56386 Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Proposed Rules 

December 7, 2000; or Revision 2, dated 

October 7, 2004. After the effective date of 

this AD, only Revision 2 of the service 

bulletin may be used. 

(1) If the lubrication passage is not blocked 

and no fractured bearing or loose or damaged 

joint is found, do paragraph (h) of this AD. 

(2) If the lubrication passage is blocked and 

no fractured bearing or loose or damaged 

joint is found, repeat the inspection required 

by paragraph (f) of this AD at intervals not 

to exceed 60 days, and within 24 months 

after doing the initial inspection, do the 

actions required by paragraph (g)(3) of this 

AD. 

(3) If any fractured bearing or loose or 

damaged joint is found, before further flight, 

do the corrective action (including removal 

of the link assembly, inspection for damage, 

and replacement with a new assembly if 

damaged), as specified in Part 2 of the 

Accomplishment Instructions of the service 

bulletin. 

New Requirements of This AD 

(h) For airplanes having line numbers 1 

through 819 inclusive, on which the 

lubrication passage has not been found 

blocked and no fractured bearing or loose or 

damaged joint has been found, and on which 

Part 2 of Boeing Alert Service Bulletin 767–

27A0167 has not been done: Within 24 

months after the most recent inspection in 

accordance with paragraph (b)(1) of AD 

2002–01–15, remove the link assembly, 

perform a detailed inspection of the link 

assembly for damage, and reinstall the 

undamaged link or replace it with a new link 

assembly that has been inspected and found 

to be free of damage or other discrepancy, in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–27A0167, Revision 2, 

dated October 7, 2004. 

Detailed Inspection of Bearing Ball and Outer 

Race 

(i) For all airplanes: Remove the link 

assembly, and perform a detailed inspection 

for cracking of the bearing ball, and for severe 

wear of the outer race of the bearing, in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–27A0167, Revision 2, 

dated October 7, 2004. Do this action at the 

applicable time specified in paragraph (i)(1) 

or (i)(2) of this AD, as applicable. Then, 

repeat this action at intervals not to exceed 

72 months. If any cracking or severe wear is 

found during any inspection required by this 

paragraph: Before further flight, do the 

corrective action in accordance with Part 2 of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 767–27A0167, 

Revision 2, dated October 7, 2004, or do 

paragraph (j) of this AD. 

(1) For airplanes identified in the service 

bulletin as being in Group 1: Within 72 

months after doing Part 2 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–27A0167, dated 

December 7, 2000; or Revision 2, dated 

October 7, 2004, or within 18 months after 

the effective date of this AD, whichever is 

later. 

(2) For airplanes identified in the service 

bulletin as being in Group 2: Do the initial 

inspection within 72 months since the date 

of issuance of the original standard 

airworthiness certificate or the date of 

issuance of the original export certificate of 

airworthiness; or within 18 months after the 

effective date of this AD; whichever is later. 

Optional Terminating Action 

(j) For all airplanes: Replacing the existing 

link assemblies of the trailing edge flaps with 

new, improved or modified assemblies that 

contain new bearings, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–27–0196, dated April 

21, 2005, ends the repetitive removal/ 

inspections required by paragraph (g), (h), 

and (i) of this AD, as applicable. 

Actions Accomplished Previously 

(k) Inspections and corrective actions done 

before the effective date of this AD in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–27A0167, Revision 1, dated June 6, 

2002, are acceptable for compliance with the 

corresponding actions required by this AD. 

No Reporting Requirement 

(l) Although Boeing Alert Service Bulletin 

767–27A0167, Revision 2, dated October 7, 

2004, specifies to submit certain information 

to the manufacturer, this AD does not require 

that action. 

Alternative Methods of Compliance (AMOCs) 

(m)(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 

Commercial Airplanes 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. 

(3) Before using any AMOC approved in 

accordance with 14 CFR 39.19 on any 

airplane to which the AMOC applies, notify 

the appropriate principal inspector in the 

FAA Flight Standards Certificate Holding 

District Office. 

(4) AMOCs approved previously according 

to AD 2002–01–15 are approved as AMOCs 

for the corresponding provisions of this AD. 

Issued in Renton, Washington, on 

September 16, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19233 Filed 9–26–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22523; Directorate 

Identifier 2005–NM–058–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 767 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Boeing Model 767 airplanes. 

