This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

2464 

Vol. 72, No. 12 

Friday, January 19, 2007 

NUCLEAR REGULATORY 

COMMISSION 

10 CFR Part 51 

[Docket No. PRM–51–10] 

Massachusetts Attorney General; 

Receipt of Petition for Rulemaking; 

Reopening of Public Comment Period 

AGENCY: Nuclear Regulatory 

Commission. 

ACTION: Petition for rulemaking; 

reopening of public comment period. 

SUMMARY: On November 1, 2006 (71 FR 

64169), the Nuclear Regulatory 

Commission (NRC) published for public 

comment a notice of receipt of a petition 

for rulemaking, dated August 25, 2006, 

which was filed with the Commission 

by Diane Curran on behalf of the 

Massachusetts Attorney General. The 

petition was docketed by the NRC on 

September 19, 2006, and has been 

assigned Docket No. PRM–51–10. On 

December 15, 2006, several external 

stakeholder groups requested a 60 day 

extension of the public comment period 

owing to the importance of the 

rulemaking, the voluminous technical 

documents that require careful review, 

and the occurrence of major national 

events (elections) and holidays 

(Thanksgiving, Christmas, Hanukkah, 

and New Years celebrations) during the 

comment period which limits the time 

available for stakeholders to comment. 

The NRC is reopening the comment 

period on the petition for an additional 

60 days from the original January 16, 

2007 deadline. The comment period 

closes on March 19, 2007. 

DATES: The comment period has been 

reopened and now expires on March 19, 

2007. Comments received after this date 

will be considered if it is practical to do 

so, but the Commission is able to assure 

consideration only for comments 

received on or before this date. 

ADDRESSES: You may submit comments 

on this petition by any one of the 

following methods. Please include 

PRM–51–10 in the subject line of your 

comments. Comments on petitions 

submitted in writing or in electronic 

form will be made available for public 

inspection. Because your comments will 

not be edited to remove any identifying 

or contact information, the NRC 

cautions you against including any 

information in your submission that you 

do not want to be publicly disclosed. 

Mail comments to: Secretary, U.S. 

Nuclear Regulatory Commission, 

Washington, DC 20555–0001, ATTN: 

Rulemakings and Adjudications Staff. 

E-mail comments to: SECY@nrc.gov. If 

you do not receive a reply e-mail 

confirming that we have received your 

comments, contact us directly at 301– 

415–1966. You may also submit 

comments via the NRC’s rulemaking 

Web site at http://ruleforum.llnl.gov. 

Address questions about our rulemaking 

Web site to Carol Gallagher (301) 415– 

5905; e-mail cag@nrc.gov. Comments 

can also be submitted via the Federal 

eRulemaking Portal http:// 

www.regulations.gov. 

Hand deliver comments to: 11555 

Rockville Pike, Rockville, Maryland 

20852, between 7:30 am and 4:15 pm 

Federal workdays. Telephone number 

301–415–1966. 

Fax comments to: Secretary, U.S. 

Nuclear Regulatory Commission at (301) 

415–1101. Publicly available documents 

related to this petition may be viewed 

electronically on the public computers 

located at the NRC’s Public Document 

Room (PDR), Room O1 F21, One White 

Flint North, 11555 Rockville Pike, 

Rockville, Maryland. The PDR 

reproduction contractor will copy 

documents for a fee. Selected 

documents, including comments, may 

be viewed and downloaded 

electronically via the NRC rulemaking 

Web site at http://ruleforum.llnl.gov. 

Publicly available documents created 

or received at the NRC after November 

1, 1999, are available electronically at 

the NRC’s Electronic Reading Room at 

http://www.nrc.gov/reading-rm/ 

adams.html. From this site, the public 

can gain entry into the NRC’s 

Agencywide Document Access and 

Management System (ADAMS), which 

provides text and image files of NRC’s 

public documents. If you do not have 

access to ADAMS or if there are 

problems in accessing the documents 

located in ADAMS, contact the PDR 

Reference staff at 1–800–397–4209, 301– 

415–4737 or by e-mail to pdr@nrc.gov. 

