Federal Register / Vol. 78, No. 156 / Tuesday, August 13, 2013 / Proposed Rules 49213 

Issued in Kansas City, Missouri, on August 

6, 2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–19638 Filed 8–12–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0692; Directorate 

Identifier 2012–NM–024–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2011–14– 

06 that applies to all Airbus Model 

A318, A319, A320, and A321 series 

airplanes. That AD currently requires 

revising the maintenance program. 

Since we issued that AD, we have 

determined that more restrictive 

limitations are necessary. This proposed 

AD would require revising the 

maintenance program to incorporate 

new limitations. We are proposing this 

AD to prevent fatigue cracking, 

accidental damage, or corrosion in 

principal structural elements, and 

possible failure of certain life limited 

parts, which could result in reduced 

structural integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by September 27, 

2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus, 

Airworthiness Office—EIAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1405; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2013–0692; Directorate Identifier 

2012–NM–024–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On June 24, 2011, we issued AD 

2011–14–06, Amendment 39–16741 (76 

FR 42024, July 18, 2011). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2011–14–06, 

Amendment 39–16741 (76 FR 42024, 

July 18, 2011), we have determined that 

more restrictive limitations are 

necessary. The European Aviation 

Safety Agency (EASA), which is the 

Technical Agent for the Member States 

of the European Community, has issued 

EASA Airworthiness Directive 2012– 

0008, dated January 16, 2012 (referred to 

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

unsafe condition for the specified 

products. The MCAI states: 

The airworthiness limitations for Airbus 

aeroplanes are currently published in 

Airworthiness Limitations Section (ALS) 

documents. The airworthiness limitations 

applicable to the Safe Life Airworthiness 

Limitation Items (SL ALI) are specified in 

Airbus A318/A319/A320/A321 ALS Part 1, 

which is approved by the European Aviation 

Safety Agency (EASA). 

EASA AD 2006–0162 [which corresponds to 

FAA AD 2007–20–05, Amendment 39–15215 

(72 FR 56262, October 3, 2007) which was 

superseded by FAA AD 2011–14–06, 

Amendment 39–16741 (76 FR 42024, July 18, 

2011)] was issued to require the 

implementation of the instructions and 

airworthiness limitations as specified in 

Airbus A318/A319/A320/A321 ALS Part 1 

original issue. Failure to comply with the 

instructions of ALS Part 1 could result in an 

unsafe condition. 

This [EASA] AD retains the requirements of 

EASA AD 2006–0162, which is superseded, 

extends the applicability by adding the 

Models A318–121, A318–122, A320–215 and 

A320–216, and requires the implementation 

of the instructions and airworthiness 

limitations as specified in Airbus A318/ 

A319/A320/A321 ALS part 1 revision 02, 

approved on 13 May 2011. 

The unsafe condition is fatigue cracking, 

accidental damage, or corrosion in 

principal structural elements and 

possible failure of certain life limited 

parts, which could result in reduced 

structural integrity of the airplane. The 

required actions also include revising 

the maintenance program to include 

Airbus A318/A319/A320/A321 ALS 

Part 4—Ageing Systems Maintenance, 

dated January 8, 2008. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued A318/A319/A320/ 

A321 ALS Part 1—Safe Life 

Airworthiness Limitation Items, 

Revision 02, dated May 13, 2011; and 

A318/A319/A320/A321 ALS Part 4— 

Ageing Systems Maintenance, dated 

January 8, 2008. The actions described 

in this service information are intended 

to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 


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in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

This proposed AD requires revisions 

to certain operator maintenance 

documents to include new actions. 

Compliance with these actions is 

required by section 91.403(c) of the 

Federal Aviation Regulations (14 CFR 

91.403(c)). For airplanes that have been 

previously modified, altered, or repaired 

in the areas addressed by these 

inspections, an operator might not be 

able to accomplish the actions described 

in the revisions. In this situation, to 

comply with 14 CFR 91.403(c), the 

operator must request approval of an 

alternative method of compliance 

(AMOC) in accordance with the 

provisions of paragraph (o) of this 

proposed AD. The request should 

include a description of changes to the 

required inspections that will ensure the 

continued damage tolerance of the 

affected structure and the continued 

operational safety of the airplane. 

