Federal Register / Vol. 74, No. 200 / Monday, October 19, 2009 / Proposed Rules 53433 

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. 

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: 

Boeing: Docket No. FAA–2008–0295; 

Directorate Identifier 2007–NM–298–AD. 

Comments Due Date 

(a) We must receive comments by 

November 13, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Boeing Model 

757–200, –200PF, –200CB, and –300 series 

airplanes, certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 32: Landing Gear. 

Unsafe Condition 

(e) This AD results from reports of cracked 

and broken aluminum springs. We are 

issuing this AD to detect and correct cracked 

or broken springs. A cracked or broken spring 

could separate from the airplane and result 

in potential hazard to persons or property on 

the ground, or ingestion into the engine with 

engine damage and potential shutdown, or 

damage to the airplane. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Inspections and Corrective Actions 

(g) At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Special Attention Service Bulletin 757–32– 

0176, Revision 1, dated October 16, 2008, 

except that where Boeing Special Attention 

Service Bulletin 757–32–0176, Revision 1, 

dated October 16, 2008, specifies a 

compliance time after the date ‘‘on this 

service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD: Do 

a general visual inspection to determine the 

material (aluminum or composite) of the two 

springs in the spin brake assemblies in the 

nose wheel well. A review of airplane 

maintenance records is acceptable in lieu of 

this inspection if the material can be 

conclusively determined from that review. 

Do all applicable related investigative and 

corrective actions, and all repetitive 

inspections thereafter, at the applicable time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Special Attention Service Bulletin 

757–32–0176, Revision 1, dated October 16, 

2008. Do all actions in accordance with 

Boeing Special Attention Service Bulletin 

757–32–0176, Revision 1, dated October 16, 

2008. 

Optional Terminating Actions 

(h) Replacing an aluminum spin brake 

assembly with a spin brake assembly made 

of composite material in accordance with 

Figure 5 of Boeing Special Attention Service 

Bulletin 757–32–0176, Revision 1, dated 

October 16, 2008, ends the repetitive 

inspections required by paragraph (g) of this 

AD for that spring. 

(i) Replacing an aluminum spring with a 

spring made of corrosion–resistant steel 

(CRES), in accordance with Figure 6 of 

Boeing Special Attention Service Bulletin 

757–32–0176, Revision 1, dated October 16, 

2008, ends the repetitive inspections 

required by paragraph (g) of this AD for that 

spring. 

Parts Installation 

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

person may install an aluminum spring on 

any airplane unless it has been inspected and 

all applicable related investigative and 

corrective actions have been applied in 

accordance with the requirements of 

paragraph (g) of this AD. 

Credit for Previous Revision of Service 

Bulletin 

(k) Actions done before the effective date 

of this AD in accordance with Boeing Special 

Attention Service Bulletin 757–32–0176, 

dated September 10, 2007, are acceptable for 

compliance with the corresponding 

requirements of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(l)(1) The Manager, Seattle Aircraft 

Certification Office (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: Chris 

Hartman, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6432; fax (425) 917–6590. Or, email information to 9-ANM-Seattle-ACOAMOC-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 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. 

Issued in Renton, Washington, on October 

5, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–24984 Filed 10–16–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0912; Directorate 

Identifier 2009–NM–047–AD] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited Model 

BAe 146 and Avro 146–RJ Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 


cprice-sewell on DSK2BSOYB1PROD with PROPOSALS
53434 Federal Register / Vol. 74, No. 200 / Monday, October 19, 2009 / Proposed Rules 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: Reports have been 

received of finding corrosion at the 

Frame 29 wing-to-fuselage attachment 

lug plate joint. This condition, if not 

detected and corrected, could result in 

a degradation of the structural integrity 

of Frame 29 and the wing-to-fuselage 

attachment. 

The unsafe condition is degradation 

of the structural integrity of Frame 29 

and the wing-to-fuselage attachment, 

which could result in loss of control of 

the airplane. The proposed AD would 

require actions that are intended to 

address the unsafe condition described 

in the MCAI. 

DATES: We must receive comments on 

this proposed AD by December 3, 2009. 

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 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact BAE Systems 

Regional Aircraft, 13850 McLearen 

Road, Herndon, Virginia 20171; 

telephone 703–736–1080; e-mail 

raebusiness@baesystems.com; Internet 

http://www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. 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 

or 425–227–1152. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office 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 Operations 

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: 

Todd Thompson, Aerospace Engineer, 

Aerospace Engineer, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, 1601 Lind Avenue, 

SW., Renton, Washington 98057–3356; 

telephone (425) 227–1175; fax (425) 

227–1149. 

