9880 Federal Register / Vol. 72, No. 43 / Tuesday, March 6, 2007 / Proposed Rules 

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 adding the following new 

airworthiness directive (AD): 

Boeing: Docket No. FAA–2007–27359; 

Directorate Identifier 2006–NM–042–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by April 20, 2007. 

Affected ADs 

(b) AD 90–06–06, amendment 39–6490, 

paragraph A., requires installation of external 

skin doublers in the area near the flight deck 

windows for Group 1 airplanes, which ends 

the repetitive high-frequency eddy current 

(HFEC) inspections required by this AD only 

for those airplanes. Installing external skin 

doublers as required by paragraph (g) of this 

AD ends certain repetitive inspections of the 

fuselage skin required by paragraph (f) of AD 

2005–08–01, amendment 39–14053, only for 

the area near the flight deck windows 

modified by the external skin doublers. 

Applicability 

(c) This AD applies to Boeing Model 747–

100, 747–100B, 747–200B, 747–200C, 747–

200F, 747–300, 747SR, and 747SP series 

airplanes, certificated in any category; as 

identified in Boeing Alert Service Bulletin 

747–53A2542, dated February 16, 2006. 

Unsafe Condition 

(d) This AD results from reports of fatigue 

cracks in the fuselage skin near stringer 5 

between body stations 340 and 350. We are 

issuing this AD to detect and correct fatigue 

cracking of the fuselage skin near stringer 5. 

Cracks in this area could join together and 

result in in-flight depressurization of the 

airplane. 

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. 

Inspections and Corrective Actions 

(f) For any airplane that has not had 

external skin doublers installed around the 

left- or right-side Number 3 flight deck 

window in accordance with Boeing Service 

Bulletin 747–53–2272, Revision 18, dated 

May 16, 2002, or an earlier revision: Do the 

applicable actions described in paragraphs 

(f)(1) and (f)(2) of this AD. Do all the actions 

in and in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2542, dated 

February 16, 2006. Do the actions at the 

compliance times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2542, dated February 16, 

2006, on the side(s) of the airplane on which 

the doubler installation has not been done; 

except where the service bulletin specifies 

compliance times after the date on the 

service bulletin, this AD requires compliance 

times after the effective date of this AD. 

Installing external skin doublers around the 

left- or right-side Number 3 flight deck 

windows in accordance with Boeing Service 

Bulletin 747–53–2272, Revision 18, or an 

earlier revision; ends the repetitive HFEC 

inspections required by this paragraph on the 

side of the airplane on which the doubler is 

installed. After the effective date of this AD, 

only Boeing Service Bulletin 747–53–2272, 

Revision 18, may be used to install the 

external skin doublers around the left- and 

right-side Number 3 flight deck windows. 

(1) Do a HFEC inspection for cracks of the 

fuselage skin at stringer 5, between body 

stations 340 and 350; and do all applicable 

corrective actions before further flight. 

(2) Repeat the HFEC inspection thereafter 

at the applicable interval specified in 

paragraph 1.E. of Boeing Alert Service 

Bulletin 747–53A2542. 

Terminating Action 

(g) For Group 2 airplanes only: Before 

accumulating 24,000 total flight cycles, or 

within 250 flight cycles after the effective 

date of the AD, whichever occurs later, 

install external skin doublers around the leftand right-side Number 3 flight deck 

windows; in accordance with Boeing Service 

Bulletin 747–53–2272, Revision 17, dated 

November 18, 1999; or Revision 18, dated 

May 16, 2002. After the effective date of this 

AD, only Boeing Service Bulletin 747–53–

2272, Revision 18, may be used to 

accomplish the doubler installation around 

the left- and right-side Number 3 flight deck 

windows. Accomplishing this action ends 

the repetitive inspections required by 

paragraph (f) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Issued in Renton, Washington, on February 

23, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–3842 Filed 3–5–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–25658; Directorate 

Identifier 2006–NM–054–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318, A319, A320, and A321 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 

