Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Proposed Rules 56383 

Issued in Renton, Washington, on 

September 16, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19232 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–2005–22529; Directorate 

Identifier 2005–NM–099–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

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

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to certain 

Boeing Model 767–200, –300, and 

–300F series airplanes. The existing AD 

currently requires repetitive inspections 

of the lubrication passage and link 

assembly joint in the inboard and 

outboard flaps of the trailing edge for 

discrepancies, and corrective action if 

necessary. This proposed AD would 

require new inspections for cracking or 

severe wear of the bearings of the link 

assembly, and corrective actions if 

necessary. This proposed AD would 

also require inspecting any link 

assembly not previously inspected for 

damage and replacing it with a new 

assembly if necessary. This proposed 

AD also ends the existing repetitive 

inspections for certain airplanes, and 

extends the repetitive interval for the 

existing repetitive inspections and the 

compliance time for the corrective 

action on certain other airplanes. This 

proposed AD also provides an optional 

terminating action that would end the 

repetitive inspections. This proposed 

AD results from additional reports 

indicating fractured bearings of the link 

assembly joint in the inboard and 

outboard flaps of the trailing edge. We 

are proposing this AD to prevent failure 

of the bearings in the link assembly 

joint, which could result in separation 

of the inboard or outboard flap and 

consequent loss of control 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, 

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 service 

information identified in this proposed 

AD. 

FOR FURTHER INFORMATION CONTACT: 

Candice Gerretsen, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6428; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Include the 

docket number ‘‘Docket No. FAA–2005–

22529; Directorate Identifier 2005–NM–

099–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 the DOT’s complete Privacy Act 

Statement in the Federal Register 

published on April 11, 2000 (65 FR 

19477–78), or may can 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 

On January 16, 2002, we issued AD 

2002–01–15, amendment 39–12609 (67 

FR 4328, January 30, 2002), for certain 

Boeing Model 767–200, –300, and 

–300F series airplanes. That AD requires 

repetitive inspections of the lubrication 

passage and link assembly joint in the 

inboard and outboard flaps of the 

trailing edge for discrepancies, and 

corrective action if necessary. That AD 

resulted from reports of fractured 

bearings and blocked lubrication 

passages of the link assembly joint in 

the inboard and outboard flaps of the 

trailing edge. We issued that AD to 

prevent failure of the bearings in the 

link assembly joint, which could result 

in separation of the outboard flap and 

consequent loss of control of the 

airplane. 

Actions Since Existing AD Was Issued 

The preamble to AD 2002–01–15 

explains that we consider the 

requirements ‘‘interim action’’ and were 

considering further rulemaking. We now 

have determined that further 

rulemaking is indeed necessary, and 

this proposed AD follows from that 

determination. 

Since we issued AD 2002–01–15, we 

have received reports of numerous 

additional incidents of fractured 

bearings of the link assembly joint in the 

inboard and outboard flaps of the 

trailing edge. In several of these 

additional incidents, the bearings were 

properly lubricated. Metallurgical 

examination of fractured bearings 

indicated environmentally assisted 

cracking. 

These additional incidents support 

the data referenced in the 

SUPPLEMENTARY INFORMATION section of 

AD 2002–01–15 that indicate that 

bearings of the link assembly joint may 

fail even when they are properly 

lubricated. However, paragraph (b)(1) of 

56384 Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Proposed Rules 

AD 2002–01–15 allows repetitive 

inspections to continue indefinitely 

(i.e., without accomplishment of the 

interim corrective action referenced in 

paragraph (b)(3) of AD 2002–01–15) if 

the lubrication passage is not blocked 

and no fractured bearing or loose or 

damaged joint is found. Based on the 

continued reports of bearing failures, we 

have determined that accomplishment 

of the corrective action specified in the 

existing AD (which involves removing 

the link assembly, inspecting it for 

damage, and replacing it with a new 

assembly if damage is found) would 

ensure the continued operating safety of 

the affected airplane fleet better than 

continued repetitive inspections. 

Accomplishing the interim corrective 

action eliminates the need to repeat the 

inspections for discrepancies of the 

lubrication passage and link assembly 

joint. 