A paper copy of the petition may be 

obtained by contacting Betty Golden, 

Office of Administration, U.S. Nuclear 

Regulatory Commission, Washington, 

DC 20555–0001, telephone 301–415– 

6863, toll-free 1–800–368–5642, or by email bkg2@nrc.gov. 

FOR FURTHER INFORMATION CONTACT: 

Michael T. Lesar, Chief, Rulemaking, 

Directives and Editing Branch, Division 

of Administrative Services, Office of 

Administration, U.S. Nuclear Regulatory 

Commission, Washington, DC 20555– 

0001, telephone 301–415–7163 or toll 

free 1–800–368–5642. 

Dated at Rockville, Maryland, this 12th day 

of January 2007. 

For the U.S. Nuclear Regulatory 

Commission. 

Annette L. Vietti-Cook, 

Secretary of the Commission. 

[FR Doc. E7–712 Filed 1–18–07; 8:45 am] 

BILLING CODE 7590–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–26857; Directorate 

Identifier 2006–NM–126–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to all Airbus 

Model A310 series airplanes. The 

existing AD currently requires 

inspections of the lower door 

surrounding structure to detect cracks 

and corrosion; inspections to detect 

cracking of the holes of the corner 

doublers, the fail-safe ring, and the door 

frames of the door structures; and repair 

if necessary. The existing AD also 

provides for optional terminating action 

for certain inspections. This proposed 

AD would retain all requirements of the 

existing AD, mandate the previously 

optional terminating action, and reduce 

the applicability of the existing AD. 


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Federal Register / Vol. 72, No. 12 / Friday, January 19, 2007 / Proposed Rules 2465 

This proposed AD results from a 

determination that further rulemaking is 

necessary to improve the fatigue 

behavior of the cabin door 

surroundings. We are proposing this AD 

to prevent corrosion between the scuff 

plates at exit and cargo doors and 

fatigue cracks originating from certain 

fastener holes located in adjacent 

structure, which could result in reduced 

structural integrity of the door 

surroundings. 

DATES: We must receive comments on 

this proposed AD by February 20, 2007. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD. 

• DOT Docket Web site: Go to http:// 

dms.dot.gov and follow the instructions 

for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street SW., Nassif Building, 

Room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

proposed AD. 

FOR FURTHER INFORMATION CONTACT: Tom 

Stafford, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–1622; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include the docket 

number ‘‘Docket No. FAA–2007–26857; 

Directorate Identifier 2006-NM–126–

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the proposed AD. We will consider all 

comments received by the closing date 

and may amend the proposed AD in 

light of those comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed AD. 

Using the search function of that Web 

site, anyone can find and read the 

comments in any of our dockets, 

including the name of the individual 

who sent the comment (or signed the 

comment on behalf of an association, 

business, labor union, etc.). You may 

review the DOT’s complete Privacy Act 

Statement in the Federal Register 

published on April 11, 2000 (65 FR 

19477–78), or you may visit http:// 

dms.dot.gov. 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System receives them. 

Discussion 

On July 24, 1998, we issued AD 98–

16–06, amendment 39–10682 (63 FR 

40819, July 31, 1998), for all Airbus 

Model A310 series airplanes. That AD 

requires inspections of the lower door 

surrounding structure to detect cracks 

and corrosion; inspections to detect 

cracking of the holes of the corner 

doublers, the fail-safe ring, and the door 

frames of the door structures; and repair 

if necessary. That AD also provides for 

optional terminating action for certain 

inspections. That AD resulted from 

reports indicating that corrosion was 

found between the scuff plates at exit 

and cargo doors, and fatigue cracks 

originated from certain fastener holes 

located in adjacent structure. We issued 

that AD to detect and correct such 

corrosion and fatigue cracking, which 

could result in reduced structural 

integrity of the door surroundings. 