Differences Between This AD and the 

MCAI or Service Information 

Although the MCAI requires revising 

the maintenance program to include the 

incorporation of Airbus A318/A319/ 

A320/A321 ALS Part 1—Safe Life 

Airworthiness Limitation Items, 

Revision 02, dated May 13, 2011, this 

AD also requires revising the 

maintenance program to include the 

incorporation of Airbus A318/A319/ 

A320/A321 ALS Part 4—Ageing 

Systems Maintenance, dated January 8, 

2008. This difference has been 

coordinated with EASA. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 851 products of U.S. 

registry. 

The actions that are required by AD 

2011–14–06, Amendment 39–16741 (76 

FR 42024, July 18, 2011), and retained 

in this proposed AD take about 1 workhour per product, at an average labor 

rate of $85 per work hour. Based on 

these figures, the estimated cost of the 

currently required actions is $85 per 

product. 

We estimate that it would take about 

1 work-hour per product to comply with 

the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$72,335, or $85 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This proposed 

regulation is within the scope of that 

authority because it addresses an unsafe 

condition that is likely to exist or 

develop on products identified in this 

rulemaking action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2011–14–06, Amendment 39–16741 (76 

FR 42024, July 18, 2011), and adding the 

following new AD: 

Airbus: Docket No. FAA–2013–0692; 

Directorate Identifier 2012–NM–024–AD. 

(a) Comments Due Date 

We must receive comments by September 

27, 2013. 

(b) Affected ADs 

This AD supersedes AD 2011–14–06, 

Amendment 39–16741 (76 FR 42024, July 18, 

2011). 

(c) Applicability 

This AD applies to all Airbus Model A318– 

111, –112, –121, and –122 airplanes; Model 

A319–111, –112, –113, –114, –115, –131, 

–132, and –133 airplanes; Model A320–111, 

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

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

–211, –212, –213, –231, and –232 airplanes; 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Periodic inspections. 

(e) Reason 

This AD was prompted by a determination 

that more restrictive limitations are 

necessary. We are issuing this AD to prevent 

fatigue cracking, accidental damage, or 

corrosion in principal structural elements, 

and possible failure of certain life limited 

parts, which could result in reduced 

structural integrity of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Revision of Airworthiness 

Limitations Section (ALS) To Incorporate 

Safe Life ALIs 

This paragraph restates the requirements of 

paragraph (g) of AD 2011–14–06, 

Amendment 39–16741 (76 FR 42024, July 18, 

2011). For Model A318–111 and –112 

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

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

Model A320–111, –211, –212, –214, –231, 

–232, and –233 airplanes; and Model A321– 

111, –112, –131, –211, –212, –213, –231, and 

–232 airplanes: Within 3 months after 

November 7, 2007 (the effective date of AD 

2007–20–05, Amendment 39–15215 (72 FR 

56262, October 3, 2007)), revise the ALS of 

the Instructions for Continued Airworthiness 

to incorporate Sub-part 1–2, ‘‘Life Limits,’’ 

and Sub-part 1–3, ‘‘Demonstrated Fatigue 

Lives,’’ of Airbus A318/A319/A320/A321 


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ALS Part 1—Safe Life Airworthiness 

Limitation Items, dated February 28, 2006. 

Accomplish the actions in Sub-part 1–2, 

‘‘Life Limits,’’ and Sub-part 1–3, 

‘‘Demonstrated Fatigue Lives,’’ of Airbus 

A318/A319/A320/A321 ALS Part 1—Safe 

Life Airworthiness Limitation Items, dated 

February 28, 2006, at the times specified in 

Sub-part 1–2, ‘‘Life Limits,’’ and Sub-part 1– 

3, ‘‘Demonstrated Fatigue Lives,’’ of Airbus 

A318/A319/A320/A321 ALS Part 1—Safe 

Life Airworthiness Limitation Items, dated 

February 28, 2006, except as provided by 

paragraph (h) of this AD. Doing the actions 

required by paragraph (m) of this AD 

terminates the requirements of this 

paragraph. 