This proposed AD would require 

drilling a drain hole in the flanged tubes 

for the E1A and E1B elevator control 

cable aft pressure seals; doing repetitive 

inspections for dirt, loose particles, or 

blockage of the flanged tube and drain 

hole for the E1A and E1B elevator 

control cable aft pressure seals and 

corrective action if necessary; replacing 

the aft air-intake duct assembly with a 

new or modified aft air-intake duct 

assembly and installing a dripshield; 

and modifying the side brace fittings 

and installing gutters on the horizontal 

stabilizer center section. This proposed 

AD results from reports of stiff operation 

of the elevator pitch control system and 

jammed elevator controls. We are 

proposing this AD to prevent moisture 

from collecting and freezing on the 

elevator control system components, 

which could limit the ability of the 

flightcrew to make elevator control 

inputs and result in reduced 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by November 14, 

2005. 

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, 

Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Proposed Rules 56387 

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

through Friday, except Federal holidays. 

Contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for the service 

information identified in this proposed 

AD. 

FOR FURTHER INFORMATION CONTACT: 

Kelly McGuckin, Aerospace Engineer, 

Systems and Equipment Branch, ANM–

130S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6490; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

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 in the 

ADDRESSES section. Include the docket 

number ‘‘FAA–2005–22523; Directorate 

Identifier 2005–NM–058–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 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 may 

review DOT’s complete Privacy Act 

Statement in the Federal Register 

published on April 11, 2000 (65 FR 

19477–78), or you may visit http:// 

dms.dot.gov. 

Examining the Docket 

You may 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 Docket 

Management System receives them. 

Discussion 

We have received reports of stiff 

operation of the elevator pitch control 

system and jammed elevator controls on 

Model 767 airplanes. One incident 

involved difficulty in flaring the 

airplane and resulted in a subsequent 

hard landing. This incident as well as 

one other incident was caused by 

moisture collecting and freezing onto 

the left elevator cables at the aft 

pressure bulkhead cable seats. Another 

incident involved a leaking auxiliary 

power unit (APU) intake duct seal, 

which allowed water to collect and 

freeze onto the linear variable 

differential transducer (LVDT) for the 

center elevator autopilot. The 

manufacturer also determined that 

water could enter section 48 of the 

airplane through the stabilizer side of 

the body fairing panels. These 

conditions, if not corrected, could limit 

the ability of the flightcrew to make 

elevator control inputs and result in 

reduced controllability of the airplane. 

Relevant Service Information 

We have reviewed Boeing Service 

Bulletin 767–27A0192, Revision 1, 

dated March 17, 2005 (for Model 767–

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

and Boeing Alert Service Bulletin 767–

27A0193, dated December 4, 2003 (for 

Model 767–400ER series airplanes). The 

service bulletins describe procedures for 

drilling a drain hole in the flanged tubes 

for the E1A and E1B elevator control 

cable aft pressure seals. 

We have also reviewed Boeing Service 

Bulletin 767–27–0204, dated January 27, 

2005 (for Model 767–200, –300, and 

–300F series airplanes); and Boeing 

Service Bulletin 767–27–0205, dated 

January 27, 2005 (for Model 767–400ER 

series airplanes). The service bulletins 

describe procedures for doing repetitive 

inspections for dirt, loose particles, or 

blockage of the flanged tube and drain 

hole for the E1A and E1B elevator 

control cable aft pressure seals and 

corrective action if necessary. The 

corrective action includes cleaning the 

flanged tube and drain hole. 

We have also reviewed Boeing Alert 

Service Bulletin 767–49A0035, Revision 

1, dated December 11, 2003 (for certain 

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

airplanes). The service bulletin 

describes procedures for replacing the 

aft air-intake duct assembly with a new 

or modified aft air-intake duct assembly 

and installing a dripshield. 

We have also reviewed Boeing Alert 

Service Bulletin 767–51A0027, dated 

December 9, 2004 (for Model 767–200, 

–300, and –300F series airplanes); and 

Boeing Alert Service Bulletin 767–

51A0028, dated December 9, 2004 (for 

Model 767–400ER series airplanes). The 

service bulletins describe procedures for 

modifying the side brace fittings and 

installing gutters on the horizontal 

stabilizer center section. The 

modification includes drilling a drain 

hole, doing a dye penetrant inspection 

for cracks of the drain hole, and 

applying certain finishes. 

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. For this reason, we are 

proposing this AD, which would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between the Proposed AD 

and Service Bulletins.’’

Differences Between the Proposed AD 

and Service Bulletins 

Boeing Service Bulletin 767–27–0204, 

dated January 27, 2005; and Boeing 

Service Bulletin 767–27–0205, dated 

January 27, 2005; specify an inspection 

threshold of 24 months after the 

delivery date of the airplane. However, 

paragraph (g)(2)(ii) of this proposed AD 

specifies an inspection threshold of 24 

months after the date of issuance of the 

original standard airworthiness 

certificate or the date of issuance of the 

original export certificate of 

airworthiness. This decision is based on 

our determination that ‘‘delivery date’’

may be interpreted differently by 

different operators. We find that our 

proposed terminology is generally 

understood within the industry and 

records will always exist that establish 

these dates with certainty. 

