Federal Register / Vol. 69, No. 220 / Tuesday, November 16, 2004 / Rules and Regulations 67043

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–19569; Directorate 

Identifier 2004–NM–179–AD; Amendment 

39–13869; AD 2004–23–14] 

RIN 2120–AA64

Airworthiness Directives; Boeing 

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

Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 767–200, –300, and 

–300F series airplanes. This AD requires 

reworking the surface of the ground stud 

brackets of the transformer rectifier unit 

(TRU) and the airplane structure 

mounting surface, and measuring the 

resistance from the bracket to the 

structure and the ground lug to the 

bracket using a bonding meter. This AD 

is prompted by a report of loss of all 

direct current (DC) power generation 

during a flight, due to inadequate 

electrical ground path between the 

ground bracket of the TRU and the 

structure. We are issuing this AD to 

prevent depletion of the main battery 

and consequent loss of all DC power, 

which could cause the loss of flight 

critical systems.

DATES: Effective December 1, 2004. 

The incorporation by reference of 

certain publications listed in the AD is 

approved by the Director of the Federal 

Register as of December 1, 2004. 

We must receive comments on this 

AD by January 18, 2005.

ADDRESSES: Use one of the following 

addresses to submit comments on this 

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 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.

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. 

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. 

Examining the Dockets 

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.

FOR FURTHER INFORMATION CONTACT:

Technical information: Louis 

Natsiopoulous, Aerospace Engineer, 

Systems and Equipment Branch, ANM–

130S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6478; fax (425) 917–6590. 

Plain language information: Marcia 

Walters, marcia.walters@faa.gov.

SUPPLEMENTARY INFORMATION: We have 

received a report of loss of DC power 

generation on a Boeing Model 767 

airplane during flight. Investigation by 

Boeing revealed that the operator had 

incorporated Boeing Service Bulletin 

767–24–0119, dated May 14, 1998, and/

or Revision 1, dated December 16, 1999, 

without proper preparation of the 

bonding surface of the ground bracket 

and the airplane structure. The 

inadequate preparation caused the loss 

of an adequate electrical ground path 

between the bracket and frame used for 

the transformer rectifier units (TRU) and 

the main battery charger, which caused 

the subsequent loss of all DC power 

generation. When the operator inspected 

the rest of its Model 767 fleet, it found 

a number of brackets that were not 

properly grounded. This condition, if 

not corrected, could result in depletion 

of the main battery and consequent loss 

of all DC power, which could cause the 

loss of flight critical systems.

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 767–24A0119, Revision 

2, dated August 19, 2004. The service 

bulletin describes procedures for 

reworking the bonding surfaces of the 

ground stud brackets of the TRU and 

airplane structure, and measuring the 

resistance from the bracket to the 

structure and from the ground lug to 

bracket using a bonding meter. The 

reworking includes: 

• Removing the ground stud bracket 

of the TRU; 

• Cleaning the bracket mounting 

surface and airplane structure surface 

for a faying surface bond; 

• Installing the ground bracket 

assembly of the TRU to the surface 

using bolts; 

• Applying fillet sealant to the 

bracket; 

• Applying alodine to the prepared 

surfaces; 

• And applying primer on bare metal 

surface. 

We have also reviewed Boeing 

Information Notice 767–24A0119 IN 01, 

dated October 21, 2004. This 

information notice provides more 

detailed illustrations than those shown 

in Figure 1, Details A and B, of Boeing 

Alert Service Bulletin 767–24A0119, 

Revision 2, dated August 19, 2004. The 

information notice clarifies the Figure 1, 

Step 10, procedure of the 

Accomplishment Instructions in the 

service bulletin. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other airplanes of the same type 

design. Therefore, we are issuing this 

AD to prevent depletion of the main 

battery and consequent loss of all DC 

power, which could cause the loss of 

flight critical systems. This AD requires 

accomplishing the actions specified in 

67044 Federal Register / Vol. 69, No. 220 / Tuesday, November 16, 2004 / Rules and Regulations 

the service information described 

previously, except as discussed below 

in ‘‘Clarification of Error in the Service 

Bulletin.’’

Clarification of Error in the Service 

Bulletin 

Boeing has informed us of an 

inadvertent error in the service bulletin. 

