30492 Federal Register / Vol. 79, No. 102 / Wednesday, May 28, 2014 / Proposed Rules 

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. Amend § 39.13 by adding the 

following new airworthiness directive 

(AD): 

The Boeing Company: Docket No. FAA– 

2014–0286; Directorate Identifier 2014– 

NM–004–AD. 

(a) Comments Due Date 

We must receive comments by July 14, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 737–600 and –700 series airplanes, 

certificated in any category, as identified in 

Boeing Alert Service Bulletin 737–53A1325, 

dated December 3, 2013. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracking in the body station (STA) 727 

bulkhead lower frame. We are issuing this 

AD to detect and correct cracking in a 

bulkhead lower frame web and inner chord, 

which could result in a severed framed and 

induced skin cracks, and lead to rapid 

decompression of the fuselage. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections 

At the applicable times specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 737–53A1325, dated 

December 3, 2013, except as provided by 

paragraph (i)(1) of this AD: Do a detailed and 

open hole high frequency eddy current 

(HFEC) inspection of the left- and right-side 

lower frame webs and inner chords for 

cracking, as applicable, and do all applicable 

corrective actions and preventative 

modifications, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1325, dated 

December 3, 2013, except as required by 

paragraph (i)(2) of this AD. Repeat the 

applicable inspections required by this 

paragraph thereafter at the applicable 

intervals specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1325, dated December 3, 

2013. Do all applicable corrective actions and 

preventative modifications before further 

flight. 

(h) Terminating Action 

Accomplishment of a modification or a 

repair in accordance with Boeing Alert 

Service Bulletin 737–53A1325, dated 

December 3, 2013, terminates the repetitive 

inspections in this AD for the repaired or 

modified side only. 

(i) Exceptions to Service Information 

Specifications 

(1) Where Boeing Alert Service Bulletin 

737–53A1325, dated December 3, 2013, 

specifies a compliance time ‘‘after the 

original issue date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) Where Boeing Alert Service Bulletin 

737–53A1325, dated December 3, 2013, 

specifies to contact Boeing for appropriate 

action: Before further flight, accomplish the 

corresponding action using a method 

approved in accordance with the procedures 

specified in paragraph (k) of this AD. 

(j) Post-Repair Inspections 

The post-repair inspections, specified in 

tables 4, 5, and 6 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1325, dated December 3, 

2013, are not required by this AD. 

Note 1 to paragraph (j) of this AD: The 

damage tolerance inspections specified in 

tables 4, 5, and 6 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1325, dated December 3, 

2013, may be used in support of compliance 

with Section 121.1109(c)(2) or 129.109(b)(2) 

of the Federal Aviation Regulations (14 CFR 

121.1109(c)(2) or 14 CFR 129.109(b)(2)). The 

corresponding actions specified in the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1325, dated 

December 3, 2013, are not required by this 

AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in 

paragraph (l)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) 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. 

(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 the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that 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. 

(l) Related Information 

(1) For more information about this AD, 

contact Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: (425) 917–6450; fax: (425) 917–6590; 

email: alan.pohl@faa.gov. 

(2) 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 view this 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 May 15, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–12244 Filed 5–27–14; 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: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for all Airbus Model A318, A319, A320, 

and A321 series airplanes. The NPRM 

proposed to supersede AD 2011–14–06 

and proposed revising the maintenance 

program. The NPRM was prompted by 

the determination that more restrictive 

limitations are necessary. This action 

revises the NPRM by 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. 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 proposed AD by July 14, 2014. 

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Federal Register / Vol. 79, No. 102 / Wednesday, May 28, 2014 / Proposed Rules 30493 

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 view this 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 Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone (800) 647–5527) 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 

We proposed to amend 14 CFR part 

39 with an earlier NPRM for the 

specified products, which was 

published in the Federal Register on 

August 13, 2013 (78 FR 49213). The 

NPRM proposed to supersede AD 2011– 

14–06, Amendment 39–16741 (76 FR 

42024, July 18, 2011), to require actions 

intended to address the unsafe 

condition for Airbus Model A318, A319, 

A320, and A321 series airplanes. 

Since the NPRM (78 FR 49213, 

August 13, 2013) was issued, it has been 

determined that more restrictive limits 

are needed for damage tolerant 

airworthiness limitation items. This 

supplemental notice of proposed 

rulemaking (SNPRM) would require 

revising the maintenance program to 

incorporate new limitations. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0147, 

dated July 16, 2013 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

The airworthiness limitations for Airbus 

A320 family aeroplanes are currently 

included in Airbus A318/A319/A320/A321 

Airworthiness Limitations Section (ALS) 

document. The airworthiness limitations 

applicable to the Damage Tolerant 

Airworthiness Limitation Items (DT ALI) are 

currently given in Airbus ALS Part 2, which 

is approved by EASA. 

