Federal Register / Vol. 72, No. 61 / Friday, March 30, 2007 / Proposed Rules 15067 

Issued in Renton, Washington, on March 

23, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–5908 Filed 3–29–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27741; Directorate 

Identifier 2006–NM–261–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–201, –202, –203, –223, –243, 

–301, –321, –322, –323, –341, –342, and 

–343 Airplanes; and Model A340–200 

and –300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (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) 

issued 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 keel beam rupture, which 

affects the structural integrity of the 

area. 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 April 30, 2007. 

ADDRESSES: You may send comments by 

any of the following methods: 

• DOT Docket Web Site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Fax: (202) 493–2251. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 

• 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. 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.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–

5227) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–2797; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD 

The FAA is implementing a new 

process for streamlining the issuance of 

ADs related to MCAI. This streamlined 

process will allow us to adopt MCAI 

safety requirements in a more efficient 

manner and will reduce safety risks to 

the public. This process continues to 

follow all FAA AD issuance processes to 

meet legal, economic, Administrative 

Procedure Act, and Federal Register 

requirements. We also continue to meet 

our technical decision-making 

responsibilities to identify and correct 

unsafe conditions on U.S.-certificated 

products. 

This proposed AD references the 

MCAI and related service information 

that we considered in forming the 

engineering basis to correct the unsafe 

condition. The proposed AD contains 

text copied from the MCAI and for this 

reason might not follow our plain 

language principles. 

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–2007–27741; Directorate Identifier 

2006–NM–261–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:// 

dms.dot.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 2006–0315, 

dated October 13, 2006 (referred to after 

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

condition for the specified products. 

The MCAI states that during the A330 

and A340 aircraft fatigue test, cracks 

appeared on the right and left sides 

between the crossing area of the keel 

beam fitting and the front spar on the 

center wing box (CWB). This situation if 

not corrected can lead in the worst case 

to keel beam rupture, which affects the 

structural integrity of the area. In order 

to maintain the structural integrity of 

the aircraft, the MCAI requires a 

repetitive special detailed inspection on 

the horizontal flange of the keel beam in 

the area of the first fastener hole aft of 

FR (frame) 40, follow-up actions (further 

inspections, installation of new 

fasteners, and sealing the fasteners), and 

repair if necessary. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A330–57–3081, including Appendix 01, 

Revision 02, dated January 24, 2006; 

and Service Bulletin A340–57–4089, 

including Appendix 01, Revision 02, 

dated January 24, 2006. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. The compliance 

times for doing the actions described in 

the service bulletins are as follows: 

• Service Bulletin A330–57–3081: 

The mandatory thresholds range from 

the earlier of 19,100 flight cycles or 

57,300 flight hours, to the earlier of 

24,200 flight cycles or 72,800 flight 

hours; the repetitive intervals range 

from the earlier of 9,800 flight cycles or 

29,400 flight hours, to the earlier of 

13,500 flight cycles or 40,500 flight 

hours. 

• Service Bulletin A340–57–4089: 

The mandatory thresholds range from 

the earlier of 19,000 flight cycles or 

95,000 flight hours, to the earlier of 

24,600 flight cycles or 49,200 flight 

hours; the repetitive intervals range 

from the earlier of 9,200 flight cycles or 

46,000 flight hours, to the earlier of 

12,600 flight cycles or 63,000 flight 

hours. 


pwalker on PROD1PC71 with PROPOSALS
15068 Federal Register / Vol. 72, No. 61 / Friday, March 30, 2007 / Proposed Rules 

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, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all 

information provided by the State of 

Design Authority and determined the 

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 

described in a separate paragraph of the 

proposed AD. These requirements, if 

ultimately adopted, will take 

precedence over the actions copied from 

the MCAI. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 9 products 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. Required 

parts would cost about $382 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these costs. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$12,078, or $1,342 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. 

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–2007–27741; 

Directorate Identifier 2006–NM–261–AD. 

Comments Due Date 

(a) We must receive comments by April 30, 

2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the airplanes 

identified in paragraphs (c)(1) and (c)(2) of 

this AD; certificated in any category; except 

as provided by paragraph (c)(3) of this AD. 

