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: 


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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–2007–26856; 

Directorate Identifier 2006–NM–125–

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–

16–05, amendment 39–10680 (63 FR 

40812, July 31, 1998), for all 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). 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 behind the scruff 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–

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. We are considering further 

rulemaking to mandate the optional 

terminating action. 

Actions Since Existing AD Was Issued 

Since we issued AD 98–16–05, 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, 1991, 

which is referred to in AD 98–16–05), 

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 

A300–600 series airplanes and to 

remove certain airplanes from the 

applicability of the existing AD 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 98–16–05 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: 

SERVICE BULLETINS

Airbus Service Bulletin— Describes procedures for—

A300–53–6011, Revision 07, dated January 24, 

2005 (Revision 3, dated February 4, 1991, of 

the service bulletin was referenced in AD 98–

16–05 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 

or contacting Airbus. The inspection and repair are essentially identical to those specified in 

Revision 3 of the service bulletin. Revision 07 also revises the effectivity by adding additional airplanes. 

A300–53–6022, Revision 04, dated January 24, 

2005 (the original issue, dated February 4, 

1991, of the service bulletin was referenced 

in AD 98–16–05 as an appropriate source of 

service information).

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/corroded 

part or contacting Airbus. The inspection and repair are essentially identical to those specified in original issue of the service bulletin. Revision 04 also revises the effectivity by adding 

additional airplanes. 


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SERVICE BULLETINS—Continued 

Airbus Service Bulletin— Describes procedures for—

A300–53–6018, Revision 03, dated July 26, 

2006, including Appendix 01 (Revision 1, 

dated April 29, 1992, of the service bulletin 

was referenced in AD 98–16–05 as an appropriate source of service information).

Doing repetitive inspections for cracks/corrosion of the holes of the corner doublers, the failsafe ring, and the door frames of the passenger/crew door structures, and repairing any 

cracked/corroded part or contacting Airbus. The inspection and repair are essentially identical to those specified in Revision 1 of the service bulletin. 

A300–53–6002, Revision 06, dated May 17, 

2004 (Revision 3, dated February 22, 1992, 

of the service bulletin was referenced in AD 

98–16–05 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 A300–53–6018, the fail-safe 

ring, and the door frames for certain airplanes. The modification includes cold expansion of 

fastener holes; a ROTO test; repair of any crack; repair of any crack that cannot be eliminated per Airbus; installation of new oversize fasteners and modified brackets; and installation of an additional steel doubler. The modification is essentially identical to that specified in 

Revision 3 of the service bulletin. 

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 

These airplane models are 

manufactured in France and are 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 98–16–05, retain the 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 would also require 

accomplishing the actions specified in 

service information described 

previously. 

Difference Between French 

Airworthiness Directive and This 

Proposed AD 

The applicability of French 

airworthiness directive 1991–132–

124(B) R1 excludes Airbus Model 

A300–600 series airplanes on which 

Airbus Service Bulletin A300–53–6002, 

Revision 2, dated May 6, 1991 (or any 

other later approved revision), has been 

accomplished 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 06 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. 

The service bulletins specify to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions using 

a method that we or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent) approve. In light of the 

type of repair that would be required to 

address the unsafe condition, and 

consistent with existing bilateral 

airworthiness agreements, we have 

determined that, for this proposed AD, 

a repair we or the EASA approve would 

be acceptable for compliance with this 

proposed AD. 

Change to Existing AD 

This proposed AD would retain all 

requirements of AD 98–16–05. Since AD 

98–16–05 was issued, the AD format has 

been revised, and certain paragraphs 

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

Requirement in 

AD 98–16–05 

Corresponding requirements in this 

proposed AD 

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

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

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

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

Paragraph (e) ............ paragraph (j). 

Paragraph (f) ............. Paragraph (k). 

Paragraph (g) ............ Paragraph (l). 

The DGAC revised the applicability of 

French airworthiness directives 1991–

132–124(B) R1 and F–2004–103 to 

exclude Model A300–600 series 

airplanes on which Airbus Modification 

5068, 6514, 7201, and 7298 have been 

incorporated in production. Therefore, 

the applicability of the proposed AD 

parallels the French airworthiness 

directives in that regard. 

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. 

ESTIMATED COSTS

Action Work hours Parts Cost per airplane 

Number of U.S.- 

registered airplanes Fleet cost 

Repetitive inspections behind scuff 

plates.

37 .......................... None ..................... $2,960 ................... 129 $381,840. 

Repetitive inspections of corner doublers, fail-safe ring, and door frames.Between 1 and 51 None ..................... Between $80 and 

$4,080.

129 Between $10,320 

and $526,320. 


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ESTIMATED COSTS—Continued 

Action Work hours Parts Cost per airplane 

Number of U.S.- 

registered airplanes Fleet cost 

Terminating modification for repetitive 

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

Between 8 and 67, 

depending on kit 

purchased.

