Federal Register / Vol. 79, No. 187 / Friday, September 26, 2014 / Rules and Regulations 57753 

envelope, which could result in loss of 

control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement of Fuse Pins and Access 

Cover Assemblies 

Within 48 months after the effective date 

of this AD: Replace the fuse pins for the 

outboard aft upper spar and the access cover 

assemblies on struts Nos. 1 and 4, with new 

fuse pins and access cover assemblies, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–54A2238, dated January 31, 2014. 

(h) 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 (i) 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. 

(4) If the service information contains steps 

that are labeled as RC (Required for 

Compliance), those steps must be done to 

comply with this AD; any steps that are not 

labeled as RC are recommended. Those steps 

that are not labeled as RC may be deviated 

from, done as part of other actions, or done 

using accepted methods different from those 

identified in the specified service 

information without obtaining approval of an 

AMOC, provided the steps labeled as RC can 

be done and the airplane can be put back in 

a serviceable condition. Any substitutions or 

changes to steps labeled as RC require 

approval of an AMOC. 

(i) Related Information 

For more information about this AD, 

contact Narinder Luthra, Aerospace Engineer, 

Airframe Branch, ANM–120S, Seattle 

Aircraft Certification Office (ACO), FAA, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6513; fax: 425–917– 

6590; email: narinder.luthra@faa.gov. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 747– 

54A2238, dated January 31, 2014. 

(ii) Reserved. 

(3) 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. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA 98057–3356. 

For information on the availability of this 

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

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 12, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–22468 Filed 9–25–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0291; Directorate 

Identifier 2013–NM–137–AD; Amendment 

39–17972; AD 2014–19–04] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2004–03– 

19, which applies to certain Airbus 

Model A320–111, –211 and –231 series 

airplanes. AD 2004–03–19 required 

repetitive inspections for cracking in the 

transition and pick-up angles in the 

lower part of the center fuselage area, 

and corrective action if necessary. AD 

2004–03–19 also provided for an 

optional terminating modification for 

the repetitive inspection requirements. 

This new AD requires accomplishing 

the modification by installing washers 

between the transition pick-up angle 

and the pin nuts, and doing related 

investigative and corrective actions if 

necessary. This new AD also adds 

airplanes to the applicability of AD 

2004–03–19. This AD was prompted by 

a determination that the optional 

terminating modification must be 

required in order to address the unsafe 

condition. We are issuing this AD to 

prevent fatigue cracking in the 

transition and pick-up angles of the 

lower part of the center fuselage, which 

could result in reduced structural 

integrity of the wing-fuselage support 

and fuselage pressure vessel. 

DATES: This AD becomes effective 

October 31, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 15, 2004 (69 FR 5922, 

February 9, 2004). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0291; or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

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 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. 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2004–03–19, 

Amendment 39–13463 (69 FR 5922, 

February 9, 2004). AD 2004–03–19 

applied to certain Airbus Model A320– 

111, –211, and –231 series airplanes. 

The NPRM published in the Federal 

Register on May 30, 2014 (79 FR 31057). 

The NPRM was prompted by a 

determination that the optional 

terminating modification must be 


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required in order to address the unsafe 

condition. The NPRM proposed to 

require repetitive inspections for 

cracking in the transition and pick-up 

angles in the lower part of the center 

fuselage area, and corrective action if 

necessary. The NPRM also proposed to 

require a terminating modification for 

the repetitive inspection requirements. 

The NPRM also proposed to add 

airplanes to the applicability. We are 

issuing this AD to prevent fatigue 

cracking in the transition and pick-up 

angles of the lower part of the center 

fuselage, which could result in reduced 

structural integrity of the wing-fuselage 

support and fuselage pressure vessel. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0137, 

dated July 9, 2013 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Model A320–111, 

–211, and –231 series airplanes. The 

MCAI states: 

During the A320 fatigue test campaign, it 

has been determined that fatigue damage 

could appear on the transition and pick-up 

angle between Frame (FR) 35 and FR36. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

To address this potential unsafe condition, 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France issued AD 2002–183 [related 

to FAA AD 2004–03–19, Amendment 39– 

13463 (69 FR 5922, February 9, 2004)], to 

require repetitive inspections of the center 

fuselage pick-up angle between FR35 and 

FR36, below stringer 30, left hand (LH) and 

right hand (RH) sides, and, depending on 

findings, accomplishment of applicable 

corrective action(s). 