(1) Airbus Model A330–201, –202, –203, 

–223, –243, –301, –321, –322, –323, –341, 

–342, and –343 airplanes, all serial numbers, 

except those on which Airbus modification 

49202 has been embodied in production, or 

Airbus Service Bulletin A330–57–3090 has 

been embodied in service. 

(2) Airbus Model A340–200 and –300 

series airplanes, all certified models, all 

serial numbers, except those on which 

Airbus modification 49202 has been 

embodied in production or Airbus Service 

Bulletin A340–57–4098 has been embodied 

in service. 

(3) This AD does not apply to Model 

A340–200 and –300 series airplanes repaired 

in accordance with Airbus Repair Drawing 

R57115053, R57115051, or R57115047 

(installation of titanium doubler). These 

airplanes are covered by European Aviation 

Safety Agency (EASA) AD 2006–0314. (The 

FAA is considering rulemaking regarding 

EASA AD 2006–0314.) 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) states that 

during the A330 and A340 fatigue test, cracks 

appeared on the right and left sides between 

the crossing area of the keel beam fitting and 

the front spar on the center wing box (CWB). 

This situation if not corrected can lead in the 

worst case to keel beam rupture which affects 

the structural integrity of the area. In order 

to maintain the structural integrity of the 

aircraft, the MCAI requires a repetitive 

special detailed inspection on the horizontal 

flange of the keel beam in the area of the first 

fastener hole aft of FR (frame) 40, follow-up 

actions, and repair if necessary. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) Within the mandatory threshold (flight 

cycles or flight hours) mentioned in the 

paragraph 1.E.(2) of Airbus Service Bulletin 

A340–57–4089, Revision 02; or A330–57–

3081, Revision 02; both dated January 24, 

2006, depending on the configuration of the 

aircraft model; or within 3 months after the 

effective date of this AD; whichever occurs 

later: Carry out the NDT (non-destructive 

test) inspection of the hole(s) of the 

horizontal flange of the keel beam located on 

FR (frame) 40 datum on RH (right-hand) and/ 

or LH (left-hand) side of the fuselage, in 

accordance with the instructions of Airbus 

Service Bulletin A340–57–4089, Revision 02; 

or A330–57–3081, Revision 02; as applicable. 

Inspection in accordance with Airbus 

Technical Disposition Ref F57D03012810, 

Issue B, dated August 18, 2003, or 582.0651/ 

2002, Issue A, dated October 17, 2002, 


pwalker on PROD1PC71 with PROPOSALS
Federal Register / Vol. 72, No. 61 / Friday, March 30, 2007 / Proposed Rules 15069 

satisfies the inspection requirements for the 

first rotating probe inspection which is 

specified at the inspection threshold of this 

AD. 

Note 1: In order to prevent large repairs or 

heavy maintenance, Airbus recommends to 

perform the above inspection according to 

recommended thresholds mentioned in 

paragraph 1.E.(2) of Airbus Service Bulletin 

A340–57–4089, Revision 02; or Airbus 

Service Bulletin A330–57–3081, Revision 02; 

both dated January 24, 2006. 

(2) In case of any crack finding, before 

further flight, contact Airbus in order to get 

repair instructions before next flight, and 

repair before further flight. 

(3) Should no crack be detected: 

(i) Before further flight: Follow up the 

actions indicated in the flow charts, figure 7, 

8, or 9, of Airbus Service Bulletin A340–57–

4089, including Appendix 01, Revision 02, 

dated January 24, 2006; or figure 5, 6, or 7, 

of Airbus Service Bulletin A330–57–3081, 

including Appendix 01, Revision 02, dated 

January 24, 2006; in accordance with the 

instructions of the applicable service 

bulletin. 

(ii) Within 30 days after the effective date 

of this AD, or within 30 days after doing the 

inspection required by paragraph (e)(1) of 

this AD, whichever occurs later: Send the 

report of actions carried out in paragraph 

(e)(3)(i) of this AD to Airbus. 