However, based on the results of 

extensive testing performed by the 

manufacturer, we have determined that 

it is appropriate to extend, from 30 days 

to 60 days, the interval for the repetitive 

inspections for discrepancies of the 

lubrication passage and link assembly 

joint for certain airplanes, and to end 

these repetitive inspections for certain 

other airplanes. Also based on the 

results of the extensive testing, we have 

determined that it is appropriate to 

extend the compliance time for doing 

the corrective action (as specified in 

Part 2 of the referenced service bulletin) 

from 6 months to 24 months after the 

initial inspection. Accordingly, we have 

revised paragraphs (f) and (g) of this 

proposed AD (which comprise the 

restatement of the requirements of 

paragraphs (a) and (b) of AD 2002–01–

15). 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 767–27A0167, Revision 

2, dated October 7, 2004. (AD 2002–01–

15 refers to the original issue of that 

service bulletin, dated December 7, 

2000, as the appropriate source of 

service information for the actions 

required by that AD.) The procedures 

described in Part 1, Lubrication Passage 

and Joint Inspection; and Part 2, Link 

Removal, Disassembly, Inspection, and 

Repair; are similar to those described in 

the original issue of the service bulletin, 

except that Revision 2 of the service 

bulletin specifies that the inspection of 

the lubrication passage and joints is a 

detailed visual inspection. (The original 

issue of the service bulletin did not 

specify the type of inspection.) 

Revision 2 of the service bulletin 

includes a new Part 3, Link Removal 

and Bearing Inspection. Part 3 describes 

procedures for repetitively removing the 

link assembly, visually inspecting the 

bearing ball for cracks, and inspecting 

the outer race of the bearing for severe 

wear. If no crack or evidence of severe 

wear is found, the service bulletin 

specifies that the link may be 

reinstalled. If any crack or excessive 

radial play/severe wear is found, the 

service bulletin says to do Part 2 of the 

service bulletin before further flight. 

Accomplishing the actions specified 

in Boeing Alert Service Bulletin 767–

27A0167, Revision 2, is intended to 

adequately address the unsafe 

condition. 

We have also reviewed Boeing Service 

Bulletin 767–27–0196, dated April 21, 

2005, which describes procedures for 

replacing the existing link assemblies of 

the trailing edge flaps with new, 

improved or modified assemblies that 

contain new bearings that use a bearing 

ball of a different material. These new 

bearings are not subject to 

environmentally induced cracking. 

Doing this replacement eliminates the 

need for the repetitive removal and 

inspections of the bearing ball for cracks 

and for severe wear of the outer race of 

the bearing. 

FAA’s Determination and Requirements 

of the Proposed AD 

The unsafe condition described 

previously is likely to exist or develop 

on other airplanes of the same type 

design that may be registered in the U.S. 

at some time in the future. We are 

proposing to supersede AD 2002–01–15. 

For certain airplanes, this proposed AD 

would continue to retain the 

requirements of the existing AD, and 

would extend the repetitive interval for 

the existing inspections and the 

compliance time for the corrective 

action. This proposed AD would also 

require accomplishing the actions 

specified in Boeing Alert Service 

Bulletin 767–27A0167, Revision 2, 

described previously, except as 

discussed under ‘‘Differences Between 

the Proposed AD and Boeing Service 

Bulletin 767–27A0167, Revision 2.’’

This proposed AD would also provide 

for doing Boeing Service Bulletin 767–

27–0196 as an optional terminating 

action for the new repetitive 

inspections. 

Clarification of Requirements of AD 

2002–01–15 

As stated previously, Boeing Alert 

Service Bulletin 767–27A0167, Revision 

2, specifies detailed visual inspections 

of the lubrication passage and joints for 

discrepancies. The original issue of that 

service bulletin did not specify the type 

of inspection that was needed, so, in AD 

2002–01–15, we identify these 

inspections as general visual 

inspections, and include a definition of 

‘‘general visual inspection.’’ As also 

stated previously, the procedures 

described in Part 1, Lubrication Passage 

and Joint Inspection, of Revision 2 of 

the service bulletin are similar to those 

described in the original issue of the 

service bulletin, except for the change in 

terminology. Therefore, for clarification, 

we have revised the inspection 

requirement restated in paragraph (f) of 

this proposed AD to specify a detailed 

inspection. Because the definition of 

this type of inspection is included in the 

service bulletin, it is not necessary to 

include the definition in this proposed 

AD. 