Between $580 and 

$11,273, depending on kit 

purchased.

Between $1,220 

and $16,633.

129 Between $157,380 

and $2,145,657. 

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 39–10680 (63 

FR 40812, July 31, 1998) and adding the 

following new airworthiness directive 

(AD): 

Airbus: Docket No. FAA–2007–26856; 

Directorate Identifier 2006–NM–125–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 98–16–05. 

Applicability 

(c) This AD applies to Airbus Model A300 

B4–601, B4–603, B4–620, and B4–622 

airplanes; Model A300 B4–605R and B4–

622R airplanes; Model A300 F4–605R and 

F4–622R airplanes; and Model A300 C4–

605R Variant F airplanes; certificated in any 

category; excluding those airplanes on which 

Airbus Modification 5068, 6514, 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 98–16–05 

Initial Inspection Behind Scuff Plates and 

Repair if Necessary 

(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 A300–53–6011, 

Revision 3, dated February 4, 1991, at the 

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 mid and aft passenger/ 

crew doors if a steel doubler that covers the 

entire inspection area is installed. 

(1) For airplanes on which Modification 

5382S6526 (for forward doors) and 

Modification 5382D4741 (for all other doors) 

have been accomplished prior to delivery of 

the airplane: Perform the initial inspection 

within 9 years since date of manufacture, or 

within 1 year after September 4, 1998 (the 

effective date of AD 98–16–05), whichever 

occurs later. 

(2) For airplanes on which Modification 

5382S6526 (for forward doors) and 

Modification 5382D4741 (for all other doors) 

have not been accomplished; and on which 

the procedures described in Airbus Service 

Information Letter (SIL) A300–53–033, 

Revision 2 (for all doors), dated November 

23, 1984, have been accomplished: Perform 

the initial inspection within 5 years after 

accomplishment of the procedures described 

in the SIL, or within 1 year after September 

4, 1998, whichever occurs later. 

(3) For airplanes on which Modification 

5382S6526 (for forward doors), and 

Modification 5382D4741 (for all other doors), 

and the procedures described in Airbus SIL 

A300–53–033, Revision 2, dated November 

23, 1984, have not been accomplished: 

Perform the initial inspection within 4 years 

since date of manufacture, or within 1 year 

after September 4, 1998, whichever occurs 

later. 

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 A300–53–6022, 

dated February 4, 1991, at the applicable 

times specified in paragraphs (g)(1) and (g)(2) 

of this AD. Accomplishment of these 

inspections is not required for the mid and 

aft passenger/crew doors if a steel doubler 

that covers the entire inspection area is 

installed. 


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(1) For the forward and mid 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: 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 

doors: Perform the first inspection within 5 

years or 6,000 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 6,000 landings, whichever 

occurs first. 

Repair of Scuff Plates if Necessary 

(h) If any crack is found during any 

inspection required by paragraph (g) of this 

AD, prior to further flight, repair in 

accordance with Airbus Service Bulletin 

A300–53–6022, dated February 4, 1991. 

Thereafter, perform the repetitive inspections 

required by paragraph (g) of this AD at the 

applicable times specified in paragraphs 

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

(i) If corrosion is found during any 

inspection required by paragraph (g) of this 

AD, prior to further flight, repair in 

accordance with Airbus Service Bulletin 

A300–53–6022, dated February 4, 1991. 

Thereafter, perform the repetitive inspections 

required by paragraph (g) of this AD at the 

applicable times specified in paragraph (i)(1) 

or (i)(2) of this AD. 

(1) For the upper and lower edges of the 

fail-safe ring and the upper edges of the 

corner doubler of the aft passenger/crew 

doors, and for the mid passenger/crew door: 

Inspect at intervals not to exceed 5 years or 

5,000 landings, whichever occurs first. 

(2) For the forward passenger/crew doors 

and bulk cargo doors: Inspect at intervals not 

to exceed 5 years. 

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

(j) Perform an inspection to detect cracking 

of the holes of the corner doublers, the failsafe 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 A300–53–6018, 

Revision 1, dated April 29, 1992, and at the 

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

(j)(2), (j)(3), or (j)(4) 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 

mid doors: Inspect prior to the accumulation 

of 20,000 total landings, or within 2,000 

landings after September 4, 1998, whichever 

occurs later. 

(4) 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 

(k) Repeat the inspections required by 

paragraph (j) of this AD at the applicable 

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

(k)(3), (k)(4), and (k)(5) of this AD. 