Previously, EASA issued AD 2010–0071R1 

[http://ad.easa.europa.eu/blob/easa_ad_

2010_0071_R1.pdf/AD_2010-0071R1_1] 

[associated with FAA AD 2011–14–06, 

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

2011)], which required the implementation of 

the DT ALI maintenance instructions as 

specified in Airbus A318/A319/A320/A321 

ALI Document ref. AI/SE–M4/95A.0252/96 

issue 10 and Airbus A319 Corporate Jet ALI 

Document ref. AI/SE–M2/95A.1038/99. 

The new Airbus A318/A319/A320/A321 

ALS Part 2 Revision 02, which includes also 

Airbus A319 Corporate Jet, introduces more 

restrictive DT ALI maintenance instructions. 

Failure to comply with these instructions 

could result in an unsafe condition. 

Application of new DT ALI tasks 531129– 

02–2 and 531129–02–3 introduces initial and 

repetitive inspections of the windshield 

central lower node continuity fittings, 

replacing the one time inspection for that 

subject, previously required by EASA AD 

2011–0231 [http://ad.easa.europa.eu/blob/

easa_ad_2011_0231.pdf] [associated with 

FAA AD 2013–13–03, Amendment 39–17491 

(78 FR 41280, July 10, 2013)]. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2010–0071R1 * * *, which are 

superseded, and requires compliance with all 

maintenance tasks as described in Airbus 

A318/A319/A320/A321 ALS part 2 at 

Revision 02. 

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. You 

may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating it in Docket No. FAA– 

2013–0692. 

Relevant Service Information 

Airbus has issued A318/A319/A320/

A321 ALS Part 2—Damage-Tolerant 

Airworthiness Limitation Items (DT 

ALI), Revision 02, dated May 28, 2013. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

Comments 

We gave the public the opportunity to 

comment on the NPRM (78 FR 49213, 

August 13, 2013). The following 

presents the comments received on the 

NPRM and the FAA’s response to each 

comment. 

Request To Incorporate Airbus A318/

A319/A320/A321 ALS Part 2, Revision 

02, Dated May 28, 2013, in Paragraph 

(m) of the NPRM (78 FR 49213, August 

13, 2013) 

American Airlines (AAL) requested 

that we either delete the phrase ‘‘doing 

the actions required by paragraph (m) of 

this AD terminates the requirements of 

this paragraph,’’ from paragraph (i) of 

the NPRM (78 FR 49213, August 13, 

2013), or incorporate Airbus A318/

A319/A320/A321 ALS Part 2—DamageTolerant Airworthiness Limitation Items 

(DT ALI), Revision 02, dated May 28, 

2013, in paragraph (m) of the NPRM. 

The commenter stated that paragraph 

(m) of the NPRM does not require 

incorporation of Airbus A318/A319/

A320/A321 ALS Part 2, Revision 02, 

dated May 28, 2013; therefore, 

incorporating paragraph (m) would not 

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30494 Federal Register / Vol. 79, No. 102 / Wednesday, May 28, 2014 / Proposed Rules 

fully terminate requirements of 

paragraph (i) of the NPRM. 

We agree to revise the final rule by 

adding the incorporation of Airbus 

A318/A319/A320/A321 ALS Part 2— 

Damage-Tolerant Airworthiness 

Limitation Items (DT ALI), Revision 02, 

dated May 28, 2013, to paragraph (p) of 

this SNPRM. 

Request To Incorporate Airbus A318/

A319/A320/A321 ALS Part 3— 

Certification Maintenance 

Requirements (CMR), Revision 01, 

Dated June 15, 2012; in Paragraph (m) 

of the NPRM (78 FR 49213, August 13, 

2013) 

AAL requested that we incorporate 

Airbus ALS Part 3—CMR, Revision 01, 

dated June 15, 2012; in paragraph (m) of 

the NPRM (78 FR 49213, August 13, 

2013). 

We acknowledge that the latest 

approved CMR has been released; 

however, we disagree to revise this 

SNPRM. EASA has issued a separate AD 

2013–0148, dated July 16, 2013 to 

require Airbus ALS Part 3—CMR, 

Revision 01, dated June 15, 2012. 

Therefore, we are considering separate 

rulemaking for mandating Airbus ALS 

Part 3—CMR, Revision 01, dated June 

15, 2012. No change has been made to 

this SNPRM in this regard. 