In Step 4, Sheet 3, of Figure 1 of the 

Accomplishment Instructions, the 

service bulletin only specifies to install 

a collar with part number (P/N) 

BACC30M6. However, a second collar 

with P/N BACC30BL6, which is listed 

in paragraph 2.C., ‘‘Parts Necessary For 

Each Airplane,’’ is also acceptable for 

installation. We have included 

paragraph (g) in this AD to allow the 

installation of P/N BACC30BL6 as an 

alternative method of compliance to the 

corresponding requirement of paragraph 

(f) of this AD (which references the 

service bulletin as the appropriate 

source of service information for 

accomplishing the required actions). 

Interim Action 

This is considered to be interim 

action. The manufacturer has advised 

that it currently is developing a 

modification (to add a redundant TRU 

grounding bracket on all 767 airplanes) 

that will address the unsafe condition 

addressed by this AD. Once this 

modification is developed, approved, 

and available, we may consider 

additional rulemaking. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD; therefore, providing notice and 

opportunity for public comment before 

the AD is issued is impracticable, and 

good cause exists to make this AD 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

relevant written data, views, or 

arguments regarding this AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2004–19569; Directorate Identifier 

2004–NM–179–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD. We will consider all 

comments received by the closing date 

and may amend the 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 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 

the clarity of our communications with 

you. You can get more information 

about plain language at http://www/

faa.gov/language and http://

www.plainlanguage.gov.

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 the 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 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 adding 

the following new airworthiness 

directive (AD):

2004–23–14 Boeing: Amendment 39–13869. 

Docket No. FAA–2004–19569; 

Directorate Identifier 2004–NM–179–AD. 

Effective Date 

(a) This AD becomes effective December 1, 

2004. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 767–

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

listed in Boeing Alert Service Bulletin 767–

24A0119, Revision 2, dated August 19, 2004, 

certificated in any category; on which the 

actions of Boeing Service Bulletin 767–24–

0119, dated May 14, 1998, and/or Revision 1, 

dated December 16, 1999, have been done. 

Unsafe Condition 

(d) This AD was prompted by a report of 

loss of all direct current (DC) power 

generation during a flight. The FAA is 

issuing this AD to prevent depletion of the 

main battery and consequent loss of all DC 

power, which could cause the loss of flight 

critical systems. 

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. 

Rework and Measure Resistance 

(f) Within 45 days after the effective date 

of this AD, rework the ground stud bracket 

of the transformer rectifier unit (TRU) and 

structure mounting surface, and measure the 

resistance from the bracket to the structure 

and the grounding lug to the bracket using a 

bonding meter, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–24A0119, Revision 2, 

dated August 19, 2004, as revised by Boeing 

Information Notice 767–24A0119 IN 01, 

dated October 21, 2004, except as provided 

by paragraph (g) of this AD. 

(g) Step 4, Sheet 3 of Figure 1 in the 

Accomplishment Instructions of the service 

bulletin only specifies to install one collar 

with part number (P/N) BACC30M6. 

However, a collar with P/N BACC30BL6 (as 

listed in paragraph 2.C., ‘‘Parts Necessary For 

Each Airplane’’ of the service bulletin) may 

be used as an alternative method of 

compliance (AMOC). 

AMOCs 

(h) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

Federal Register / Vol. 69, No. 220 / Tuesday, November 16, 2004 / Rules and Regulations 67045

requested in accordance with the procedures 

found in 14 CFR 39.19. 

Material Incorporated by Reference 

(i) You must use Boeing Alert Service 

Bulletin 767–24A0119, Revision 2, dated 

August 19, 2004, as revised by Boeing 

Information Notice 767–24A0119 IN 01, 

dated October 21, 2004, to perform the 

actions that are required by this AD, unless 

the AD specifies otherwise. The Director of 

the Federal Register approves the 

incorporation by reference of this document 

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

part 51. For copies of the service information, 

contact Boeing Commercial Airplanes, P.O. 

Box 3707, Seattle, Washington 98124–2207. 

You can review copies at the Docket 

Management Facility, U.S. Department of 

Transportation, 400 Seventh Street SW., 

room PL–401, Nassif Building, Washington, 

DC; or at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

(202) 741–6030, or go to http://

www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html.