Boeing Alert Service Bulletin 767–

51A0027, dated December 9, 2004; and 

Boeing Alert Service Bulletin 767–

51A0028, dated December 9, 2004; do 

not specify a corrective action if cracks 

are found during the dye penetrant 

inspection for cracks of the drain hole 

specified in Figure 2 of the service 

bulletins. This proposed AD would 

require operators to repair this 

condition according to a method 

approved by the FAA. 

Clarification of Inspection Terminology 

In this proposed AD, the inspections 

specified in Boeing Service Bulletin 

767–27–0204, dated January 27, 2005; 

and Boeing Service Bulletin 767–27–

56388 Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Proposed Rules 

0205, dated January 27, 2005; are 

referred to as a ‘‘detailed inspection.’’

We have included the definition for a 

detailed inspection in a note in the 

proposed AD. 

Costs of Compliance 

There are about 900 airplanes of the 

affected design in the worldwide fleet. 

This proposed AD would affect about 

410 airplanes of U.S. registry. The 

following table provides the estimated 

costs for U.S. operators to comply with 

this proposed AD. The average labor 

rate per hour is $65. We estimate that 

this proposed AD may have a total fleet 

cost of up to $1,789,953 for the initial 

inspection and modifications as well as 

a fleet cost of $26,650 per inspection 

cycle for the repetitive inspections. 

ESTIMATED COSTS

Airplanes Action Work 

hours Parts Cost per airplane 

Model 767 airplanes identified in Boeing Service Bulletin 767–27A0192, Revision 1, dated March 17, 

2005; and Boeing Alert Service Bulletin 767–

27A0193, dated December 4, 2003.

Drain hole addition 2 $0 ....................................... $130. 

Model 767 airplanes identified in Boeing Service Bulletin 767–27–0204, dated January 27, 2005; and 

Boeing Service Bulletin 767–27–0205, dated January 

27, 2005.

Drain Hole Inspection.1 $0 ....................................... $65, per inspection cycle. 

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

identified in Boeing Alert Service Bulletin 767–

49A0035, Revision 1, dated December 11, 2003.

Aft Air-intake Duct 

Assembly and 

Dripshield Installation.

4 $1,462 for rework kit (optional—$18,985 for new 

assembly used for first 

replacement to generate 

a spare assembly).

$1,722 with rework kit (optional—$19,245 with new 

assembly used for first 

replacement to generate 

a spare assembly). 

Model 767 airplanes dentified in Boeing Alert Service 

Bulletin 767–51A0027, dated December 9, 2004; and 

Boeing Alert Service Bulletin 767–51A0028, dated 

December 9, 2004.

Gutter Installation 9 $1,821 ................................ $2,406. 

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 

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 and placed it in the 

AD docket. 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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

Boeing: Docket No. FAA–2005–22523; 

Directorate Identifier 2005–NM–058–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by November 14, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 767–

200, –300, –300F, and –400ER series 

airplanes, certificated in any category; as 

identified in Boeing Service Bulletin 767–

27A0192, Revision 1, dated March 17, 2005; 

Boeing Alert Service Bulletin 767–27A0193, 

dated December 4, 2003; Boeing Alert Service 

Bulletin 767–49A0035, Revision 1, dated 

December 11, 2003; Boeing Service Bulletin 

767–27–0204, dated January 27, 2005; Boeing 

Service Bulletin 767–27–0205, dated January 

27, 2005; Boeing Alert Service Bulletin 767–

51A0027, dated December 9, 2004; and 

Boeing Alert Service Bulletin 767–51A0028, 

dated December 9, 2004. 

Unsafe Condition 

(d) This AD results from reports of stiff 

operation of the elevator pitch control system 

and jammed elevator controls. We are issuing 

this AD to prevent moisture from collecting 

and freezing on the elevator control system 

components, which could limit the ability of 

the flightcrew to make elevator control inputs 

and result in reduced controllability of the 

airplane. 

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. 

Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Proposed Rules 56389 

Inspections, Modifications, Replacements, 

and Corrective Actions 

(f) For airplanes identified in Boeing 

Service Bulletin 767–27A0192, Revision 1, 

dated March 17, 2005; and Boeing Alert 

Service Bulletin 767–27A0193, dated 

December 4, 2003: Within 18 months after 

the effective date of this AD, drill a drain 

hole in the flanged tubes for the E1A and E1B 

elevator control cable aft pressure seals by 

doing all the actions specified in the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–727A0192, Revision 1, 

dated March 17, 2005 (for Model 767–200, 

–300, and –300F series airplanes); and 

Boeing Alert Service Bulletin 767–27A00193, 

dated December 4, 2003 (for Model 767–

400ER series airplanes); as applicable. 

