Federal Register / Vol. 75, No. 67 / Thursday, April 8, 2010 / Proposed Rules 17887 

TABLE 1—SERVICE BULLETINS—Continued 

Model— Bombardier Service 

Bulletin— Revision— Dated— 

CL–600–2C10, CL–600–2D15, CL–600–2D24 airplanes ... 670BA–24–026 .................... Original ................................ October 23, 2009. 

(i) If the ADG serial number determined in 

paragraph (g) or (h) of this AD is identified 

in paragraph 1.A. of the applicable service 

bulletin listed in Table 1 of this AD, before 

further flight do an inspection to determine 

if the symbol ‘‘24–5’’ is marked on the ADG 

identification plate. A review of airplane 

maintenance records is acceptable in lieu of 

this inspection if the symbol ‘‘24–5’’ mark can 

be conclusively identified from that review. 

(1) If the symbol ‘‘24–5’’ is marked on the 

ADG identification plate, the balance washer 

screws have already been replaced, and no 

further action is required by this paragraph. 

(2) If the symbol ‘‘24–5’’ is not marked on 

the ADG identification plate, before further 

flight replace all balance washer screws with 

new balance washer screws, part number 

MS24667–14, and mark the ADG 

identification plate with symbol ‘‘24–5,’’ in 

accordance with the Accomplishment 

Instructions of the applicable service bulletin 

listed in Table 1 of this AD. 

(j) As of the effective date of this AD, no 

person may install on any airplane, a 

replacement or spare ADG, Hamilton 

Sundstrand part number in the 761339 or 

1711405 series, having one of the serial 

numbers identified in paragraph 1.A. of the 

applicable service bulletin identified in Table 

1 of this AD, unless the ADG is identified 

with the symbol ‘‘24–5’’ on the identification 

plate. 

Actions Accomplished According to 

Previous Issue of Service Bulletin 

(k) Inspections accomplished before the 

effective date of this AD according to 

Bombardier Service Bulletin 601R–24–127, 

dated October 23, 2009, are considered 

acceptable for compliance with the 

corresponding action specified in this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: The 

MCAI specifies to inspect only airplanes 

having certain serial numbers that are part of 

the MCAI applicability. Because the affected 

part could be rotated onto any of the 

airplanes listed in the applicability, this AD 

requires the inspection be done on all 

airplanes. We have coordinated this with the 

TCCA. 

Other FAA AD Provisions 

(l) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. Send information to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone 516–228–7300; fax 516– 

794–5531. Before using any approved AMOC 

on any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(m) Refer to MCAI Canadian Airworthiness 

Directive CF–2009–48, dated December 14, 

2009; and Bombardier Service Bulletins 

601R–24–127, Revision A, dated February 25, 

2010, and 670BA–24–026, dated October 23, 

2009; for related information. 

Issued in Renton, Washington, on April 1, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–7947 Filed 4–7–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0377; Directorate 

Identifier 2009–NM–246–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 767 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Model 767 airplanes. This proposed AD 

would require doing a detailed 

inspection for correct main track 

downstop assembly, thread protrusion, 

and damaged and missing parts of the 

main track downstop assemblies of the 

outboard slats, and related investigative 

and corrective actions if necessary. This 

proposed AD would also require doing 

a detailed inspection for foreign objects 

debris and damage to the wall of the 

track housing of the outboard slats, and 

corrective actions if necessary. This 

proposed AD results from reports of 

broken bolts in the outboard slat main 

track downstop assembly. We are 

proposing this AD to detect and correct 

incorrectly installed main track 

downstop assemblies, which can allow 

the main track downstop hardware to 

fall into the track housing and cause a 

puncture in the track housing when the 

slat is retracted. This condition, if not 

corrected, could result in a fuel leak and 

an increased risk of fire. 

DATES: We must receive comments on 

this proposed AD by May 24, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 


sroberts on DSKD5P82C1PROD with PROPOSALS
17888 Federal Register / Vol. 75, No. 67 / Thursday, April 8, 2010 / Proposed Rules 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6577; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2010–0377; Directorate Identifier 

2009–NM–246–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We have received two reports of 

broken bolts on the main track 

downstop assembly of the outboard slat. 

In one case, the broken bolt was found 

at the bottom of the track housing. The 

main track downstop assembly was 

found to have had only one of the two 

required spacers installed, which 

allowed the bolt to slide and contact the 

wing spar web cutout. This contact 

fractured the bolt and scratched the 

wing spar web cutout. In the second 

case the bolt was found fractured at the 

thread. The bolt, spacers, and nut were 

found at the bottom of the track 

housing, and no damage was found on 

the wing spar web cutout or the track 

housing. An incorrectly installed main 

track downstop assembly can allow the 

main track downstop hardware to fall 

into the track housing, which could 

cause a puncture in the track housing 

when the slat is retracted. This 

condition, if not corrected, could result 

in a fuel leak and an increased risk of 

fire. 

Relevant Service Information 

We have reviewed Boeing Special 

Attention Service Bulletin 767–57– 

0118, dated October 8, 2009. The service 

bulletin describes procedures for doing 

a detailed inspection of the main track 

downstop assemblies of the outboard 

slats number 1 through 5 and 8 through 

12 for correct assembly, thread 

protrusion, and damaged or missing 

parts to make sure that the bolt, nut, and 

two spacers are in place and correctly 

installed, and doing related 

investigative and corrective actions if 

necessary. The related investigative 

actions include doing a detailed 

inspection of the bolt and spacer for 

corrosion and damage, and inspecting 

for looseness of the bolt and nut by 

applying torque to the nut and bolt of 

the main track downstop assembly. The 

corrective actions include: 

• Installing a bolt and spacer with a 

new nut (including applying torque to 

make sure that it has been correctly 

installed). 