Differences Between the Proposed AD 

and Boeing Service Bulletin 767–

27A0167, Revision 2 

For airplanes on which Part 2 of 

Boeing Service Bulletin 767–27A0167 

(any revision) has not been done, Boeing 

Alert Service Bulletin 767–27A0167, 

Revision 2, specifies a compliance time 

of 90 days after October 7, 2004 (the 

release date of Revision 2 of that service 

bulletin) for doing Part 2 of the service 

bulletin. However, for these airplanes, if 

the lubrication passage has not been 

found blocked and no fractured bearing 

or loose or damaged joint has been 

found during any inspection required by 

paragraph (f) of this proposed AD, this 

proposed AD requires doing Part 2 

within 24 months after the most recent 

inspection required by paragraph (g)(1) 

of this AD. If the lubrication passage has 

been found blocked, but no fractured 

bearing or loose or damaged joint has 

been found, this proposed AD requires 

doing Part 2 within 24 months after the 

initial inspection required by paragraph 

(f) of this proposed AD. 

Part 3 of Boeing Alert Service Bulletin 

767–27A0167, Revision 2, specifies to 

‘‘visually inspect the bearing ball for 

cracks and the outer race for wear.’’ We 

find that the procedures for this 

inspection constitute a detailed 

inspection. Therefore, paragraph (i) of 

this proposed AD would require a 

detailed inspection for cracking of the 

bearing ball and for evidence of severe 

wear of the outer race of the bearing. 

The Accomplishment Instructions of 

Boeing Alert Service Bulletin 767–

27A0167, Revision 2, specify submitting 

a report of any damaged, cracked, or 

fractured bearings or joint pins, this 

proposed AD would not require that 

action. We do not need this information 

from operators. 

Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Proposed Rules 56385 

Costs of Compliance 

There are about 855 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD, at an 

average labor rate of $65 per work hour. 

ESTIMATED COSTS

Action Work 

hours Cost per airplane 

Number of U.S.- 

registered airplanes Fleet cost 

Part 1 of Boeing Service Bulletin 767– 

27A0167 (required by AD 2002–01–15*).

6 $390* ........................................... 332* .................. $129,480*. 

Part 2 of Boeing Service Bulletin 767– 

27A0167 (new proposed action**).

17 $1,105 ......................................... Up to 332** ....... Up to $366,860**. 

Part 3 of Boeing Service Bulletin 767– 

27A0167 (new proposed action).

8 $520, per inspection cycle .......... 371 ................... $192,920, per inspection cycle. 

* Repetitive Part 1 inspections are required only on condition, and only until Part 2 of Boeing Service Bulletin 767–27A0167 has been done. 

** Applies to airplanes on which Part 2 has not been previously accomplished. 

The optional terminating action 

provided in this proposed AD, if 

accomplished, would take about 23 

work hours per airplane, at an average 

labor rate of $65 per work hour. 

Required parts would cost about $3,885 

per airplane. Based on these figures, the 

estimated cost of the optional 

terminating action specified in this 

proposed AD is $5,380 per airplane. 

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 removing amendment 39–12609 (67 

FR 4328, January 30, 2002) and adding 

the following new airworthiness 

directive (AD): 

Boeing: Docket No. FAA–2005–22529; 

Directorate Identifier 2005–NM–099–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by November 14, 2005. 

Affected ADs 

(b) This AD supersedes AD 2002–01–15. 

Applicability 

(c) This AD applies to Boeing Model 767–

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

certificated in any category; identified in 

Boeing Alert Service Bulletin 767–27A0167, 

Revision 2, dated October 7, 2004. 

Unsafe Condition 

(d) This AD results from additional reports 

indicating fractured bearings of the link 

assembly joint in the inboard and outboard 

flaps of the trailing edge. We are issuing this 

AD to prevent failure of the bearings in the 

link assembly joint, which could result in 

separation of the inboard and outboard flap 

and consequent loss of control 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. 

Requirements of AD 2002–01–15 

Initial Inspection 

(f) For airplanes having line numbers 1 

through 819 inclusive, on which Part 2 of 

Boeing Alert Service Bulletin 767–27A0167 

has not been done: Within 90 days after 

February 14, 2002 (the effective date of AD 

2002–01–15), or within 36 months after date 

of manufacture of the airplane, whichever is 

later, do detailed inspections of the 

lubrication passage and link assembly joint 

in the inboard and outboard flaps of the 

trailing edge for discrepancies (e.g., 

lubrication passage blocked, fractured 

bearing, loose or damaged joint); per Part 1 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 767–27A0167, 

dated 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. 

Repetitive Inspections/Corrective Action 

(g) For airplanes having line numbers 1 

through 819 inclusive, on which Part 2 of 

Boeing Alert Service Bulletin 767–27A0167 

has not been done: Do the actions required 

by paragraph (g)(1), (g)(2), or (g)(3) of this AD, 

as applicable, at the time specified, per the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–27A0167, dated 

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,