NPRM for an airworthiness directive 

(AD) that applies to certain Airbus 

Model A318, A319, A320, and A321 

airplanes. The original NPRM would 

have superseded an existing AD that 

currently requires repetitive detailed 

inspections of the inboard flap 

trunnions for any wear marks and of the 

sliding panels for any cracking at the 

long edges, and corrective actions if 

necessary. The original NPRM proposed 

to add airplanes to the applicability in 

the existing AD and change the 

inspection type. The original NPRM 

resulted from a determination that 

certain airplanes must be included in 

the applicability of the AD, and that the 

inspection type must be revised. This 

new action revises the original NPRM 

by including airplanes that were 

inadvertently excluded from the 

applicability. We are proposing this 

supplemental NPRM to detect and 

correct wear of the inboard flap 

trunnions, which could lead to loss of 

flap surface control and consequently 

result in the flap detaching from the 

airplane. A detached flap could result in 

damage to the tail of the airplane. 

DATES: We must receive comments on 

this supplemental NPRM by April 2, 

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. 


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• 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 

supplemental NPRM. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed in the 

ADDRESSES section. Include the docket 

number ‘‘Docket No. FAA–2006–25658; 

Directorate Identifier 2006–NM–054–

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this supplemental NPRM. We will 

consider all comments received by the 

closing date and may amend this 

supplemental NPRM in light of those 

comments. 

We will post all comments submitted, 

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 supplemental NPRM. 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 ADDRESSES. 

Comments will be available in the AD 

docket shortly after the Docket 

Management System receives them. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) (the ‘‘original 

NPRM’’) to amend 14 CFR part 39 to 

include an AD that supersedes AD 

2006–04–06, amendment 39–14487 (71 

FR 8439, February 17, 2006). The 

original NPRM applies to certain Airbus 

Model A318, A319, A320, and A321–

100 airplanes. The original NPRM was 

published in the Federal Register on 

August 22, 2006 (71 FR 48838). The 

original NPRM proposed to continue to 

require repetitive detailed inspections of 

the inboard flap trunnions for any wear 

marks and of the sliding panels for any 

cracking at the long edges, and 

corrective actions if necessary. The 

original NPRM also proposed to add 

airplanes to the applicability in the 

existing AD and change the inspection 

type. 

Actions Since Original NPRM Was 

Issued 

We have determined that the original 

NPRM should have applied to certain 

Airbus Model A318 airplanes, and all 

Airbus Model A319, A320, and A321–

111, –112, and –131 airplanes. In the 

original NPRM, we stated that we were 

adding Model A321–211 and –231 

airplanes; however, the applicability 

was inadvertently changed to Model 

A318, A319, A320, and A321 airplanes 

on which Airbus Modification 26495 

has been incorporated in production. 

The change resulted in the airplanes 

identified in paragraph (f) of the original 

NPRM (Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 

airplanes; Model A320–111 airplanes; 

Model A320–211, –212, –214, –231, 

–232, and –233 airplanes; and Model 

A321–111, –112, and –131 airplanes; 

except those on which Airbus 

Modification 26495 has been 

accomplished in production) being 

excluded from the applicability of the 

original NPRM. We have changed the 

applicability in this supplemental 

NPRM to certain Airbus Model A318 

airplanes, and ‘‘all’’ Airbus Model 

A319–111, –112, –113, –114, –115, 

–131, –132, and –133 airplanes; Model 

A320–111 airplanes; Model A320–211, 

–212, –214, –231, –232, and –233 

airplanes; and Model A321–111, –112, 

–131, –211, and –231 airplanes. 

Relevant Service Information 

Airbus has issued Service Bulletins 

A320–27–1117, Revision 03, dated 

August 24, 2001; and Revision 04, dated 

November 6, 2001. (Airbus Service 

Bulletin A320–27–1117, Revision 02, 

dated January 18, 2000, was referenced 

in the original NPRM as the appropriate 

source of service information for 

accomplishing the modification.) Airbus 

has also issued Airbus Service Bulletin 

A320–57–1133, Revision 01, dated 

August 7, 2006. (Airbus Service Bulletin 

A320–57–1133, dated July 28, 2005, was 

referenced in the original NPRM as the 

appropriate source of service 

information for accomplishing the 

inspections.) The changes in these 

revisions are minor and no additional 

work is necessary for airplanes modified 

by the previous issues. We have 

changed the AD to refer to this revised 

service information as the appropriate 

source of service information for 

accomplishing the required actions. In 

addition, we have added new 

paragraphs (k) and (l) to this AD to 

provide credit for accomplishing the 

actions before the effective date of this 

AD in accordance with the service 

information referenced in the original 

NPRM. Subsequent paragraphs have 

been re-identified accordingly. 