Other Relevant Rulemaking 

We have previously issued AD 97–

11–03, amendment 39–10032 (62 FR 

28325, May 23, 1997), applicable to all 

Airbus Model A300 series airplanes. 

That AD requires inspections of the 

lower door surrounding structure to 

detect cracks and corrosion; inspections 

to detect cracking of the holes of the 

corner doublers, the fail-safe ring, and 

the door frames of the door structures; 

and repair if necessary. That AD also 

requires modification of the passenger/ 

crew door frames, which terminates 

certain inspections. 

We also previously issued AD 98–16–

05, amendment 39–10680 (63 FR 40812, 

July 31, 1998), applicable to all Airbus 

Model A300–600 series airplanes. That 

AD requires inspections of the areas 

behind the scuff plates below the 

passenger/crew doors and bulk cargo 

door to detect cracks and corrosion; 

inspections to detect cracking of the 

holes of the corner doublers, the failsafe ring, and the door frames of the 

door structures; and repair if necessary. 

In addition, that AD provides for an 

optional terminating action for certain 

inspections. We are considering further 

rulemaking to mandate the optional 

terminating action. 

Actions Since Existing AD Was Issued 

Since we issued AD 98–16–06, the 

Direction Ge ́ne ́rale de l’Aviation Civile 

(DGAC), which is the airworthiness 

authority for France, issued French 

airworthiness directives 1991–132–

124(B) R1, dated November 29, 2000 (to 

replace French airworthiness directive 

91–132–124(B), dated June 26, 1992, 

which is referred to in AD 98–16–06), 

and F–2004–103, dated July 7, 2004. 

The DGAC advises that further 

rulemaking is necessary to improve the 

fatigue behavior of the cabin door 

surroundings on certain Airbus Model 

A310 series airplanes and to remove 

certain airplanes from the applicability 

of the existing French airworthiness 

directive 91–132–124(B) that are no 

longer subject to the existing 

requirements. Corrosion between the 

scuff plates at exit and cargo doors and 

fatigue cracks originating from certain 

fastener holes located in adjacent 

structure, if not corrected, could result 

in reduced structural integrity of the 

door surroundings. 

After the DGAC issued French 

airworthiness directive 1991–132–

124(B) R1 on November 29, 2000, we 

determined at that time that further 

rulemaking was not necessary, because 

the changes to AD 98–16–06 would be 

relieving in nature. However, since 

French airworthiness directive F–2004–

103 mandates the previously optional 

modification, we now agree with the 

DGAC that further rulemaking is indeed 

necessary to improve the fatigue 

behavior of the cabin door 

surroundings, and this proposed AD 

follows from that determination. 

Relevant Service Information 

Airbus has issued and revised the 

service bulletins in the following table: 


jlentini on PROD1PC65 with PROPOSAL
2466 Federal Register / Vol. 72, No. 12 / Friday, January 19, 2007 / Proposed Rules 

SERVICE BULLETINS

Airbus Service Bulletin— Describes procedures for— 

A310–53–2030, Revision 06, dated 

July 2, 1996 (Revision 5 of the 

service bulletin was referenced in 

AD 98–16–06 as an appropriate 

source of service information).

Doing initial inspections for cracks and corrosion of the areas behind the scuff plates below the passenger/ 

crew doors and bulk cargo door, and repairing any cracked or corroded part. The inspection and repair 

are essentially identical to those specified in Revisions 2 through 5 of the service bulletin. 

A310–53–2037, Revision 02, dated 

November 27, 2000 (Revision 1 

of the service bulletin was referenced in AD 98–16–06 as an 

appropriate source of service information).

Doing repetitive inspections for cracks of the holes of the corner doublers, the fail-safe ring, and the door 

frames of the passenger/crew door structures, and repairing any cracked part. The inspection and repair 

are essentially identical to those specified in Revision 1 of the service bulletin. 

A310–53–2017, Revision 09, dated 

May 17, 2004 (Revision 7 of the 

service bulletin was referenced in 

AD 98–16–06 as an appropriate 

source of service information).

