Federal Register / Vol. 73, No. 153 / Thursday, August 7, 2008 / Proposed Rules 45891 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0849; Directorate 

Identifier 2008–NM–080–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 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 the 

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: Two operators of A300 

aircraft fitted with General Electric (GE) 

CF6–50 engine series have reported 

cracks on the lower side of Rib 5 in the 

pylon box. Investigations disclosed that 

these cracks are due to the stresses 

resulting from the pressure applied by 

the thrust reverser cowl bumpers. 

Cracking of the engine pylons could 

result in reduced structural integrity of 

the engine support structure. 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 September 8, 2008. 

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. 

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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; 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–2008–0849; Directorate Identifier 

2008–NM–080–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 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 2008–0066, 

dated March 31, 2008 (referred to after 

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

condition for the specified products. 

The MCAI states: 

Two operators of A300 aircraft fitted with 

General Electric (GE) CF6–50 engine series 

have reported cracks on the lower side of Rib 

5 in the pylon box. 

The concerned area is similar on A310 

aircraft fitted with GE CF6–80A or CF6–80C 

series engines. 

Investigations disclosed that these cracks 

are due to the stresses resulting from the 

pressure applied by the thrust reverser cowl 

bumpers. 

As a result of the A310 Extended Service 

Goal (ESG) study, an inspection programme 

of this area is required by this Airworthiness 

Directive (AD). 

A similar inspection programme is being 

contemplated for A300 and A300–600 series 

aircraft. 

Cracking of the engine pylons could 

result in reduced structural integrity of 

the engine support structure. Corrective 

actions include modifying the Rib 5 in 

the pylon box. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Airbus has issued Service Bulletins 

A310–54–2032, Revision 01, dated 

October 8, 2007, and A310–54–2036, 

Revision 02, dated September 28, 2007. 

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. 

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 33 products of U.S. registry. 

We also estimate that it would take 

about 8 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 

$21,120, or $640 per product, per 

inspection cycle. 


rmajette on PRODPC74 with PROPOSALS
45892 Federal Register / Vol. 73, No. 153 / Thursday, August 7, 2008 / Proposed Rules 

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, 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: 

Airbus: Docket No. FAA–2008–0849; 

Directorate Identifier 2008–NM–080–AD. 

Comments Due Date 

(a) We must receive comments by 

September 8, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A310–

203, –204 and –304 airplanes, all serial 

numbers, certificated in any category; 

excluding airplanes that have received 

Airbus Modification 11110 during 

production or that have been modified in 

service in accordance with Airbus Service 

Bulletin A310–54–2032 (Airbus Modification 

11109). 

Subject 

(d) Air Transport Association (ATA) of 

America Code 54: Nacelles/Pylons. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Two operators of A300 aircraft fitted with 

General Electric (GE) CF6–50 engine series 

have reported cracks on the lower side of Rib 

5 in the pylon box. 

The concerned area is similar on A310 

aircraft fitted with GE CF6–80A or CF6–80C 

series engines. 

Investigations disclosed that these cracks 

are due to the stresses resulting from the 

pressure applied by the thrust reverser cowl 

bumpers. 

As a result of the A310 Extended Service 

Goal (ESG) study, an inspection programme 

of this area is required by this Airworthiness 

Directive (AD). 

A similar inspection programme is being 

contemplated for A300 and A300–600 series 

aircraft. 

Cracking of the engine pylons could result in 

reduced structural integrity of the engine 

support structure. Corrective actions include 

modifying the Rib 5 in the pylon box. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Perform a high frequency eddy current 

(HFEC) inspection and a detailed visual 

inspection on the lower side of Rib 5 of the 

left-hand and right-hand pylons, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A310–

54–2036, Revision 02, dated September 28, 

2007. Do the inspections at the times 

specified in paragraph (f)(1)(i) or (f)(1)(ii) of 

this AD, as applicable. 

(i) For Model A310–203 and –204 

airplanes: Inspect at the later of the times 

specified in paragraphs (f)(1)(i)(A) and 

(f)(1)(i)(B) of this AD. 

(A) Prior to the accumulation of 40,000 

total flight cycles or 60,000 total flight hours, 

whichever occurs first. 

(B) Within 250 flight hours after the 

effective date of this AD. 