Since that [DGAC] AD [2002–183] was 

issued, a modification was developed, which 

has been published through Airbus Service 

Bulletin (SB) A320–53–1027 for in-service 

application, introducing additional washers 

below the riveting, which constitutes 

terminating action for the repetitive 

inspections. 

For the reasons described above, this 

[EASA] AD retains the requirements of DGAC 

France AD 2002–183, which is superseded, 

and requires modification of the transition 

and pick-up angle between FR35 and FR36. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0291- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 31057, May 30, 2014) or on the 

determination of the cost to the public. 

‘‘Contacting the Manufacturer’’ 

Paragraph in this AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 

FAA develops an AD based on a foreign 

authority’s AD. 

The MCAI or referenced service 

information in an FAA AD often directs 

the owner/operator to contact the 

manufacturer for corrective actions, 

such as a repair. Briefly, the Airworthy 

Product paragraph allowed owners/

operators to use corrective actions 

provided by the manufacturer if those 

actions were FAA-approved. In 

addition, the paragraph stated that any 

actions approved by the State of Design 

Authority (or its delegated agent) are 

considered to be FAA-approved. 

In the NPRM (79 FR 11016, February 

27, 2014), we proposed to prevent the 

use of repairs that were not specifically 

developed to correct the unsafe 

condition, by requiring that the repair 

approval provided by the State of 

Design Authority or its delegated agent 

specifically refer to this FAA AD. This 

change was intended to clarify the 

method of compliance and to provide 

operators with better visibility of repairs 

that are specifically developed and 

approved to correct the unsafe 

condition. In addition, for certain new 

requirements, we proposed to change 

the phrase ‘‘its delegated agent’’ to 

include a design approval holder (DAH) 

with State of Design Authority design 

organization approval (DOA), as 

applicable, to refer to a DAH authorized 

to approve required repairs for the 

proposed AD. 

No comments were provided to the 

NPRM (79 FR 11016, February 27, 2014) 

about these proposed changes. However, 

a comment was provided for an NPRM 

having Directorate Identifier 2012–NM– 

101–AD (78 FR 78285, December 26, 

2013). The commenter stated the 

following: ‘‘The proposed wording, 

being specific to repairs, eliminates the 

interpretation that Airbus messages are 

acceptable for approving minor 

deviations (corrective actions) needed 

during accomplishment of an AD 

mandated Airbus service bulletin.’’ 

This comment has made the FAA 

aware that some operators have 

misunderstood or misinterpreted the 

Airworthy Product paragraph to allow 

the owner/operator to use messages 

provided by the manufacturer as 

approval of deviations during the 

accomplishment of an AD-mandated 

action. The Airworthy Product 

paragraph does not approve messages or 

other information provided by the 

manufacturer for deviations to the 

requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed the 

paragraph and retitled it ‘‘Contacting the 

Manufacturer.’’ This paragraph now 

clarifies that for any requirement in this 

AD to obtain corrective actions from a 

manufacturer, the actions must be 

accomplished using a method approved 

by the FAA, the European Aviation 

Safety Agency (EASA), or Airbus’s 

EASA Design Organization Approval 

(DOA). 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DOA, the approval must include 

the DOA-authorized signature. The DOA 

signature indicates that the data and 

information contained in the document 

are EASA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that do not contain the 

DOA-authorized signature approval are 

not EASA-approved, unless EASA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

Other commenters to the NPRM 

having Directorate Identifier 2012–NM– 

101–AD (78 FR 78285, December 26, 

2013) pointed out that in many cases the 

foreign manufacturer’s service bulletin 

and the foreign authority’s MCAI might 


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Federal Register / Vol. 79, No. 187 / Friday, September 26, 2014 / Rules and Regulations 57755 

have been issued some time before the 

FAA AD. Therefore, the DOA might 

have provided U.S. operators with an 

approved repair, developed with full 

awareness of the unsafe condition, 

before the FAA AD is issued. Under 

these circumstances, to comply with the 

FAA AD, the operator would be 

required to go back to the 

manufacturer’s DOA and obtain a new 

approval document, adding time and 

expense to the compliance process with 

no safety benefit. 