Accomplishing the actions specified in 

the service information is intended to 

adequately address the unsafe 

condition. 

Comments 

We have considered the following 

comments on the original NPRM. 

Support for the NPRM 

Airbus supports the original NPRM. 

Request To Incorporate/Publish Certain 

Information 

The Modification and Replacement 

Parts Association (MARPA) states that, 

frequently, airworthiness directives are 

based on service information originating 

with the type certificate holder or its 

suppliers. MARPA adds that 

manufacturer service documents are 

privately authored instruments 

generally having copyright protection 

against duplication and distribution. 

MARPA notes that when a service 

document is incorporated by reference 

into a public document, such as an 

airworthiness directive, it loses its 

private, protected status and becomes a 

public document. MARPA adds that if 

a service document is used as a 

mandatory element of compliance, it 

should not simply be referenced, but 

should be incorporated into the 

regulatory document; by definition, 

public laws must be public, which 


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means they cannot rely upon private 

writings. MARPA notes that since the 

interpretation of a document is a 

question of law, and not fact, a service 

document not incorporated by reference 

will not be considered in a legal finding 

of the meaning of an airworthiness 

directive. MARPA is concerned that the 

failure to incorporate essential service 

information could result in a court 

decision invalidating the airworthiness 

directive. 

MARPA adds that incorporated by 

reference service documents should be 

made available to the public by 

publication in the Docket Management 

System (DMS), keyed to the action that 

incorporates them. MARPA notes that 

the stated purpose of the incorporation 

by reference method is brevity, to keep 

from expanding the Federal Register 

needlessly by publishing documents 

already in the hands of the affected 

individuals; traditionally, ‘‘affected 

individuals’’ means aircraft owners and 

operators, who are generally provided 

service information by the 

manufacturer. MARPA adds that a new 

class of affected individuals has 

emerged, since the majority of aircraft 

maintenance is now performed by 

specialty shops instead of aircraft 

owners and operators. MARPA notes 

that this new class includes 

maintenance and repair organizations, 

component servicing and repair shops, 

parts purveyors and distributors, and 

organizations manufacturing or 

servicing alternatively certified parts 

under section 21.303 (‘‘Replacement 

and modification parts’’) of the Federal 

Aviation Regulations (14 CFR 21.303). 

MARPA adds that the distribution to 

owners may, when the owner is a 

financing or leasing institution, not 

actually reach the persons responsible 

for accomplishing the airworthiness 

directive. Therefore, MARPA asks that 

the service documents deemed essential 

to the accomplishment of the NPRM be 

incorporated by reference into the 

regulatory instrument, and published in 

the DMS. 

We do not agree that documents 

should be incorporated by reference 

during the NPRM phase of rulemaking. 

The Office of the Federal Register (OFR) 

requires that documents that are 

necessary to accomplish the 

requirements of the AD be incorporated 

by reference during the final rule phase 

of rulemaking. We intend that the final 

rule in this action will incorporate by 

reference the documents necessary for 

the accomplishment of the proposed 

requirements mandated by this AD. 

Further, we point out that while 

documents that are incorporated by 

reference do become public information, 

they do not lose their copyright 

protection. For that reason, we advise 

the public to contact the manufacturer 

to obtain copies of the referenced 

service information. 

Additionally, we do not publish 

service documents in DMS. We are 

currently reviewing our practice of 

publishing proprietary service 

information. Once we have thoroughly 

examined all aspects of this issue, and 

have made a final determination, we 

will consider whether our current 

practice needs to be revised. However, 

we consider that to delay this AD action 

for that reason would be inappropriate, 

since we have determined that an 

unsafe condition exists and that the 

requirements in this AD must be 

accomplished to ensure continued 

safety. Therefore, we have not changed 

the supplemental NPRM in this regard. 