Modifying the passenger/crew door structures, which ends the repetitive inspections of the holes of the 

corner doublers specified in Airbus Service Bulletin A310–53–2037, the fail-safe ring, and the door 

frames for certain airplanes. The modification includes cold expansion of fastener holes; a ROTO test; 

installation of new oversize fasteners and modified brackets; and installation of an additional steel doubler. The modification is essentially identical to that specified in Revisions 7 and 08 of the service bulletin. 

In addition, Airbus previously issued 

Service Bulletin A310–53–2041, 

Revision 02, dated July 2, 1996 (which 

was referenced in AD 98–16–06 as an 

appropriate source of service 

information). The service bulletin 

describes procedures for doing 

repetitive inspections for cracks and 

corrosion of the areas behind the scuff 

plates below the passenger/crew doors 

and bulk cargo door, and repairing any 

cracked or corroded part. 

Accomplishing the actions specified 

in the service information is intended to 

adequately address the unsafe 

condition. The DGAC mandated the 

service information to ensure the 

continued airworthiness of these 

airplanes in France. 

FAA’s Determination and Requirements 

of the Proposed AD 

This airplane model is manufactured 

in France and is type certificated for 

operation in the United States under the 

provisions of section 21.29 of the 

Federal Aviation Regulations (14 CFR 

21.29) and the applicable bilateral 

airworthiness agreement. Pursuant to 

this bilateral airworthiness agreement, 

the DGAC has kept the FAA informed 

of the situation described above. We 

have examined the DGAC’s findings, 

evaluated all pertinent information, and 

determined that AD action is necessary 

for airplanes of this type design that are 

certificated for operation in the United 

States. 

This proposed AD would supersede 

AD 98–16–06 and would retain the 

requirements of the existing AD. This 

proposed AD would also require 

accomplishing the actions specified in 

service information described 

previously. 

Difference Between French 

Airworthiness Directives and This 

Proposed AD 

The applicability of French 

airworthiness directives 1991–132–

124(B) R1 and F–2004–103 exclude 

airplanes on which Airbus Service 

Bulletin A310–53–2017 at Revision 1 (or 

any other later approved revision) has 

been done in service. However, we have 

not excluded those airplanes in the 

applicability of this proposed AD; 

rather, this proposed AD includes a 

requirement to accomplish the actions 

specified in Revision 09 of that service 

bulletin. This requirement would ensure 

that the actions specified in the service 

bulletin and required by this proposed 

AD are accomplished on all affected 

airplanes. Operators must continue to 

operate the airplane in the configuration 

required by this proposed AD unless an 

alternative method of compliance is 

approved. 

Change to Existing AD 

This proposed AD would retain all 

requirements of AD 98–16–06. Since AD 

98–16–06 was issued, the AD format has 

been revised, and certain paragraphs 

and a note have been rearranged. As a 

result, the corresponding paragraph 

identifiers have changed in this 

proposed AD, as listed in the following 

table: 

REVISED PARAGRAPH IDENTIFIERS

Paragraphs and note 

in AD 98–16–06 

Corresponding paragraphs in this proposed AD 

Paragraph (a) ............ Paragraph (f). 

Paragraph (b) ............ Paragraph (g). 

Paragraph (c) ............ Paragraph (h). 

Paragraph (d) ............ Paragraph (i). 

NOTE 2 ..................... Paragraph (j). 

Paragraph (e) ............ Paragraph (k). 

Paragraph (f) ............. Paragraph (l). 

Paragraph (g) ............ Paragraph (m). 

Paragraph (h) ............ Paragraph (o). 

The DGAC revised the applicability of 

French airworthiness directives 1991–

132–124(B) R1 and F–2004–103 to 

exclude Model A310 series airplanes on 

which Airbus Modification 5068, 7201, 

and 7298 have been incorporated in 

production. Therefore, the applicability 

of the proposed AD parallels the French 

airworthiness directives in that regard. 