• Replacing a missing, corroded, or 

damaged spacer or bolt, and installing a 

new nut. 

• Tightening the existing nut. 

Boeing Special Attention Service 

Bulletin 767–57–0118, dated October 8, 

2009, also describes procedures for 

doing a detailed inspection for foreign 

objects debris and damage to the wall of 

the track housing of the outboard slats 

1 through 5 and slats 8 through 12, and 

corrective actions if necessary. The 

corrective actions include: 

• Removing foreign object debris. 

• Repairing damage. 

• Replacing the track housing or 

contacting Boeing for repair instructions 

and doing the repair. 

FAA’s Determination and Requirements 

of This Proposed AD 

We are proposing this AD because we 

evaluated all relevant information and 

determined the unsafe condition 

described previously is likely to exist or 

develop in other products of these same 

type designs. This proposed AD would 

require accomplishing the actions 

specified in the service information 

described previously, except as 

discussed under ‘‘Differences Between 

the Proposed AD and Service Bulletin.’’ 

Differences Between the Proposed AD 

and Service Bulletin 

Boeing Special Attention Service 

Bulletin 767–57–0118, dated October 8, 

2009, specifies to contact the 

manufacturer for instructions on how to 

repair certain conditions, but this 

proposed AD would require repairing 

those conditions in one of the following 

ways: 

• Using a method that we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 361 airplanes of U.S. 

registry. We also estimate that it would 

take about 8 work-hours per product to 

comply with this proposed AD. The 

average labor rate is $85 per work-hour. 

Required parts would cost $0 per 

product. Based on these figures, we 

estimate the cost of this proposed AD to 

the U.S. operators to be $245,480, or 

$680 per product. 

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 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. 


sroberts on DSKD5P82C1PROD with PROPOSALS
Federal Register / Vol. 75, No. 67 / Thursday, April 8, 2010 / Proposed Rules 17889 

For the reasons discussed above, I 

certify this 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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2010–0377; Directorate Identifier 2009– 

NM–246–AD. 

Comments Due Date 

(a) We must receive comments by May 24, 

2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to The Boeing 

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

–400ER series airplanes, certificated in any 

category, as identified in Boeing Special 

Attention Service Bulletin 767–57–0118, 

dated October 8, 2009. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Unsafe Condition 

(e) This AD results from reports of broken 

bolts in the main track downstop assembly of 

the outboard slat. The Federal Aviation 

Administration is issuing this AD to detect 

and correct incorrectly installed main track 

downstop assemblies, which can allow the 

main track downstop hardware to fall into 

the track housing and cause a puncture in the 

track housing when the slat is retracted. This 

condition, if not corrected, could result in a 

fuel leak and an increased risk of fire. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Inspection 

(g) Within 24 months after the effective 

date of this AD, do the actions specified in 

paragraphs (g)(1) and (g)(2) of this AD. 

(1) Do a detailed inspection for correct 

assembly, thread protrusion, and damaged 

and missing parts of the main track downstop 

assemblies of outboard slats 1 through 5 and 

slats 8 through 12, and do all applicable 

related investigative and corrective actions, 

in accordance with Part 2 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 767–57– 

0118, dated October 8, 2009. Do all 

applicable related investigative and 

corrective actions before further flight. 

(2) Do a detailed inspection for foreign 

objects debris and damage to the wall of the 

track housing of the outboard slats 1 through 

5 and slats 8 through 12, and do all 

applicable corrective actions, in accordance 

with Part 3 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 767–57–0118, dated October 

8, 2009, except as required by paragraph (h) 

of this AD. Do all applicable corrective 

actions before further flight. 

Exception to the Service Bulletin 

(h) If any damage is found during any 

inspection required by paragraph (g)(2) of 

this AD, and Boeing Special Attention 

Service Bulletin 767–57–0118, dated October 

8, 2009, specifies to replace the track housing 

or contact Boeing for appropriate action: 

Before further flight, replace the track 

housing or repair the damage using a method 

approved in accordance with the procedures 

specified in paragraph (j) of this AD. 

Reporting 

(i) Submit a report of positive findings of 

the inspections required by paragraph (g) of 

this AD to the Manager, Seattle Aircraft 

Certification Office (ACO), at the applicable 

time specified in paragraph (i)(1) or (i)(2) of 

this AD. The report must include the 

inspection results, a description of any 

discrepancies found, the airplane registry, 

variable or line number, and the number of 

landings and flight hours on the airplane. 

Under the provisions of the Paperwork 

Reduction Act (44 U.S.C. 3501 et seq.), the 

Office of Management and Budget (OMB) has 

approved the information collection 

requirements contained in this AD and has 

assigned OMB Control Number 2120 0056. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Seattle ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. Send information to ATTN: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6577; fax (425) 

917–6590. Information may be e-mailed to: 9- 

ANM-Seattle-ACO-AMOC-Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that 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. 

Issued in Renton, Washington, on April 1, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–7945 Filed 4–7–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0376; Directorate 

Identifier 2009–NM–267–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 777–200, –200LR, 

–300, and –300ER Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Model 777–200, –200LR, –300, and 

–300ER series airplanes. This proposed 

AD would require removing and 

repairing the sealant at the four lower 

corners of the wing center section and 

the four lower t-chord segment gaps on 

each side of the wing center section. 

This proposed AD results from reports 

of fuel leakage from the center tank. We 

are proposing this AD to detect and 

correct improperly applied sealant, 

which could result in the disbonding 

and displacing of sealant, and 


sroberts on DSKD5P82C1PROD with PROPOSALS