Clarification of Compliance Times and 

Applicability of Paragraphs (g) and 

(j)(2) of This Supplemental NPRM 

We have changed paragraphs (g) and 

(j)(2) of this supplemental NPRM 

(paragraph (i)(2) of the original NPRM) 

to specify the ‘‘applicable’’ compliance 

times in the subparagraphs. Paragraphs 

(g)(2) and (j)(2)(ii) of this supplemental 

NPRM are applicable only to airplanes 

that have not had Airbus Modification 

26495 done in production. 

Revised Applicability in Paragraph (g) 

of This Supplemental NPRM 

We have changed the applicability in 

paragraph (g) of this supplemental 

NPRM for clarity and we have added 

Model A320–111 airplanes, which were 

inadvertently excluded from that 

paragraph in the original NPRM. 

Paragraph (g) is applicable to all 

airplanes identified in the existing AD, 

and Model A320–111 airplanes are 

included in that applicability. 

FAA’s Determination and Proposed 

Requirements of the Supplemental 

NPRM 

The changes discussed above expand 

the scope of the original NPRM; 

therefore, we have determined that it is 

necessary to reopen the comment period 

to provide additional opportunity for 

public comment on this supplemental 

NPRM. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this supplemental NPRM. 

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour Parts Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Modification in AD 

2006–04–06.

14 $80 The manufacturer 

states that it will 

supply required 

parts to operators 

at no cost.

$1,120 ...................... 755 $845,600. 

Detailed inspection in 

AD 2006–04–06.

2 80 None ......................... $160, per inspection 

cycle.

755 $120,800, per inspection cycle. 

General visual inspection (new action).1 80 None ......................... $80, per inspection 

cycle.

741 $59,280, per inspection cycle. 

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 


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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 supplemental NPRM 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 39–14487 (71 

FR 8439, February 17, 2006) and adding 

the following new airworthiness 

directive (AD): 

Airbus: Docket No.: FAA–2006–25658; 

Directorate Identifier 2006–NM–054–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by April 2, 2007. 

Affected ADs 

(b) This AD supersedes AD 2006–04–06. 

Applicability 

(c) This AD applies to the airplanes 

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

this AD, certificated in any category. 

(1) Airbus Model A318–111 and –112 

airplanes on which Airbus Modification 

26495 has been incorporated in production. 

(2) All Airbus Model A319–111, –112, 

–113, –114, –115, –131, –132, and –133 

airplanes; Model A320–111 airplanes; Model 

A320–211, –212, –214, –231, –232, and –233 

airplanes; and Model A321–111, –112, –131, 

–211, and –231 airplanes. 

Unsafe Condition 

(d) This AD results from a determination 

that certain airplanes must be included in the 

applicability of the AD, and that the 

inspection type must be revised. We are 

issuing this AD to detect and correct wear of 

the inboard flap trunnions, which could lead 

to loss of flap surface control and 

consequently result in the flap detaching 

from the airplane. A detached flap could 

result in damage to the tail of the airplane. 

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. 

Restatement of Requirements of AD 2006–

04–06 

Modification 

(f) For Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes; Model 

A320–111 airplanes; Model A320–211, –212, 

–214, –231, –232, and –233 airplanes; and 

Model A321–111, –112, and –131 airplanes; 

except those on which Airbus Modification 

26495 has been accomplished in production: 

Within 18 months after January 8, 2001 (the 

effective date of AD 2000–24–02, amendment 

39–12009), modify the sliding panel driving 

mechanism of the flap drive trunnions, in 

accordance with Airbus Service Bulletin 

A320–27–1117, Revision 02, dated January 

18, 2000; or Revision 04, dated November 6, 

2001. As of the effective date of this AD, only 

Revision 04 may be used. 

Note 1: Accomplishment of the 

modification required by paragraph (f) of this 

AD before January 8, 2001, in accordance 

with Airbus Service Bulletin A320–27–1117, 

dated July 31, 1997; or Revision 01, dated 

June 25, 1999; is acceptable for compliance 

with that paragraph. 

