‘You are responsible for having 

the actions required by this AD 

performed within the compliance times 

specified, unless the actions have 

already been done.’’ While the language 

has changed, the intent of the statement 

is the same. Therefore, no further 

change to this AD is necessary in this 

regard. 

Request To Add Credit for Previous 

Accomplishment 

One commenter requests that we add 

a note to the proposed AD, which would 

give credit for work accomplished in 

compliance with AD 2002–08–07. The 

commenter suggests the following note, 

or language similar to this: 

‘‘Accomplishment of the actions 

required by paragraph[s] (a) through (l) 

of AD 2002–08–07 amendment 39–

12715, is acceptable for compliance 

5918 Federal Register / Vol. 70, No. 23 / Friday, February 4, 2005 / Rules and Regulations 

with the requirements of paragraph[s] 

(g) through (r) of this AD. This AD does 

not require that those actions be 

repeated.’’ We infer that the commenter 

believes the proposed AD, as written, 

would require repeating work the 

commenter has already accomplished. 

We do not agree that a credit note is 

necessary because paragraph (e) of this 

AD, as discussed in the first comment, 

already gives credit for any work 

previously accomplished. Operators 

should note that the new requirements 

of paragraph (s) of this AD are 

applicable only to Boeing Model 767–

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

with line numbers (L/Ns) 834 through 

874 inclusive. Furthermore, if an 

operator previously accomplished these 

new required actions on any applicable 

airplane (L/Ns 834 through 874 

inclusive), then that airplane is also in 

compliance, as stated in paragraph (e) of 

this AD. Therefore no change to this AD 

is necessary in this regard. 

Explanation of Change to This AD 

Boeing has received a Delegation 

Option Authorization (DOA). We have 

revised this final rule to delegate the 

authority to approve an alternative 

method of compliance for any repair 

required by this AD to the Authorized 

Representative for the Boeing DOA 

Organization rather than the Designated 

Engineering Representative (DER).

Conclusion 

We have carefully reviewed the 

available data, including the comments 

that have been submitted, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We have determined that these changes 

will neither increase the economic 

burden on any operator nor increase the 

scope of the AD. 

Costs of Compliance 

There are about 848 airplanes of the 

affected design in the worldwide fleet. 

This AD will affect about 357 airplanes 

of U.S. registry. The new requirements 

of this 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 None ........ $65, per application 

cycle.

$23,205 per application cycle. 

Cross Bolt Hole Inspection—Bushings Removed.2 65 None ........ 130 ........................... 46,410. 

Restoration for Bushings Removed ............ 6 65 None ........ 390 ........................... 139,230. 

Cross Bolt Inner Chamfer Inspection—

Bushings Not Removed.

2 65 None ........ 130, per inspection 

cycle.

46,410, per inspection cycle. 

Restoration for Bushings Not Removed ..... 6 65 None ........ 390 ........................... 139,230. 

Terminating Action ...................................... 64 65 $6,356 ...... 10,516 ...................... 3,754,212. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

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 39–12715 (67 FR 

19322, April 19, 2002), and by adding the 

following new airworthiness directive 

(AD):

2005–03–03 Boeing: Amendment 39–13959. 

Docket No. FAA–2004–19201; 

Directorate Identifier 2003–NM–100–AD. 

Effective Date 

(a) This AD becomes effective March 11, 

2005. 

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 

Federal Register / Vol. 70, No. 23 / Friday, February 4, 2005 / Rules and Regulations 5919

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 39–12715 

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 

39–12715), 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 

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. 

5920 Federal Register / Vol. 70, No. 23 / Friday, February 4, 2005 / Rules and Regulations 

(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. 

(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 an 

Authorized Representative for the Boeing 

Delegation Option Authorization 

Organization who has been authorized by the 

Manager, Seattle ACO, to make those 

findings. For a repair method to be approved, 

the repair must meet the certification basis of 

the airplane, and the approval must 

specifically refer to this AD. 

Material Incorporated by Reference 

(v) Unless otherwise specified by this AD, 

the actions shall be done in accordance with 

Boeing Alert Service Bulletin 767–32A0192, 

dated May 31, 2001; or Boeing Alert Service 

Bulletin 767–32A0192, Revision 1, dated 

March 13, 2003. 

(1) The Director of the Federal Register 

approves the incorporation by reference of 

Boeing Alert Service Bulletin 767–32A0192, 

Revision 1, dated March 13, 2003 in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of Boeing Alert Service Bulletin 

767–32A0192, dated May 31, 2001, as of May 

6, 2002 (67 FR 19322, April 19, 2002). 

(3) For copies of the service information, 

contact Boeing Commercial Airplanes, P.O. 

Box 3707, Seattle, Washington 98124–2207. 

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.

Issued in Renton, Washington, on January 

21, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 05–1805 Filed 2–3–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–20250; Directorate 

Identifier 2003–NM–267–AD; Amendment 

39–13961; AD 2005–03–05] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Model MD–90–30 Airplanes

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT).

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is revising an 

existing airworthiness directive (AD), 

which applies to certain McDonnell 

Douglas Model MD–90–30 airplanes. 

This AD requires a one-time general 

visual inspection to detect wire chafing 

damage and to determine adequate 

clearance between the disconnect panel 

structure and the wires above the aft left 

lavatory; and corrective actions, if 

necessary. This new AD revises the 

applicability of the existing AD. This 

AD is prompted by the determination 

that certain airplanes unaffected by the 

existing AD are subject to the unsafe 

condition, and certain other airplanes 

should be removed from the 

applicability. We are issuing this AD to 

prevent damage to certain wires due to 

contact between the wires and the 

adjacent structure, which could result in 

electrical arcing and consequent smoke 

and fire in the cabin.

DATES: Effective February 22, 2005. 

The incorporation by reference of a 

certain publication listed in the AD is 

approved by the Director of the Federal 

Register as of February 22, 2005. 

We must receive comments on this 

AD by April 5, 2005.