(h) Retained Grace Period for New or More 

Restrictive Actions 

This paragraph restates certain provisions 

of paragraph (i) of AD 2011–14–06, 

Amendment 39–16741 (76 FR 42024, July 18, 

2011). For Model A318–111 and –112 

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

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

Model A320–111, –211, –212, –214, –231, 

–232, and –233 airplanes; and Model A321– 

111, –112, –131, –211, –212, –213, –231, and 

–232 airplanes: For any new or more 

restrictive life limit introduced with Sub-part 

1–2, ‘‘Life Limits,’’ and Sub-part 1–3, 

‘‘Demonstrated Fatigue Lives,’’ of Airbus 

A318/A319/A320/A321 ALS Part 1—Safe 

Life Airworthiness Limitation Items, dated 

February 28, 2006, replace the part at the 

time specified in Sub-part 1–2, ‘‘Life Limits,’’ 

and Sub-part 1–3, ‘‘Demonstrated Fatigue 

Lives,’’ of Airbus A318/A319/A320/A321 

ALS Part 1—Safe Life Airworthiness 

Limitation Items, dated February 28, 2006, or 

within 6 months after November 7, 2007 (the 

effective date of AD 2007–20–05, 

Amendment 39–15215 (72 FR 56262, October 

3, 2007)), whichever is later. 

(i) Retained Revision of ALS To Incorporate 

Damage-Tolerant ALIs With Revised 

Compliance Times 

This paragraph restates the requirements of 

paragraph (j) of AD 2011–14–06, Amendment 

39–16741 (76 FR 42024, July 18, 2011), with 

revised compliance times. Within 9 months 

after August 22, 2011 (the effective date of 

AD 2011–14–06): Revise the maintenance 

program by incorporating all maintenance 

requirements and associated airworthiness 

limitations specified in the Airbus A318/ 

A319/A320/A321 Airworthiness Limitation 

Items, Document AI/SE–M4/95A.0252/96, 

Issue 10, dated October 2009; or Issue 11, 

dated September 2010. Comply with all 

applicable maintenance requirements and 

associated airworthiness limitations included 

in Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 10, dated 

October 2009; or Issue 11, dated September 

2010; except as provided by paragraph (j) of 

this AD. Doing the actions required by 

paragraph (m) of this AD terminates the 

requirements of this paragraph. 

(j) Retained Special Compliance Times for 

Certain Tasks 

This paragraph restates the requirements of 

paragraph (k) of AD 2011–14–06, 

Amendment 39–16741 (76 FR 42024, July 18, 

2011), with changes to table 1 to paragraph 

(j) of this AD. For new and more restrictive 

tasks introduced with Airbus A318/A319/ 

A320/A321 Airworthiness Limitation Items, 

Document AI/SE–M4/95A.0252/96, Issue 10, 

dated October 2009; or Issue 11, dated 

September 2010; as specified in table 1 to 

paragraph (j) of this AD: The initial 

compliance time for doing the tasks is 

specified in table 1 to paragraph (j) of this 

AD. 

TABLE 1 TO PARAGRAPH (j) OF THIS AD—Compliance Times for Tasks 

Task Applicability (as specified in the 

applicability column of the task) 

Compliance time, whichever occurs later 

545102–01–6 .................. Group 19–1A CFM, Group 19– 

1B CFM, and Model A320– 

200 airplanes with CFM Industrial (CFM)/International 

Aero Engine (IAE) engines.

The threshold as defined in Airbus 

A318/A319/A320/A321 Airworthiness 

Limitation Items, Document AI/SE– 

M4/95A.0252/96, Issue 10, dated October 2009; or Issue 11, dated September 2010.

Within 2,000 flight cycles or 5,500 flight 

hours, after August 22, 2011 (the effective date of AD 2011–14–06, 

Amendment 39–16741 (76 FR 42024, 

July 18, 2011)), whichever occurs 

first. 

545102–01–7 .................. Model A320–100 series airplanes.The threshold as defined in Airbus 

A318/A319/A320/A321 Airworthiness 

Limitation Items, Document AI/SE– 

M4/95A.0252/96, Issue 10, dated October 2009; or Issue 11, dated September 2010.

Within 2,000 flight cycles or 2,000 flight 

hours, after August 22, 2011 (the effective date of AD 2011–14–06, 

Amendment 39–16741 (76 FR 42024, 

July 18, 2011)), whichever occurs 

first. 

572050–01–1 or alternative task 572050– 

02–1.

Group 19–1A and Group 19–1B 

airplanes.

At the time of the next due accomplishment of any one of the tasks 572004, 

572020, or 572053 as currently described in the Airbus A318/A319/ 

A320/A321 Airworthiness Limitation 

Items, Document AI/SE–M4/ 

95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 

2006; or Issue 09, dated November 

2006.

Within 6 months after August 22, 2011 

(the effective date of AD 2011–14– 

06, Amendment 39–16741 (76 FR 

42024, July 18, 2011)). 

572050–01–4 or alternative task 572050– 

02–4.