(ii) For Model A310–304 airplanes: Inspect 

at the later of the times specified in 

paragraphs (f)(1)(ii)(A) and (f)(1)(ii)(B) of this 

AD. 

(A) Prior to the accumulation of 35,000 

total flight cycles or 60,000 total flight hours, 

whichever occurs first. 

(B) Within 250 flight hours after the 

effective date of this AD. 

(2) If no crack is found during any 

inspection required by paragraph (f)(1) of this 

AD: Repeat the inspections thereafter at 

intervals not to exceed 15,000 flight hours. 

(3) If any crack is found during any 

inspection required by paragraph (f)(1) of this 

AD: Before further flight, modify Rib 5 in the 

pylon box in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletins A310–54–2032, Revision 

01, dated October 8, 2007. Accomplishment 

of this modification ends the repetitive 

inspections required by this AD. 

(4) Accomplishment of the HFEC and 

detailed visual inspections before the 

effective date of this AD in accordance with 

Airbus Service Bulletin A310–54–2036, 

Revision 01, dated September 14, 1999, 

meets the corresponding requirements of 

paragraph (f) of this AD. 

(5) Accomplishment of the modification 

before the effective date of this AD in 

accordance with Airbus Service Bulletin 

A310–54–2032, dated May 29, 1996, meets 

the corresponding requirements of paragraph 

(f) of this AD. 

(6) Submit the initial inspection results 

specified in Appendix 01 of Airbus Service 

Bulletin A310–54–2036, Revision 02, dated 

September 28, 2007, at the time specified in 

paragraph (f)(6)(i) or (f)(6)(ii) of this AD. 

(i) If the inspections were done after the 

effective date of this AD: Within 30 days after 

accomplishing the inspections required by 

paragraph (f)(1) of this AD. 

(ii) If the inspections were done prior to 

the effective date of this AD: Within 30 days 

after the effective date of this AD. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: Although 

the MCAI allows further flight after cracks 

are found during compliance with the 

required action, this AD requires that you 

repair the crack(s) before further flight. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, 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: Dan Rodina, Aerospace 

Engineer, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–2125; fax 

(425) 227–1149. Before using any approved 

AMOC on any airplane to which the AMOC 

applies, notify your appropriate principal 

inspector (PI) in the FAA Flight Standards 

District Office (FSDO), or lacking a PI, your 

local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 


rmajette on PRODPC74 with PROPOSALS
Federal Register / Vol. 73, No. 153 / Thursday, August 7, 2008 / Proposed Rules 45893 

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, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI EASA Airworthiness 

Directive 2008–0066, dated March 31, 2008, 

and Airbus Service Bulletins A310–54–2032, 

Revision 01, dated October 8, 2007; and 

A310–54–2036, Revision 02, dated 

September 28, 2007; for related information. 

Issued in Renton, Washington, on July 29, 

2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–18210 Filed 8–6–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0847; Directorate 

Identifier 2008–NM–056–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 777 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 777 airplanes. This 

proposed AD would require doing an 

inspection of the motor operated valve 

(MOV) actuators of the main and center 

fuel tanks for a certain part number; 

replacing the MOV actuator with a new 

MOV actuator if necessary; and 

measuring the electrical resistance of 

the bond from the adapter plate to the 

airplane structure, and corrective 

actions if necessary. This proposed AD 

would also require revising the 

Airworthiness Limitations section of the 

Instructions for Continued 

Airworthiness. This proposed AD 

results from fuel system reviews 

conducted by the manufacturer. We are 

proposing this AD to prevent electrical 

current from flowing through a MOV 

actuator into a fuel tank, which could 

create a potential ignition source inside 

the fuel tank. This condition, 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 September 22, 

2008. 

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 AD, contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207. 

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: 

Margaret Langsted, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6500; 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–2008–0847; Directorate Identifier 

2008–NM–056–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 

unsafe conditions identified as a result 

of these reviews. 

In evaluating these design reviews, we 

have established four criteria intended 

to define the unsafe conditions 

associated with fuel tank systems that 

require corrective actions. The 

percentage of operating time during 

which fuel tanks are exposed to 

flammable conditions is one of these 

criteria. The other three criteria address 

the failure types under evaluation: 

single failures, single failures in 

combination with a latent condition(s), 

and in-service failure experience. For all 

four criteria, the evaluations included 

consideration of previous actions taken 


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