We have revised the affected airplanes 

in paragraphs (f)(1) through (f)(3) of this 

proposed AD (paragraphs (a)(1) through 

(a)(3) of AD 98–16–06) to include ‘‘and 

Modification 5382D4741 for all other 

doors.’’ This information is specified in 

the referenced service bulletin, but was 

inadvertently omitted from those 

paragraphs in AD 98–16–06. This 

change reduces the number of affected 

airplanes. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD. The 

average labor rate per work hour is $80. 


jlentini on PROD1PC65 with PROPOSAL
Federal Register / Vol. 72, No. 12 / Friday, January 19, 2007 / Proposed Rules 2467 

ESTIMATED COSTS

Action Work hours Parts Cost per airplane 

Number of U.S.- 

registered airplanes Fleet cost 

Repetitive inspections behind scuff 

plates (required by AD 98–16–06).

26 .......................... None ..................... $2,080 ................... 46 $95,680. 

Repetitive inspections of corner doublers, fail-safe ring, and door frames 

(required by AD 98–16–06).

Between 4 and 

100 depending 

on kit purchased.

None ..................... Between $320 and 

$8,000.

46 Between $14,720, 

and $368,000 

per inspection 

cycle. 

Terminating modification for repetitive 

inspection of corner doublers, failsafe ring, and door frames.

Between 8 and 55 

depending on kit 

purchased.

Between $506 and 

$6,098 depending on kit purchased.

Between $1,146 

and $10,498.

46 Between $52,716 

and $482,908. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would not 

have a substantial direct effect on the 

States, on the relationship between the 

national Government and the States, or 

on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. See the ADDRESSES section 

for a location to examine the regulatory 

evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–10682 (63 

FR 40819, July 31, 1998) and adding the 

following new airworthiness directive 

(AD): 

Airbus: Docket No. FAA–2007–26857; 

Directorate Identifier 2006–NM–126–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by February 20, 2007. 

Affected ADs 

(b) This AD supersedes AD 98–16–06. 

Applicability 

(c) This AD applies to Airbus Model A310 

series airplanes; certificated in any category; 

excluding those airplanes on which Airbus 

Modification 5068, 7201, and 7298 have been 

incorporated in production. 

Unsafe Condition 

(d) This AD results from a determination 

that further rulemaking is necessary to 

improve the fatigue behavior of the cabin 

door surroundings. We are issuing this AD to 

prevent corrosion between the scuff plates at 

exit and cargo doors and fatigue cracks 

originating from certain fastener holes 

located in adjacent structure, which could 

result in reduced structural integrity of the 

door surroundings. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Requirements of AD 98–16–06 

Initial Inspection Behind Scuff Plates and 

Repair If Necessary With Revised Affected 

Doors 

(f) Perform an initial inspection of the areas 

behind the scuff plates below the passenger/ 

crew doors and bulk cargo door to detect 

cracks and corrosion, in accordance with 

Airbus Service Bulletin A310–53–2030, 

Revision 5, dated March 6, 1991, at the 

applicable time specified in paragraph (f)(1), 

(f)(2), or (f)(3) of this AD. If any crack or 

corrosion is found during this inspection, 

prior to further flight, repair in accordance 

with the service bulletin. Accomplishment of 

this inspection is not required for the aft 

passenger/crew doors if a steel doubler that 

covers the entire inspection area is installed. 

(1) For any door on which Modification 

5382 and Modification 5382D4741 for all 

other doors have been accomplished: Perform 

the initial inspection within 9 years since 

airplane manufacture, or within 1 year after 

September 4, 1998 (the effective date of AD 

98–16–06), whichever occurs later. 

(2) For any door on which Modification 

5382 and Modification 5382D4741 for all 

other doors have not been accomplished, and 

on which the procedures described in Airbus 

Service Bulletin A310–53–2004, Revision 2, 

dated June 17, 1985, or Airbus Service 

Information Letter 53–033, Revision 2, dated 

November 23, 1984, have been accomplished: 

Perform the initial inspection within 5 years 

since airplane manufacture, or within 1 year 

after September 4, 1998, whichever occurs 

later. 