(g) For airplanes identified in Boeing 

Service Bulletin 767–27–0204, dated January 

27, 2005; and Boeing Service Bulletin 767–

27–0205, dated January 27, 2005: At the 

applicable time specified in paragraph (g)(1) 

or (g)(2) of this AD, do a detailed inspection 

for dirt, loose particles, or blockage of the 

flanged tube and drain hole for the E1A and 

E1B elevator control cable aft pressure seals, 

and any applicable corrective action, by 

doing all the actions specified in the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–27–0204, dated January 

27, 2005 (for Model 767–200, –300, and 

–300F series airplanes); and Boeing Service 

Bulletin 767–27–0205, dated January 27, 

2005 (for Model 767–400ER series airplanes); 

as applicable. Do any applicable corrective 

actions before further flight. Repeat the 

detailed inspection thereafter at intervals not 

to exceed 24 months. 

(1) For airplanes identified in paragraph (g) 

that are also identified in paragraph (f) of this 

AD: Do the inspection at the time specified 

in paragraph (g)(1)(i) or (g)(1)(ii) of this AD, 

whichever occurs later. 

(i) Within 24 months after doing the 

actions required by paragraph (f) of this AD. 

(ii) Within 24 months after the effective 

date of this AD. 

(2) For airplanes identified in paragraph (g) 

that are not identified in paragraph (f) of this 

AD: Do the inspection at the time specified 

in paragraph (g)(2)(i) or (g)(2)(ii) of this AD, 

whichever occurs later. 

(i) Within 24 months after the effective 

date of this AD. 

(ii) Within 24 months since the date of 

issuance of the original standard 

airworthiness certificate or the date of 

issuance of the original export certificate of 

airworthiness. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘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.’’

(h) For airplanes identified in Boeing Alert 

Service Bulletin 767–49A0035, Revision 1, 

dated December 11, 2003: Within 18 months 

after the effective date of this AD, replace the 

aft air-intake duct assembly with a new or 

modified aft air-intake duct assembly and 

install a dripshield by doing all the actions 

specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–49A0035, Revision 1, dated December 

11, 2003. 

(i) For airplanes identified in Boeing Alert 

Service Bulletin 767–51A0027, dated 

December 9, 2004; and Boeing Alert Service 

Bulletin 767–51A0028, dated December 9, 

2004: Within 60 months after the effective 

date of this AD, modify the side brace fittings 

and install gutters on the horizontal stabilizer 

center section, by doing all the actions 

specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–51A0027, dated December 9, 2004 (for 

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

airplanes); and Boeing Alert Service Bulletin 

767–51A0028, dated December 9, 2004 (for 

Model 767–400ER series airplanes); as 

applicable; except if cracks are found during 

the dye penetrant inspection specified in 

Figure 2 of the service bulletins, this AD 

requires, before further flight, operators to 

repair this condition according to a method 

approved by the Manager, Seattle Aircraft 

Certification Office (ACO), FAA. For a repair 

method to be approved by the Manager, 

Seattle ACO, as required by this paragraph, 

the Manager’s approval letter must 

specifically refer to this AD. 

Actions Accomplished According to 

Previous Issue of Service Bulletin 

(j) Actions accomplished before the 

effective date of this AD according to Boeing 

Alert Service Bulletin 767–27A0192, dated 

December 4, 2003, are considered acceptable 

for compliance with the corresponding 

actions specified in this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(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) Before using any AMOC approved in 

accordance with 14 CFR 39.19 on any 

airplane to which the AMOC applies, notify 

the appropriate principal inspector in the 

FAA Flight Standards Certificate Holding 

District Office. 

Issued in Renton, Washington, on 

September 16, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19234 Filed 9–26–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22524; Directorate 

Identifier 2005–NM–135–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200, A330–300, A340–200, and 

A340–300 Series Airplanes, and Model 

A340–541 and A340–642 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Airbus Model A330–200, A330–

300, A340–200, and A340–300 series 

airplanes, and A340–541 and A340–642 

airplanes. This proposed AD would 

require inspecting to determine if 

certain emergency escape slides/slide 

rafts (referred to as slide/rafts) are 

installed in certain crew/passenger 

doors; and, if so, performing a one-time 

inspection to determine if the electrical 

harnesses of the slide/rafts are properly 

routed, and rerouting the harnesses if 

necessary. This proposed AD results 

from a report that a slide/raft failed to 

deploy properly during a deployment 

test. We are proposing this AD to detect 

and correct improper routing of the 

electrical harnesses of certain slide/ 

rafts, which could prevent proper 

deployment of the slide/rafts and delay 

evacuation of passengers and flightcrew 

during an emergency. 

DATES: We must receive comments on 

this proposed AD by October 27, 2005. 

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. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France,