(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 

mid and aft doors on which an inspection 

required by paragraph (j) 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 

mid and aft doors on which an inspection 

required by paragraph (j) 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 (j) 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 

(l) If any crack is found during any 

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

this AD: Prior to further flight, accomplish 

the requirement of paragraph (l)(1) or (l)(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 A300–53–6018, 

Revision 1, dated April 29, 1992; or Revision 

02, excluding Appendix 01, 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 A300–

53–6018, 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 

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

only the applicable service bulletins 

specified in Table 1 of this AD; except where 

the service bulletins recommend contacting 

Airbus for appropriate action, before further 

flight, repair the cracked part using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the European Aviation 

Safety Agency (EASA) (or its delegated 

agent). 

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 ...................................................................... A300–53–6011, Revision 07, dated January 24, 2005. 

(2) Paragraphs (g) through (i) of this AD ................................................. A300–53–6022, Revision 04, dated January 24, 2005. 

(3) Paragraphs (j), (k), and (l)(1) of this AD ............................................. A300–53–6018, Revision 03, excluding Appendix 01, dated July 26, 

2006. 

Initial Inspection Behind Scuff Plates and 

Repair If Necessary for Additional Airplanes 

(n) 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 the Accomplishment Instructions of 

Airbus Service Bulletin A300–53–6011, 

Revision 07, dated January 24, 2005; at the 

applicable time specified in Table 2 of this 

AD. If any crack or corrosion is found during 

this inspection, before further flight, repair in 

accordance with the service bulletin. 

Accomplishment of this inspection is not 

required for the mid and aft passenger/crew 

doors if a steel doubler that covers the entire 

inspection area is installed. 


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TABLE 2.—COMPLIANCE TIME INITIAL INSPECTION BEHIND SCUFF PLATE FOR ADDITIONAL AIRPLANES

For airplanes on which— And on which—

Compliance time 

(whichever occurs later) 

Threshold Grace period 

(1) Modification 5382S6526 (for forward 

doors) and Modification 5382D4485 (for 

all other doors) have been done before 

the date of issuance of the original 

French standard airworthiness certificate 

or the date of issuance of the original 

French export certificate of airworthiness.

None ........................................ Within 108 months after first 

flight.

Within 12 months after the effective date of this AD. 

(2) Modification 5382S6180 (for forward 

doors) and Modification 5382D4741 or 

5382D4485 (for all other doors) have 

been done before the date of issuance of 

the original French standard airworthiness 

certificate or the date of issuance of the 

original French export certificate of airworthiness.

None ........................................ Within 108 months after first 

flight.

Within 12 months after the effective date of this AD. 

(3) Modification 5382S6526 (for forward 

doors) and Modification 5382D4485 (for 

all other doors) have not been done before the effective date of this AD.

The actions specified in Airbus 

Service Information Letter 

(SIL) A300–53–033, Revision 2 (for all doors), dated 

November 23, 1984, have 

been done.

Within 60 months after accomplishing the actions specified 

in the SIL.

Within 12 months after the effective date of this AD. 

(4) Modification 5382S6180 (for forward 

doors) and Modification 5382D4741 or 

5382D4485 (for all other doors) have not 

been done before the effective dated of 

this AD.

The actions specified in Airbus 

SIL A300–53–033, Revision 

2 (for all doors), dated November 23, 1984, have been 

done.

Within 60 months after accomplishing the actions specified 

in the SIL.

Within 12 months after the effective date of this AD. 

(5) Modification 5382S6526 (for forward 

doors) and Modification 5382D4485 (for 

all other doors) have not been done before the effective date of this AD.

The actions specified in Airbus 

SIL A300–53–033, Revision 

2, dated November 23, 

1984, have not been done.

Within 48 months 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.

Within 12 months after the effective date of this AD. 

(6) Modification 5382S6180 (for forward 

doors) and Modification 5382D4741 or 

5382D4485 (for all other doors) have not 

been done before the effective date of 

this AD.

The actions specified in Airbus 

SIL A300–53–033, Revision 

2, dated November 23, 

1984, have not been done.

Within 48 months 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.

Within 12 months after the effective date of this AD. 

Repetitive Inspections behind Scuff Plates for 

Additional Airplanes 

(o) For airplanes identified in Table 2 of 

this AD: 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 A300–53–6022, 

Revision 04, dated January 24, 2005, at the 

applicable times specified in paragraphs 

(o)(1) and (o)(2) of this AD. Accomplishment 

of these inspections is not required for the 

mid and aft passenger/crew doors if a steel 

doubler that covers the entire inspection area 

is installed. 

(1) For the forward and mid 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: Perform 

the first inspection within 60 months after 

accomplishing the inspection required by 

paragraph (n) of this AD; and repeat the 

inspection thereafter at intervals not to 

exceed 60 months. 

(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 

doors: Perform the first inspection within 60 

months or 6,000 landings after accomplishing 

the inspection required by paragraph (n) of 

this AD, whichever occurs first; and repeat 

the inspection thereafter at intervals not to 

exceed 60 months or 6,000 landings, 

whichever occurs first. 