Detailed Inspections 

(g) For Model A318–111 and –112 

airplanes; Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 airplanes; 

Model A320–111 airplanes; Model A320–

211, –212, –214, –231, –232, and –233 

airplanes; and Model A321–111, –112, and 

–131 airplanes: At the latest of the applicable 

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

and (g)(3) of this AD, do a detailed inspection 

of the inboard flap trunnions for any wear 

marks and of the sliding panels for any 

cracking at the long edges, and do any 

corrective actions, as applicable, by 

accomplishing all of the applicable actions 

specified in the Accomplishment 

Instructions of Airbus Service Bulletin A320–

57–1133, dated July 28, 2005; or Revision 01, 

dated August 7, 2006; except as provided by 

paragraph (p) of this AD. As of the effective 

date of this AD, only Revision 01 may be 

used. Any corrective actions must be done at 

the compliance times specified in Figures 5 

and 6, as applicable, of the service bulletin; 

except as provided by paragraphs (m), (n), 

and (o) of this AD. Repeat the inspection 

thereafter at intervals not to exceed 4,000 

flight hours until the inspection required by 

paragraph (j) of this AD is done. 

Note 2: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

(1) Before accumulating 4,000 total flight 

hours on the inboard flap trunnion since 

new. 

(2) Within 4,000 flight hours after 

accomplishing paragraph (f) of this AD. 

(3) Within 600 flight hours after March 24, 

2006 (the effective date of AD 2006–04–06). 

New Requirements of This AD 

Modification 

(h) For Model A321–211 and –231 

airplanes, except those on which Airbus 

Modification 26495 has been accomplished 

in production: Within 18 months after the 

effective date of this AD, modify the sliding 

panel driving mechanism of the flap drive 

trunnions, in accordance with Airbus Service 

Bulletin A320–27–1117, Revision 04, dated 

November 6, 2001. 

(i) Accomplishing the modification 

specified in paragraph (h) of this AD is 

acceptable for compliance with the 

requirements of that paragraph if done before 

the effective date of this AD in accordance 

with the applicable service bulletin 

identified in Table 1 of this AD. 

TABLE 1.—AIRBUS SERVICE BULLETINS

Service Bulletin Revision level Date 

A320–27–1117 .................................................................................................................................... Original .................... July 31, 1997. 

A320–27–1117 .................................................................................................................................... Revision 01 .............. June 25, 1999. 

A320–27–1117 .................................................................................................................................... Revision 02 .............. January 18, 2000. 


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TABLE 1.—AIRBUS SERVICE BULLETINS—Continued 

Service Bulletin Revision level Date 

A320–27–1117 .................................................................................................................................... Revision 03 .............. August 24, 2001. 

General Visual Inspections 

(j) For all airplanes: At the time specified 

in paragraph (j)(1) or (j)(2) of this AD, as 

applicable, do a general visual inspection of 

the inboard flap trunnions for any wear 

marks and of the sliding panels for any 

cracking at the long edges, and do all 

applicable corrective actions, by 

accomplishing all of the applicable actions 

specified in the Accomplishment 

Instructions of Airbus Service Bulletin A320–

57–1133, Revision 01, dated August 7, 2006; 

except as provided by paragraph (p) of this 

AD. All corrective actions must be done at 

the compliance times specified in Figures 5 

and 6, as applicable, of the service bulletin; 

except as provided by paragraphs (m), (n), 

and (o) of this AD. Repeat the inspection 

thereafter at intervals not to exceed 4,000 

flight hours. Accomplishment of the general 

visual inspection required by this paragraph 

terminates the detailed inspection 

requirement of paragraph (g) of this AD. 

Note 3: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’

(1) For airplanes on which the detailed 

inspection required by paragraph (g) of this 

AD has been done before the effective date 

of this AD: Inspect before accumulating 4,000 

total flight hours on the inboard flap 

trunnion since new, or within 4,000 flight 

hours after accomplishing the most recent 

inspection required by paragraph (g) of this 

AD, whichever occurs later. 