(3) For any door on which Modification 

5382 and Modification 5382D4741 for all 

other doors have not been accomplished, and 

on which the procedures described in Airbus 

Service Bulletin A310–53–2004, Revision 2, 

dated June 17, 1985, or Airbus Service 

Information Letter 53–033, Revision 2, dated 

November 23, 1984, have not been 

accomplished: Perform the initial inspection 

within 4 years since airplane manufacture, or 

within 1 year after September 4, 1998, 

whichever occurs later. 


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Repetitive Inspections Behind Scuff Plates 

(g) Perform repetitive inspections of the 

areas behind the scuff plates below the 

passenger/crew doors and bulk cargo door to 

detect cracks and corrosion, in accordance 

with Airbus Service Bulletin A310–53–2041, 

Revision 02, dated July 2, 1996, at the 

applicable times specified in paragraphs 

(g)(1), (g)(2), and (g)(3) of this AD. 

Accomplishment of these inspections is not 

required for the aft passenger/crew doors if 

a steel doubler that covers the entire 

inspection area is installed. 

(1) For the forward passenger/crew doors, 

the bulk cargo door, and the aft passenger/ 

crew doors, except the upper and lower 

edges of the fail-safe ring and the upper edges 

of the corner doubler, on all Model A310–200 

and –300 series airplanes: Perform the first 

inspection within 5 years after accomplishing 

the inspection required by paragraph (f) of 

this AD; and repeat the inspection thereafter 

at intervals not to exceed 5 years. 

(2) For the upper and lower edges of the 

fail-safe ring and the upper edges of the 

corner doubler of the aft passenger/crew door 

on all Model A310–200 series airplanes: 

Perform the first inspection within 5 years or 

12,000 landings after accomplishing the 

inspection required by paragraph (f) of this 

AD, whichever occurs first; and repeat the 

inspection thereafter at intervals not to 

exceed 5 years or 12,000 landings, whichever 

occurs first. 

(3) For the upper and lower edges of the 

fail-safe ring and the upper edges of the 

corner doubler of the aft passenger/crew door 

on all Model A310–300 series airplanes: 

Perform the first inspection within 5 years or 

7,000 landings after accomplishing the 

inspection required by paragraph (f) of this 

AD, whichever occurs first; and repeat the 

inspection thereafter at intervals not to 

exceed 5 years or 7,000 landings, whichever 

occurs first. 

Repair of Scuff Plates If Necessary 

(h) If any crack is found during any 

inspection required by paragraph (g) or (n) of 

this AD, prior to further flight, repair in 

accordance with Airbus Service Bulletin 

A310–53–2041, Revision 02, dated July 2, 

1996. Thereafter, perform the repetitive 

inspections required by paragraph (g) of this 

AD at the applicable times specified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD. 

(i) If any corrosion is found during any 

inspection required by paragraph (g) of this 

AD, prior to further flight, repair in 

accordance with Airbus Service Bulletin 

A310–53–2041, Revision 02, dated July 2, 

1996. Thereafter, perform the repetitive 

inspections required by paragraph (g) of this 

AD at the applicable time specified in 

paragraph (i)(1) or (i)(2) of this AD. 

(1) For Model A310–200 series airplanes: 

Inspect at intervals not to exceed 5 years or 

9,600 landings, whichever occurs first. 

(2) For Model A310–300 series airplanes: 

Inspect at intervals not to exceed 5 years or 

5,600 landings, whichever occurs first. 

(j) Accomplishment of the actions required 

by paragraph (g), (h), or (i) of this AD in 

accordance with Airbus Service Bulletin 

A310–53–2041, dated December 5, 1990; or 

Revision 1, dated March 6, 1991, prior to 

September 4, 1998, is acceptable for 

compliance with that paragraph. 