Request To Incorporate Airbus A318/

A319/A320/A321 ALS Part 4—Ageing 

Systems Maintenance (ASM), Revision 

01, Dated June 15, 2012 in Paragraph 

(m) of the NPRM (78 FR 49213, August 

13, 2013) 

Airbus and AAL requested that we 

revise paragraph (m) of the NPRM (78 

FR 49213, August 13, 2013) to 

incorporate Airbus A318/A319/A320/

A321 ALS Part 4—ASM, Revision 01, 

dated June 15, 2012. Airbus stated that 

the NPRM mentions Airbus A318/A319/ 

A320/A321 ALS Part 4—ASM, dated 

January 8, 2008; however, Airbus A318/ 

A319/A320/A321 ALS Part 4—ASM, 

Revision 01, dated June 15, 2012, 

introduces the extended service goal 1 

(ESG1) exercise which allows continued 

operation of the A320–200 systems postmodification 39020 at a different 

compliance time. 

We acknowledge that the latest 

approved ALS Part 4 has been released; 

however, we disagree to revise this 

SNPRM. EASA has issued EASA AD 

2013–0146, dated July 16, 2013 to 

require Airbus A318/A319/A320/A321 

ALS Part 4—ASM, Revision 01, dated 

June 15, 2012. Therefore, we might 

consider separate rulemaking for 

mandating Airbus A318/A319/A320/

A321 ALS Part 4—ASM, Revision 01, 

dated June 15, 2012. No change has 

been made to this SNPRM in this regard. 

Retained Paragraph of AD 2011–14–06, 

Amendment 39–16741 (76 FR 42024, 

July 18, 2011) 

The NPRM (78 FR 49213, August 13, 

2013) did not retain paragraph (h) of AD 

2011–14–06, Amendment 39–16741 (76 

FR 42024, July 18, 2011). We have 

retained that paragraph as paragraph (h) 

of this SNPRM and have re-designated 

the subsequent paragraphs accordingly. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

The MCAI specifies that if there are 

findings from the ALS inspection tasks, 

corrective actions must be accomplished 

in accordance with Airbus maintenance 

documentation. However, this proposed 

AD does not include that requirement. 

Operators of U.S.-registered airplanes 

are required by general airworthiness 

and operational regulations to perform 

maintenance using methods that are 

acceptable to the FAA. We consider 

those methods to be adequate to address 

any corrective actions necessitated by 

the findings of ALS inspections required 

by this proposed AD. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, 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. 

Certain changes described above 

expand the scope of the NPRM (78 FR 

49213, August 13, 2013). As a result, we 

have determined that it is necessary to 

reopen the comment period to provide 

additional opportunity for the public to 

comment on this proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 851 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD. 

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 

required actions is $85 per product. 

We also estimate that it would take 

about 1 work-hour per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this 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 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. 

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, 

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Federal Register / Vol. 79, No. 102 / Wednesday, May 28, 2014 / Proposed Rules 30495 

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. Amend § 39.13 by removing 

Airworthiness Directive (AD) 2011–14– 

06, Amendment 39–16741 (76 FR 

42024, July 18, 2011) and by 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 July 14, 

2014. 

(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 

Comply with this AD within the 

compliance times specified, unless already 

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 

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 (i) of this AD. Doing the actions 

required by paragraph (n) of this AD 

terminates the requirements of this 

paragraph. 

(h) Retained Revision to ALS To Incorporate 

Damage Tolerant ALIs 

This paragraph restates certain provisions 

of paragraph (h) 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; except Model A319 airplanes 

on which Airbus Modifications 28238, 

28162, and 28342 have been incorporated in 

production: Within 14 days 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 

Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 7, dated 

December 2005 (approved by the EASA on 

February 7, 2006); Issue 08, dated March 

2006 (approved by the EASA on January 4, 

2007); or Issue 09, dated November 2006 

(approved by the EASA on May 21, 2007). 

Accomplish the actions 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; at the times specified 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; as applicable; except as provided by 

paragraph (i) of this AD. Doing the actions 

required by paragraph (j) of this AD 

terminates the requirements of this 

paragraph. Doing the actions required by 

paragraph (n) of this AD terminates the 

requirements of this paragraph. 

(i) 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. Accomplishing 

the actions required by paragraph (n) of this 

AD terminates the requirements of this 

paragraph. 

(j) 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 (k) of 

this AD. Doing the actions required by this 

paragraph terminates the requirements of 

paragraph (h) of this AD. Accomplishing the 

actions required by paragraph (n) of this AD 

terminates the requirements of this 

paragraph. 

(k) 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 

(k) 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 (k) of this AD: The initial 

compliance time for doing the tasks is 

specified in table 1 to paragraph (k) of this 

AD. Accomplishing the actions specified in 

paragraph (n) of this AD terminates the 

requirements of this paragraph. 