(iii) Renew the inspection at mandatory 

intervals given in paragraph 1.E.(2) of Airbus 

Service Bulletin A340–57–4089, Revision 02, 

dated January 24, 2006; or Airbus Service 

Bulletin A330–57–3081, Revision 02, dated 

January 24, 2006; as applicable; in 

accordance with the instructions of Service 

Bulletin A340–57–4089, Revision 02, or 

Service Bulletin A330–57–3081, Revision 02; 

as applicable, and send the inspection results 

to Airbus. 

Note 2: In order to prevent large repairs or 

heavy maintenance, Airbus recommends to 

perform the above repetitive inspection 

according to recommended intervals 

mentioned in paragraph 1.E.(2) of Airbus 

Service Bulletin A340–57–4089, Revision 02, 

dated January 24, 2006; or Airbus Service 

Bulletin A330–57–3081, Revision 02, dated 

January 24, 2006. 

(4) Upon detection of a crack during a 

repetitive inspection, before further flight, 

contact Airbus to get repair instructions, and 

repair before further flight. 

(5) No additional work is required for 

aircraft inspected in accordance with the 

instructions of Airbus Service Bulletin A330–

57–3081, dated October 30, 2003, or Revision 

01, dated May 18, 2004; or Airbus Service 

Bulletin A340–57–4089, dated October 30, 

2003, or Revision 01, dated March 2, 2004. 

Nevertheless, the operators must check that 

their inspection program is in accordance 

with paragraph 1.E.(2) of Airbus Service 

Bulletin A340–57–4089, Revision 02, dated 

January 24, 2006; or Airbus Service Bulletin 

A330–57–3081, Revision 02, dated January 

24, 2006, for the repetitive inspection. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: 

(1) The MCAI did not have a required 

action if cracks are found during a repetitive 

inspection. This AD requires contacting 

Airbus for repair instructions before further 

flight. 

Other FAA AD Provisions 

(f) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, ANM–116, 

Transport Airplane Directorate, FAA, ATTN: 

Tim Backman, Aerospace Engineer, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. Before 

using any AMOC approved in accordance 

with § 39.19 on any airplane to which the 

AMOC applies, notify the appropriate 

principal inspector in the FAA Flight 

Standards Certificate Holding District Office. 

(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 FAAapproved 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 

(g) Refer to MCAI EASA Airworthiness 

Directive 2006–0315, dated October 13, 2006; 

Airbus Service Bulletin A340–57–4089, 

Revision 02, dated January 24, 2006; and 

Airbus Service Bulletin A330–57–3081, 

Revision 02, dated January 24, 2006; for 

related information. 

Issued in Renton, Washington, on March 

23, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–5909 Filed 3–29–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21701; Directorate 

Identifier 2005–NM–086–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747 and 767 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: The FAA is revising an earlier 

proposed airworthiness directive (AD) 

for certain Boeing Model 747 and 767 

airplanes. The original NPRM would 

have required reworking the electrical 

bonding between the airplane structure 

and the pump housing of the outboard 

boost pumps in the main fuel tank of 

certain Boeing Model 747 airplanes, and 

between the airplane structure and the 

pump housing of the override/jettison 

pumps in the left and right wing center 

auxiliary fuel tanks of certain Boeing 

Model 767 airplanes. The original 

NPRM would also have required related 

investigative actions and corrective 

actions if necessary. The original NPRM 

resulted from fuel system reviews 

conducted by the manufacturer. This 

action revises the original NPRM by 

adding an inspection requirement for 

certain Model 747 airplanes, and by 

specifying cold-working the fastener 

holes for certain other Model 747 

airplanes. We are proposing this 

supplemental NPRM to prevent 

insufficient electrical bonding, which 

could result in a potential of ignition 

sources inside the fuel tanks, and 

which, in combination with flammable 

fuel vapors, could result in fuel tank 

explosions and consequent loss of the 

airplane. 

DATES: We must receive comments on 

this supplemental NPRM by April 24, 

2007. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

supplemental NPRM. 

• 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: 

Philip Sheridan, Aerospace Engineer, 


pwalker on PROD1PC71 with PROPOSALS