Issued in Renton, Washington, on 

November 3, 2004. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–25191 Filed 11–15–04; 8:45 am] 

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2001–NM–182–AD; Amendment 

39–13867; AD 2004–23–12] 

RIN 2120–AA64

Airworthiness Directives; Boeing 

Model 757–200 and –300 Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain Boeing Model 757–

200 and –300 series airplanes. This AD 

requires inspection of the guide arm 

assembly on passenger door number 1 

left for a part mark to determine 

whether the guide arm assembly 

contains an adjuster rod, which was 

incorrectly manufactured, and 

replacement of any such adjuster rod. 

This action is necessary to prevent 

failure of the adjuster rod in the 

passenger door guide arm assembly, 

which could prevent the door from 

opening or closing during normal or 

emergency operations, resulting in the 

inability to evacuate the crew and 

passengers in an emergency. This action 

is intended to address the identified 

unsafe condition.

DATES: Effective December 21, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of December 

21, 2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Boeing Commercial Airplanes, 

P.O. Box 3707, Seattle, Washington 

98124–2207. This information may be 

examined at the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, Rules Docket, 

1601 Lind Avenue, SW., Renton, 

Washington; or at the National Archives 

and Records Administration (NARA). 

For information on the availability of 

this material at NARA, call (202) 741–

6030, or go to: http://www.archives.gov/

federal_register/

code_of_federal_regulations/

ibr_locations.html.

FOR FURTHER INFORMATION CONTACT:

David Crotty, 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) 917–6422; fax (425) 917–6590.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an airworthiness directive (AD) 

that is applicable to certain Boeing 

Model 757–200 and –300 series 

airplanes was published in the Federal 

Register on February 9, 2004 (69 FR 

5939). That action proposed to require 

inspection of the guide arm assembly on 

passenger door number 1 left for a part 

mark to determine whether the guide 

arm assembly contains an adjuster rod, 

which was incorrectly manufactured, 

and replacement of any such adjuster 

rod. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the 

comments received. 

Request To Revise Compliance Time 

One commenter requests that the 

compliance time specified in paragraph 

(b) of the proposed AD be changed from 

‘‘Within 18 months of the effective date 

of this AD’’ to ‘‘Within 18 months of the 

effective date of this AD or prior to 

6,666 total aircraft cycles, whichever 

occurs later.’’ The commenter notes that 

Boeing Special Attention Service 

Bulletin 757–52–0077, dated February 

15, 2001; and Boeing Special Attention 

Service Bulletin 757–52–0078, dated 

February 15, 2001 (both service 

bulletins were referenced as the 

appropriate sources of service 

information for accomplishing the 

proposed AD); suggest replacing any 

applicable adjuster rod before the 

aircraft reaches 6,666 flight cycles. The 

commenter states that Boeing and the 

hardware manufacturer base the cycle 

limits on fatigue analysis. 

We partially agree. We do not agree 

that the compliance time specified in 

paragraph (b) of the final rule should be 

revised. The referenced service bulletins 

specify that the initial inspection should 

be done at the next maintenance time. 

The compliance time of ‘‘within 18 

months of the effective date of this AD’’

allows most operators to inspect during 

scheduled maintenance and is an 

appropriate interval for affected 

airplanes to continue to operate without 

compromising safety. 

However, we have revised the 

compliance times specified in 

paragraphs (c) and (d) of the final rule 

from ‘‘before further flight’’ to ‘‘prior to 

the accumulation of 6,666 total flight 

cycles’’ for the replacement and test of 

the adjuster rod of the guide arm 

assembly in order to align with the 

flight cycle compliance time 

recommended in the referenced service 

bulletins. 

Request To Remove ‘‘Parts Installation’’

Paragraph 

Two commenters request that ‘‘Parts 

Installation’’ paragraph (e) of the 

proposed AD be removed. One 

commenter states that only the adjuster 

rods of the guide arm assemblies on 

passenger door number 1 left are 

defective for airplanes specified in the 

referenced service bulletins. The 

commenter notes that all other adjuster 

rods are not affected. The other 

commenter points out that the 

referenced service bulletins do not 

indicate any spares or existing parts 

accountability concerns. 

We agree with the commenters’

request. Boeing and the part 

manufacturer have accounted for all 

affected parts and, therefore, 

replacement adjuster rods are not 

affected. We have removed paragraph 

(e) from the final rule and reidentified 

the paragraphs that follow. 

Request To Revise Wording 

One commenter requests that the 

wording in the ‘‘Summary’’ paragraph of 

the proposed AD be changed from