Model A320–200 series airplanes.At the time of the next due accomplishment of any one of the tasks 572004, 

572020, or 572053 as currently described in the Airbus A318/A319/ 

A320/A321 Airworthiness Limitation 

Items, Document AI/SE–M4/ 

95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 

2006; or Issue 09, dated November 

2006.

Within 6 months after August 22, 2011 

(the effective date of AD 2011–14– 

06, Amendment 39–16741 (76 FR 

42024, July 18, 2011)). 


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TABLE 1 TO PARAGRAPH (j) OF THIS AD—Compliance Times for Tasks—Continued 

Task 

572050–01–5 or alternative task 572050– 

02–5.

Group 21–1A airplanes ............. At the time of the next due accomplishment of any one of the tasks 572004, 

572020, or 572053 as currently described in the Airbus A318/A319/ 

A320/A321 Airworthiness Limitation 

Items, Document AI/SE–M4/ 

95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 

2006; or Issue 09, dated November 

2006.

Within 6 months after August 22, 2011 

(the effective date of AD 2011–14– 

06, Amendment 39–16741 (76 FR 

42024, July 18, 2011)). 

572050–01–7 or alternative task 572050– 

02–7.

Model A320–100 series airplanes.At the time of the next due accomplishment of any one of the tasks 572004, 

572020, or 572053 as currently described in the Airbus A318/A319/ 

A320/A321 Airworthiness Limitation 

Items, Document AI/SE–M4/ 

95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 

2006; or Issue 09, dated November 

2006.

Within 6 months after August 22, 2011 

(the effective date of AD 2011–14– 

06, Amendment 39–16741 (76 FR 

42024, July 18, 2011)). 

534132–01–1 .................. Model A320 PRE 30748 airplanes.The threshold/interval as defined in Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/ 

SE–M4/95A.0252/96, Issue 10, dated 

October 2009; or Issue 11, dated 

September 2010.

Within 100 days after August 22, 2011 

(the effective date of AD 2011–14– 

06, Amendment 39–16741 (76 FR 

42024, July 18, 2011)), without exceeding the previous threshold/interval as defined in Airbus A318/A319/ 

A320/A321 Airworthiness Limitation 

Items, Document AI/SE–M4/ 

95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 

2006; or Issue 09, dated November 

2006. 

531118–01–1 .................. Model A318 (except (A318–121 

and –122), Group 19–1A, 

Group 19–1B, and Model 

A320 and A321 series airplanes.

The threshold/interval as defined in Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/ 

SE–M4/95A.0252/96, Issue 10, dated 

October 2009; or Issue 11, dated 

September 2010.

Within 100 days after August 22, 2011 

(the effective date of AD 2011–14– 

06, Amendment 39–16741 (76 FR 

42024, July 18, 2011)), without exceeding the previous threshold/interval as defined in Airbus A318/A319/ 

A320/A321 Airworthiness Limitation 

Items, Document AI/SE–M4/ 

95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March 

2006; or Issue 09, dated November 

2006. 

531118–01–1 .................. Model A318–121 and –122 airplanes.The threshold/interval as defined in Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/ 

SE–M4/95A.0252/96, Issue 10, dated 

October 2009; or Issue 11, dated 

September 2010.

Within 100 days after August 22, 2011 

(the effective date of AD 2011–14– 

06, Amendment 39–16741 (76 FR 

42024, July 18, 2011)). 

Note 1 to table 1 to paragraph (j) of this AD: ALI Task 572050 refers to the outer wing dry bay and is comprised of extracts from three ALI 

Tasks 572004, 572020, and 572053. The threshold of ALI Task 572050 for the whole dry bay area is that of the lowest threshold of the source 

ALI tasks, i.e., that of ALI Task 572053. 

(k) Retained Limitation: No Alternative Life 

Limits, Inspections, or Inspection Intervals 

After Accomplishment of the Actions 

Specified in Paragraph (g) of This AD 

This paragraph restates the requirements of 

paragraph (l) of AD 2011–14–06, Amendment 

39–16741 (76 FR 42024, July 18, 2011). After 

the actions specified in paragraph (g) of this 

AD have been accomplished, no alternative 

life limits, inspections, or inspection 

intervals may be used, except as provided by 

paragraph (h) of this AD, and except as 

required by paragraph (m) of this AD. 