Initial Inspection of Corner Doublers, FailSafe Ring, and Door Frames 

(k) Perform an inspection to detect 

cracking of the holes of the corner doublers, 

the fail-safe ring, and the door frames of the 

left- and right-hand forward, mid, and aft 

passenger/crew door structures, in 

accordance with Airbus Service Bulletin 

A310–53–2037, Revision 1, dated April 29, 

1992, and at the applicable times specified in 

paragraphs (k)(1), (k)(2), and (k)(3) of this AD. 

(1) For the upper corners of the forward 

doors: Inspect prior to the accumulation of 

20,000 total landings, or within 2,000 

landings after September 4, 1998, whichever 

occurs later. 

(2) For the lower corners of the forward 

doors: Inspect prior to the accumulation of 

20,000 total landings, or within 4,000 

landings after September 4, 1998, whichever 

occurs later. 

(3) For the upper and lower corners of the 

aft doors, and for the parts underneath the 

corners of the upper door frames: Inspect 

prior to the accumulation of 20,000 total 

landings, or within 4,000 landings after 

September 4, 1998, whichever occurs later. 

Repetitive Inspections of Corner Doublers, 

Fail-Safe Ring, and Door Frames 

(l) Repeat the inspections required by 

paragraph (k) of this AD at the applicable 

times specified in paragraphs (l)(1), (l)(2), 

(l)(3), (l)(4), and (l)(5). 

(1) For the upper corners of the forward 

doors: Inspect at intervals not to exceed 6,000 

landings. 

(2) For the lower corners of the forward 

doors: Inspect at intervals not to exceed 

10,000 landings. 

(3) For the upper and lower corners of the 

aft doors on which an inspection required by 

paragraph (k) of this AD was accomplished 

using a ROTO test technique: Inspect at 

intervals not to exceed 8,000 landings. 

(4) For the upper and lower corners of the 

aft doors on which an inspection required by 

paragraph (k) of this AD was accomplished 

using an X-ray technique: Inspect at intervals 

not to exceed 3,500 landings. 

(5) For the areas around the fasteners in the 

vicinity of stringer 12 on the upper door 

frames of the aft doors on which an 

inspection required by paragraph (k) of this 

AD was accomplished using a visual 

technique: Inspect at intervals not to exceed 

6,900 landings. 

Repair of Corner Doublers, Fail-Safe Ring, 

and/or Door Frames If Necessary 

(m) If any crack is found during any 

inspection required by paragraph (k) or (l) of 

this AD: Prior to further flight, accomplish 

the requirement of paragraph (m)(1) or (m)(2) 

of this AD, as applicable. 

(1) If any crack is found, and the crack can 

be eliminated using the method specified in 

Airbus Service Bulletin A310–53–2037, 

Revision 1, dated April 29, 1992; or Revision 

02, dated November 27, 2000: Prior to further 

flight, repair the crack in accordance with 

that service bulletin. 

(2) If any crack is found, and the crack 

cannot be eliminated using the method 

specified in Airbus Service Bulletin A310–

53–2037, Revision 1, dated April 29, 1992; or 

Revision 02, dated November 27, 2000: Prior 

to further flight, repair the crack in 

accordance with a method approved by the 

Manager, International Branch, ANM–116, 

FAA, Transport Airplane Directorate. 

New Requirements of This AD 

New Revision of Service Bulletins 

(n) As of the effective date of this AD, use 

only the service bulletin specified in Table 1 

of this AD. 

TABLE 1.—NEW REVISION OF SERVICE BULLETINS

Do the action(s) required by— In accordance with the accomplishment instructions of Airbus Service Bulletin—

(1) Paragraph (f) of this AD ............ A310–53–2030, Revision 06, dated July 2, 1996. 

(2) Paragraph (k) and (m)(1) of this 

AD.

A310–53–2037, Revision 02, dated November 27, 2000. 