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–2009–0912; Directorate Identifier 

2009–NM–047–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 based on those comments. 

We have lengthened the 30-day 

comment period for proposed ADs that 

address MCAI originated by aviation 

authorities of other countries to provide 

adequate time for interested parties to 

submit comments. The comment period 

for these proposed ADs is now typically 

45 days, which is consistent with the 

comment period for domestic transport 

ADs. 

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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2009–0046, 

dated March 2, 2009 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Reports have been received of finding 

corrosion at the Frame 29 wing-to-fuselage 

attachment lug plate joint. This condition, if 

not detected and corrected, could result in a 

degradation of the structural integrity of 

Frame 29 and the wing-to-fuselage 

attachment. 

The current method of inspecting the 

Frame 29 wing-to-fuselage attachment lug 

plate joint for corrosion is not considered 

adequate for finding corrosion in this 

particular area. 

To address this concern, BAE Systems 

(Operations) Limited has published 

Inspection Service Bulletin ISB.53–213, 

which replaces current Maintenance Review 

Board Report Structurally Significant Items 

Task 53–20–103 (equal to Maintenance 

Planning Document Tasks 532003–DVI– 

10000–1, 532003–DVI–10000–2 and 532003– 

DVI–10000–3) and Corrosion Prevention and 

Control Programme Task C53–230–02–01. 

For the reason described above, this AD 

requires [detailed] repetitive inspections of 

the Frame 29 wing-to-fuselage attachment lug 

plate joint [for discrepancies, which are 

corrosion and fatigue cracking of the bolts 

and fastener bores; degraded, cracked, 

missing, and poor condition sealant] and 

repair(s) [which include replacing bolts, 

contacting BAE Systems for repair 

instructions and doing the repair, and reapplying sealant], as necessary. 

The unsafe condition is degradation of 

the structural integrity of Frame 29 and 

the wing-to-fuselage attachment, which 

could result in loss of control of the 

airplane. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

BAE Systems (Operations) Limited 

has issued Inspection Service Bulletin 

ISB.53–213, dated May 21, 2008. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 


cprice-sewell on DSK2BSOYB1PROD with PROPOSALS
Federal Register / Vol. 74, No. 200 / Monday, October 19, 2009 / Proposed Rules 53435 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a note within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 1 product of U.S. registry. 

We also estimate that it would take 

about 12 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $80 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$960. 

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. 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it 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: 

BAE Systems (Operations) Limited 

(Formerly British Aerospace Regional 

Aircraft): Docket No. FAA–2009–0912; 

Directorate Identifier 2009–NM–047–AD. 

Comments Due Date 

(a) We must receive comments by 

December 3, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to BAE Systems 

(Operations) Limited Model BAe 146–100A, 

–200A, and –300A series airplanes, and BAE 

Systems (Operations) Limited Model Avro 

146–RJ70A, 146–RJ85A, and 146–RJ100A 

airplanes, certificated in any category, all 

serial numbers. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Reports have been received of finding 

corrosion at the Frame 29 wing-to-fuselage 

attachment lug plate joint. This condition, if 

not detected and corrected, could result in a 

degradation of the structural integrity of 

Frame 29 and the wing-to-fuselage 

attachment. 

The current method of inspecting the 

Frame 29 wing-to-fuselage attachment lug 

plate joint for corrosion is not considered 

adequate for finding corrosion in this 

particular area. 

To address this concern, BAE Systems 

(Operations) Limited has published 

Inspection Service Bulletin ISB.53–213, 

which replaces current Maintenance Review 

Board Report Structurally Significant Items 

Task 53–20–103 (equal to Maintenance 

Planning Document Tasks 532003–DVI– 

10000–1, 532003–DVI–10000–2 and 532003– 

DVI–10000–3) and Corrosion Prevention and 

Control Programme Task C53–230–02–01. 

For the reason described above, this AD 

requires repetitive [detailed] inspections of 

the Frame 29 wing-to-fuselage attachment lug 

plate joint [for discrepancies, which are 

corrosion and fatigue cracking of the bolts 

and fastener bores; degraded, cracked, 

missing, and poor condition sealant] and 

repair(s) [which include replacing bolts, 

contacting BAE Systems for repair 

instructions and doing the repair and reapplying sealant], as necessary. 