Repair of Scuff Plates If Necessary 

(p) If any crack is found during any 

inspection required by paragraph (o) of this 

AD, prior to further flight, repair in 

accordance with Airbus Service Bulletin 

A300–53–6022, Revision 04, dated January 

24, 2005. Thereafter, perform the repetitive 

inspections required by paragraph (o) of this 

AD at the applicable times specified in 

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

(q) If corrosion is found during any 

inspection required by paragraph (o) of this 

AD, prior to further flight, repair in 

accordance with Airbus Service Bulletin 

A300–53–6022, Revision 04, dated January 

24, 2005. Thereafter, perform the repetitive 

inspections required by paragraph (g) of this 

AD at the applicable times specified in 

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

(1) For the upper and lower edges of the 

fail-safe ring and the upper edges of the 

corner doubler of the aft passenger/crew 

doors, and for the mid passenger/crew door: 

Inspect at intervals not to exceed 60 months 

or 5,000 landings, whichever occurs first. 

(2) For the forward passenger/crew doors 

and bulk cargo doors: Inspect at intervals not 

to exceed 60 months. 

Terminating Modification for Repetitive 

Inspection of Corner Doublers, Fail-Safe 

Ring, and Door Frames 

(r) Before the accumulation of 30,000 total 

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 (k) of this AD, 

whichever occurs later: Modify the 

passenger/crew door structures in accordance 


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with the Accomplishment Instructions of 

Airbus Service Bulletin A300–53–6002, 

Revision 06, dated May 17, 2004. 

Accomplishment of this modification 

constitutes terminating action for the 

inspections required by paragraphs (j) and (k) 

of this AD. The inspections required by 

paragraphs (f) and (n) of this AD, as 

applicable, must be done before 

accomplishing this modification. 

Earlier Revisions of Service Bulletins 

(s) 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 REVISIONS OF SERVICE BULLETINS

Airbus Service Bulletin Revision 

level Date 

(1) A300–53–6002 ........................................................................................................................................... 03 February 22, 1992. 

(2) A300–53–6002 ........................................................................................................................................... 4 July 13, 1992. 

(3) A300–53–6002 ........................................................................................................................................... 05 September 7, 2000. 

(4) A300–53–6011 ........................................................................................................................................... 04 July 2, 1996. 

(5) A300–53–6011 ........................................................................................................................................... 05 September 7, 2000. 

(6) A300–53–6011 ........................................................................................................................................... 06 November 12, 2002. 

(7) A300–53–6018, excluding Appendix 01 .................................................................................................... 02 November 27, 2000. 

(8) A300–53–6022 ........................................................................................................................................... 01 July 2, 1996. 

(9) A300–53–6022 ........................................................................................................................................... 02 September 7, 2000. 

(10) A300–53–6022 ......................................................................................................................................... 03 November 12, 2002. 

Alternative Methods of Compliance (AMOCs) 

(t)(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) AMOCs approved previously in 

accordance with AD 98–16–05 are approved 

as AMOCs for the corresponding provisions 

of paragraphs (f) through (l) 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 

(u) 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. E7–715 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–2007–26864; Directorate 

Identifier 2006–NM–228–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–200, –300, –400, –500, –600, 

–700, –800, and –900 Series Airplanes; 

Boeing Model 757–200 and –300 Series 

Airplanes; and McDonnell Douglas 

Model DC–10–10, DC–10–10F, DC–10–

30, DC–10–30F, DC–10–40, MD–10–

30F, MD–11, and MD–11F Airplanes; 

Equipped With Reinforced Flight Deck 

Doors Installed in Accordance With 

Supplemental Type Certificate (STC) 

ST01335LA, STC ST01334LA, and STC 

ST01391LA, Respectively 

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 certain 

transport category airplanes identified 

above. The existing AD currently 

requires modification of the reinforced 

flight deck door and other actions 

related to the reinforced flight deck 

door. Those other actions include 

modifying the door, inspecting and 

modifying wiring in the area, and 

revising the maintenance program to 

require more frequent testing of the 

decompression panels of the flight deck 

door. This proposed AD would add 

airplanes to the existing requirement of 

a one-time inspection for chafing of wire 

bundles in the area of the flight deck 

door and corrective actions if necessary. 

This proposed AD would remove 

certain airplanes from the applicability. 

This proposed AD results from a report 

of smoke and fumes in the cockpit of a 

Model 737–300 series airplane. We are 

proposing this AD to prevent 

inadvertent release of the 

decompression latch and consequent 

opening of the decompression panel in 

the flight deck door, or penetration of 

the flight deck door by smoke or 

shrapnel, any of which could result in 

injury to the airplane flightcrew. We are 

also proposing this AD to detect and 

correct wire chafing, which could result 

in arcing, fire, and/or reduced 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by March 5, 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 Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207; Boeing 

Commercial Airplanes, Long Beach 


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