Terminating Modification for Repetitive 

Inspection of Corner Doublers, Fail-Safe 

Ring, and Door Frames 

(o) Modify the passenger/crew door 

structures in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–53–2017, Revision 09, 

dated May 17, 2004. Do the modification at 

the applicable time in paragraph (o)(1) or 

(o)(2) of Table 2 of this AD. Accomplishment 

of this modification constitutes terminating 

action for the repetitive inspections required 

by paragraph (l) of this AD. The inspections 

required by paragraph (f) of this AD must be 

done before accomplishing this modification. 


jlentini on PROD1PC65 with PROPOSAL
Federal Register / Vol. 72, No. 12 / Friday, January 19, 2007 / Proposed Rules 2469 

TABLE 2.—COMPLIANCE TIME FOR TERMINATING MODIFICATION

For model Compliance time 

(1) A310–203, –204, 

–221, and –222 airplanes.

Before the accumulation of 40,000 flight cycles since the date of issuance of the original French standard Airworthiness 

Certificate or the date of issuance of the original French Export Certificate of Airworthiness, or during the next inspection required by paragraph (l) of this AD, whichever occurs later. 

(2) A310–304, –322, 

–324, and –325 airplanes.

Before the accumulation of 35,000 flight cycles since the date of issuance of the original French standard Airworthiness 

Certificate or the date of issuance of the original French Export Certificate of Airworthiness, or during the next inspection required by paragraph (l) of this AD, whichever occurs later 

Earlier Revision of Service Bulletins 

(p) Actions done before the effective date 

of this AD in accordance with the service 

bulletins identified in Table 3 of this AD, are 

acceptable for compliance with the 

corresponding requirements of this AD. 

TABLE 3.—EARLIER REVISION OF SERVICE BULLETINS

Airbus service bulletin Revision 

level Date 

(1) A310–53–2017 ........................................................................................................................................... 7 February 25, 1992. 

(2) A310–53–2017 ........................................................................................................................................... 08 September 7, 2000. 

Alternative Methods of Compliance 

(AMOCs) 

(q)(1) The Manager, International Branch, 

ANM–116, has the authority to approve 

AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

(2) Alternative methods of compliance, 

approved previously in accordance with AD 

98–16–06 are approved as alternative 

methods of compliance with the 

corresponding provisions of paragraphs (f) 

through (m) of this AD. 

(3) 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. 

Related Information 

(r) French airworthiness directives 1991–

132–124(B) R1, dated November 29, 2000, 

and F–2004–103, dated July 7, 2004, also 

address the subject of this AD. 

Issued in Renton, Washington, on January 

8, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–702 Filed 1–18–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–26856; Directorate 

Identifier 2006–NM–125–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

Series Airplanes, and Model C4–605R 

Variant F Airplanes (Collectively Called 

A300–600 Series Airplanes) 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to all Airbus 

Model A300–600 series airplanes. The 

existing AD currently requires 

inspections of the lower door 

surrounding structure to detect cracks 

and corrosion; inspections to detect 

cracking of the holes of the corner 

doublers, the fail-safe ring, and the door 

frames of the door structures; and repair 

if necessary. The existing AD also 

provides for optional terminating action 

for certain inspections. This proposed 

AD would retain all requirements of the 

existing AD, mandate the previously 

optional terminating action, reduce the 

applicability of the existing AD, and add 

repetitive inspections behind scuff 

plates for certain affected airplanes. 

This proposed AD results from a 

determination that further rulemaking is 

necessary to improve the fatigue 

behavior of the cabin door 

surroundings. We are proposing this AD 

to prevent corrosion between the scuff 

plates at exit and cargo doors and 

fatigue cracks originating from certain 

fastener holes located in adjacent 

structure, which could result in reduced 

structural integrity of the door 

surroundings. 

DATES: We must receive comments on 

this proposed AD by February 20, 2007. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD. 

• DOT Docket Web site: Go to 

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

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street SW., Nassif Building, 

Room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

proposed AD. 

FOR FURTHER INFORMATION CONTACT: Tom 

Stafford, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–1622; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 


jlentini on PROD1PC65 with PROPOSAL