The unsafe condition is degradation of the 

structural integrity of Frame 29 and the wingto-fuselage attachment, which could result in 

loss of control of the airplane. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within 24 months after the effective 

date of this AD, do a detailed inspection for 

discrepancies of the frame 29 wing-tofuselage attachment lug plate joint, in 

accordance with the Accomplishment 

Instructions of BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.53– 

213, dated May 21, 2008. 

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.’’ 

(2) Repeat the inspection required by 

paragraph (f)(1) of this AD thereafter at 

intervals not to exceed 48 months. 

(3) During any inspection required by 

paragraph (f)(1) or (f)(2) of this AD, if it is not 

possible to replace a removed bolt with 

another bolt having the same part number as 

a replacement item, before further flight, 

contact BAE Systems to replace the removed 

bolt with an alternative bolt and do the 

approved BAE Systems repair. 

(4) If during any inspection required by 

paragraph (f)(1) or (f)(2) of this AD, any 

discrepancy is found, before further flight, 

repair in accordance with paragraph 2.C. of 

the Accomplishment Instructions of BAE 

Systems (Operations) Limited Inspection 

Service Bulletin ISB.53–213, dated May 21, 

2008. 

(5) Although BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.53– 

213, dated May 21, 2008, specifies to submit 

certain information to the manufacturer, this 

AD does not include that requirement. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows. 

Although BAE Systems (Operations) Limited 

Inspection Service Bulletin ISB.53–213, 

dated May 21, 2008, and European Aviation 

Safety Agency AD 2009–0046, dated March 

2, 2009, specify to submit certain information 

to the manufacturer, this AD does not 

include that requirement. 


cprice-sewell on DSK2BSOYB1PROD with PROPOSALS
53436 Federal Register / Vol. 74, No. 200 / Monday, October 19, 2009 / Proposed Rules 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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: Todd Thompson, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1175; fax (425) 227–1149. 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. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2009– 

0046, dated March 2, 2009; and BAE Systems 

(Operations) Limited Inspection Service 

Bulletin ISB.53–213, dated May 21, 2008; for 

related information. 

Issued in Renton, Washington, on October 

5, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–24985 Filed 10–16–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0908; Directorate 

Identifier 2009–NM–067–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 757 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 

Boeing Model 757 airplanes. This 

proposed AD would require replacing 

the power control relays for the fuel 

boost pumps and override pumps with 

new relays having a ground fault 

interrupt (GFI) feature. This proposed 

AD results from fuel system reviews 

conducted by the manufacturer. We are 

proposing this AD to prevent damage to 

the fuel pumps caused by electrical 

arcing that could introduce an ignition 

source in the fuel tank, which, in 

combination with flammable fuel 

vapors, could result in a fuel tank 

explosion and consequent loss of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by December 3, 2009. 

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 or 425–227–1152. 

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: 

Georgios Roussos, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6482; 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–2009–0908; Directorate Identifier 

2009–NM–067–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 

The FAA has examined the 

underlying safety issues involved in fuel 

tank explosions on several large 

transport airplanes, including the 

adequacy of existing regulations, the 

service history of airplanes subject to 

those regulations, and existing 

maintenance practices for fuel tank 

systems. As a result of those findings, 

we issued a regulation titled ‘‘Transport 

Airplane Fuel Tank System Design 

Review, Flammability Reduction and 

Maintenance and Inspection 

Requirements’’ (66 FR 23086, May 7, 

2001). In addition to new airworthiness 

standards for transport airplanes and 

new maintenance requirements, this 

rule included Special Federal Aviation 

Regulation No. 88 (‘‘SFAR 88,’’ 

Amendment 21–78, and subsequent 

Amendments 21–82 and 21–83). 

Among other actions, SFAR 88 

requires certain type design (i.e., type 

certificate (TC) and supplemental type 

certificate (STC)) holders to substantiate 

that their fuel tank systems can prevent 

ignition sources in the fuel tanks. This 

requirement applies to type design 

holders for large turbine-powered 

transport airplanes and for subsequent 

modifications to those airplanes. It 

requires them to perform design reviews 

and to develop design changes and 

maintenance procedures if their designs 

do not meet the new fuel tank safety 

standards. As explained in the preamble 

to the rule, we intended to adopt 

airworthiness directives to mandate any 

changes found necessary to address 


cprice-sewell on DSK2BSOYB1PROD with PROPOSALS