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30496 Federal Register / Vol. 79, No. 102 / Wednesday, May 28, 2014 / Proposed Rules 

TABLE 1—TO PARAGRAPH (K) 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)). 

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)). 

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Federal Register / Vol. 79, No. 102 / Wednesday, May 28, 2014 / Proposed Rules 30497 

TABLE 1—TO PARAGRAPH (K) OF THIS AD—COMPLIANCE TIMES FOR TASKS—Continued 

Task Applicability 

(as specified in 

the applicability 

column of the task) 

Compliance time, whichever occurs later 

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 (k) 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. 

(l) Retained Limitation: No Alternative Life 

Limits, Inspections, or Inspection Intervals 

After Accomplishment of the Actions 

Specified in Paragraphs (g) and (h) 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 paragraphs (g) and (h) 

of this AD have been accomplished, no 

alternative life limits, inspections, or 

inspection intervals may be used, except as 

provided by paragraphs (i) and (m) of this 

AD, and except as required by paragraphs (j) 

and (n) of this AD. 

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30498 Federal Register / Vol. 79, No. 102 / Wednesday, May 28, 2014 / Proposed Rules 

(m) 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 (j) of this AD have been 

accomplished, no alternative life limits, 

inspections, or inspection intervals may be 

used, except as required by paragraph (n) of 

this AD. 

(n) New Maintenance or Inspection Program 

Revision 

Within 30 days after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, to incorporate the 

Airworthiness Limitation Items specified in 

paragraphs (n)(1), (n)(2), and (n)(3) of this 

AD. The initial compliance time for the 

accomplishing the actions is at the applicable 

time specified in Airworthiness Limitation 

Items specified in paragraphs (n)(1), (n)(2), 

and (n)(3) of this AD; or within 4 months 

after the effective date of this AD; whichever 

occurs later. Doing these actions terminates 

the requirements of paragraphs (g), (h), (i), (j), 

and (k) of this AD. 

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

Part 1—Safe Life Airworthiness Limitation 

Items, Revision 02, dated May 13, 2011. 

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

Part 2—Damage-Tolerant Airworthiness 

Limitation Items (DT ALI), Revision 02, dated 

May 28, 2013. 

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

Part 4—Ageing Systems Maintenance, dated 

January 8, 2008. 

(o) New Limitation: No Alternative Actions, 

Intervals, and/or Critical Design 

Configuration Control Limitations (CDCCLs) 

After accomplishing the revision required 

by paragraph (n) of this AD, no alternative 

actions (e.g., inspections), intervals, and/or 

CDCCLs may be used unless the actions, 

intervals, and/or CDCCLs are approved as an 

alternative method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (p)(1) of this AD. 

(p) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 for 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, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or the DAH with a State 

of Design Authority’s design organization 

approval). You are required to ensure the 

product is airworthy before it is returned to 

service. 

(q) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2012–0008, dated 

January 16, 2012; and 2013–0147, dated July 

16, 2013; for related information. This MCAI 

may be found in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating it in Docket No. 

FAA–2013–0692. 

(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.airworth-eas@

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

You may view this 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 May 15, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–12251 Filed 5–27–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0285; Directorate 

Identifier 2014–NM–035–AD] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc. Air Data Pressure 

Transducers 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Proposed rule; rescission. 

SUMMARY: We propose to rescind 

airworthiness directive (AD) 2012–26– 

15, which applies to certain Honeywell 

International Inc. air data pressure 

transducers as installed on various 

aircraft. AD 2012–26–15 requires doing 

various tests or checks of equipment 

having certain air data pressure 

transducers, removing equipment if 

necessary, and reporting the results of 

the tests or checks. As an option to the 

tests or checks, AD 2012–26–15 allows 

removal of affected equipment having 

certain air data pressure transducers. 

We issued AD 2012–26–15 to detect and 

correct inaccuracies of the pressure 

sensors, which could result in altitude, 

computed airspeed, true airspeed, and 

Mach computation errors. AD 2012–26– 

15 reported that these errors could 

reduce the ability of the flightcrew to 

maintain the safe flight of the aircraft 

and could result in consequent loss of 

control of the aircraft. Since we issued 

AD 2012–26–15, we have received new 

data indicating that the safety risk is 

lower than originally estimated. 

DATES: We must receive comments on 

this proposed AD by July 14, 2014. 

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: Deliver to the Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For Honeywell service information 

identified in this AD, contact Honeywell 

Aerospace, Technical Publications and 

Distribution, M/S 2101–201, P.O. Box 

52170, Phoenix, AZ 85072–2170; 

telephone 602–365–5535; fax 602–365– 

5577; Internet http://

www.honeywell.com. 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 by searching for 

and locating Docket No. FAA–2014– 

0285; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

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