(2) For airplanes other than those 

identified in paragraph (j)(1) of this AD: 

Inspect at the latest of the applicable times 

specified in paragraphs (j)(2)(i), (j)(2)(ii), and 

(j)(2)(iii) of this AD. 

(i) Before accumulating 4,000 total flight 

hours on the inboard flap trunnion since 

new. 

(ii) Within 4,000 flight hours after 

accomplishing paragraph (f) or (h) of this AD. 

(iii) Within 600 flight hours after the 

effective date of this AD. 

Actions Accomplished According to Previous 

Issue of Service Bulletins 

(k) Accomplishment of the modification 

required by paragraph (f) of this AD before 

the effective date of this AD, in accordance 

with Airbus Service Bulletin A320–27–1117, 

Revision 03, dated August 24, 2001, is 

acceptable for compliance with the 

requirements of that paragraph. 

(l) Accomplishment of the inspections 

required by paragraph (j) of this AD before 

the effective date of this AD, in accordance 

with Airbus Service Bulletin A320–57–1133, 

dated July 28, 2005, is acceptable for 

compliance with the requirements of that 

paragraph. 

Compliance Times 

(m) Where Airbus Service Bulletins A320–

57–1133, dated July 28, 2005; and Revision 

01, dated August 7, 2006; specify replacing 

the sliding panel at the next opportunity if 

damaged, replace it within 600 flight hours 

after the inspection required by paragraph (g) 

or (j) of this AD, as applicable. 

(n) If any damage to the trunnion is found 

during any inspection required by paragraph 

(g) or (j) of this AD, before further flight, do 

the corrective actions specified in Airbus 

Service Bulletin A320–57–1133, dated July 

28, 2005; or Revision 01, dated August 7, 

2006. As of the effective date of this AD, only 

Revision 01 may be used. 

Grace Period Assessment 

(o) Where Airbus Service Bulletins A320–

57–1133, dated July 28, 2005; and Revision 

01, dated August 7, 2006; specify contacting 

the manufacturer for a grace period 

assessment after replacing the trunnion or 

flap, contact the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; the Direction Ge ́ne ́rale de 

l’Aviation Civile; or the European Aviation 

Safety Agency (or its delegated agent); for the 

grace period assessment. 

No Reporting Requirement 

(p) Although Airbus Service Bulletins 

A320–57–1133, dated July 28, 2005; and 

Revision 01, dated August 7, 2006; specify to 

submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

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) Before using any AMOC approved in 

accordance with 14 CFR 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 directive F–2005–

139, dated August 3, 2005, also addresses the 

subject of this AD. 

Issued in Renton, Washington, on February 

23, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–3841 Filed 3–5–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE INTERIOR 

Minerals Management Service 

30 CFR Part 250 

RIN 1010–AD12 

Oil and Gas and Sulphur Operations 

on the Outer Continental Shelf (OCS)—

Oil and Gas Production Requirements 

AGENCY: Minerals Management Service 

(MMS), Interior. 

ACTION: Proposed rule. 

SUMMARY: MMS proposes to amend the 

regulations regarding oil and natural gas 

production. This is a complete rewrite 

of these regulations, addressing issues 

such as production rates, burning oil, 

and venting and flaring natural gas. The 

proposed rule would eliminate most 

restrictions on production rates and 

clarify flaring and venting limits. The 

proposed rule was written using plain 

language, so it will be easier to read and 

understand. 

DATES: Submit comments by June 4, 

2007. MMS may not fully consider 

comments received after this date. 

Submit comments to the Office of 

Management and Budget on the 

information collection burden in this 

rule by April 5, 2007. 

ADDRESSES: You may submit comments 

on the rulemaking by any of the 

following methods. Please use the 

Regulation Identifier Number (RIN) 

1010–AD12 as an identifier in your 

message. See also Public Comment 

Procedures under Procedural Matters. 

• MMS’s Public Connect on-line 

commenting system, https:// 

ocsconnect.mms.gov. Follow the 

instructions on the Web site for 

submitting comments. 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions on the Web site for 

submitting comments. 

• E-mail MMS at 

rules.comments@mms.gov. Use RIN 

1010–AD12 in the subject line. 


cprice-sewell on PROD1PC67 with PROPOSALS