(l) Retained Limitation: No Alternative Life 

Limits, Inspections, or Inspection Intervals 

After Accomplishment of the Actions 

Specified in Paragraph (j) of This AD 

This paragraph restates the requirements of 

paragraph (m) of AD 2011–14–06, 

Amendment 39–16741 (76 FR 42024, July 18, 

2011). After the actions specified in 

paragraph (i) of this AD have been 

accomplished, no alternative life limits, 

inspections, or inspection intervals may be 

used, except as required by paragraph (m) of 

this AD. 

(m) New Maintenance Program Revision 

Within 30 days after the effective date of 

this AD, revise the maintenance program to 

incorporate Airbus A318/A319/A320/A321 

ALS Part 1—Safe Life Airworthiness 

Limitation Items, Revision 02, dated May 13, 

2011; and Airbus A318/A319/A320/A321 

ALS Part 4—Ageing Systems Maintenance, 

dated January 8, 2008. The initial compliance 

time for the accomplishing the actions is at 

the applicable time specified in Airbus A318/ 

A319/A320/A321 ALS Part 1—Safe Life 

Airworthiness Limitation Items, Revision 02, 

dated May 13, 2011, and Airbus A318/A319/ 

A320/A321 ALS Part 4—Ageing Systems 


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Maintenance, dated January 8, 2008; or 

within 4 months after the effective date of 

this AD; whichever occurs later. 

(n) New Limitation: No Alternative Actions 

or Intervals 

After accomplishing the revision required 

by paragraph (m) of this AD, no alternative 

actions (e.g., inspections) or intervals, may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (o) of this 

AD. 

(o) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. AMOCs 

approved previously in accordance with AD 

2011–14–06, Amendment 39–16741 (76 FR 

42024, July 18, 2011), are approved as 

AMOCs for the corresponding actions 

specified in this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2012–0008, dated 

January 16, 2012, and the service information 

specified in paragraphs (p)(1)(i) through 

(p)(1)(viii) of this AD, for related information. 

(i) Airbus A318/A319/A320/A321 ALS Part 

1—Safe Life Airworthiness Limitation Items, 

Revision 02, dated May 13, 2011. 

(ii) Airbus A318/A319/A320/A321 ALS 

Part 1—Safe Life Airworthiness Limitation 

Items, dated February 28, 2006. 

(iii) Airbus A318/A319/A320/A321 ALS 

Part 4—Ageing Systems Maintenance, dated 

January 8, 2008. 

(iv) Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 7, dated 

December 2005. 

(v) Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 08, dated 

March 2006. 

(vi) Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 09, dated 

November 2006. 

(vii) Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 10, dated 

October 2009. 

(viii) Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 11, dated 

September 2010. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. You may review copies of 

the referenced service information at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on August 

2, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–19528 Filed 8–12–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1069; Directorate 

Identifier 2012–NM–044–AD] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD), 

for all The Boeing Company Model 727 

airplanes, which proposed to supersede 

an existing AD. That NPRM proposed to 

retain repetitive inspections of the intank fuel boost pump wiring, 

installation of sleeving over the in-tank 

fuel boost pump wires, repetitive 

inspections of a certain electrical wire, 

sleeve, and conduit, and applicable 

investigative and corrective actions; and 

repetitive engine fuel suction feed 

operational tests. That NPRM proposed 

to also require replacement of the wire 

bundles for the wing and center fuel 

boost pumps, installation of convoluted 

liners, and related investigative and 

corrective actions if necessary. That 

NPRM also proposed to require 

replacement of the fuel quantity 

indicating system (FQIS) wires; a lowfrequency eddy current inspection for 

cracking; and repair if necessary. That 

NPRM also proposed to require revising 

the maintenance program to incorporate 

changes to the airworthiness limitations 

section. That NPRM was prompted by a 

report of damage found to the sleeve, 

jacket, and insulation on an electrical 

wire during a repetitive inspection. This 

action revises that NPRM by revising 

certain compliance times, specifying a 

terminating action, and adding a 

proposed requirement to incorporate 

another change to the airworthiness 

limitations section. We are proposing 

this supplemental NPRM to prevent 

chafing of the fuel boost pump electrical 

wiring and leakage of fuel into the 

conduit, and to prevent electrical arcing 

between the wiring and the surrounding 

conduit, which could result in arcthrough of the conduit, and consequent 

fire or explosion of the fuel tank. Since 

these actions impose an additional 

burden over that proposed in the NPRM, 

we are reopening the comment period to 

allow the public the chance to comment 

on these proposed changes. 

DATES: We must receive comments on 

this supplemental NPRM by September 

27, 2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206– 

766–5680; Internet https:// 

www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport 


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