Based on these comments, we 

removed the requirement that the DAHprovided repair specifically refer to this 

AD. Before adopting such a 

requirement, the FAA will coordinate 

with affected DAHs and verify they are 

prepared to implement means to ensure 

that their repair approvals consider the 

unsafe condition addressed in this AD. 

Any such requirements will be adopted 

through the normal AD rulemaking 

process, including notice-and-comment 

procedures, when appropriate. 

We also have decided not to include 

a generic reference to either the 

‘‘delegated agent’’ or ‘‘DAH with State of 

Design Authority design organization 

approval,’’ but instead we have 

provided the specific delegation 

approval granted by EASA for the DAH. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

31057, May 30, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 31057, 

May 30, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 482 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Inspection [retained action 

from AD 2004–03–19, 

Amendment 39–13463 (69 

FR 5922, February 9, 2004)].

9 work-hours × $85 per hour = 

$765 per inspection cycle.

$0 $765 per inspection cycle ....... $18,360 per inspection cycle 

(24 airplanes). 

Inspection for Model A320–212 

airplanes [new action].

9 work-hours × $85 per hour = 

$765 per inspection cycle.

$0 $765 per inspection cycle ....... $32,130 per inspection cycle 

(42 airplanes). 

Terminating modification [new 

action].

28 work-hours × $85 per hour 

= $2,380.

$1,837 $4,217 ..................................... $2,032,594. 

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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

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 this AD: 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0291; 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 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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) 

2004–03–19, Amendment 39–13463 (69 

FR 5922, February 9, 2004), and adding 

the following new AD: 

2014–19–04 Airbus: Amendment 39–17972. 

Docket No. FAA–2014–0291; Directorate 

Identifier 2013–NM–137–AD. 

(a) Effective Date 

This AD becomes effective October 31, 

2014. 


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(b) Affected ADs 

This AD replaces AD 2004–03–19, 

Amendment 39–13463 (69 FR 5922, February 

9, 2004). 

(c) Applicability 

This AD applies to Airbus Model A320– 

111, –211, –212, and –231 airplanes, 

certificated in any category, all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by the 

determination that the modification must be 

accomplished in order to address the unsafe 

condition. We are issuing this AD to prevent 

fatigue cracking in the transition and pick-up 

angles of the lower part of the center 

fuselage, which could result in reduced 

structural integrity of the wing-fuselage 

support and fuselage pressure vessel. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Detailed and Rotating Probe 

Inspections 

This paragraph restates the requirements of 

paragraph (b) of AD 2004–03–19, 

Amendment 39–13463 (69 FR 5922, February 

9, 2004). For Model A320–111, –211, and 

–231 airplanes on which the modification 

specified in AD 98–12–18, Amendment 39– 

10573 (63 FR 31345, June 9, 1998), has not 

been done: Do the applicable inspections 

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

this AD, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1028, Revision 01, 

dated February 12, 2002. 

(1) For airplanes on which the inspections 

required by AD 98–12–18, Amendment 39– 

10573 (63 FR 31345, June 9, 1998), have been 

done: Within 12,000 flight cycles after 

accomplishment of the last inspection 

required by AD 98–12–18, do a detailed 

inspection of the transition angle and a 

rotating probe inspection of the pick-up angle 

in the lower part of the center fuselage area 

for cracking. 

(2) For airplanes on which the inspections 

required by AD 98–12–18, Amendment 39– 

10573 (63 FR 31345, June 9, 1998), have not 

been done: At the later of the times specified 

in paragraphs (g)(2)(i) and (g)(2)(ii) of this 

AD, do a detailed inspection of the transition 

angle and a rotating probe inspection of the 

pick-up angle in the lower part of the center 

fuselage area for cracking. 

(i) Before the accumulation of 10,400 total 

flight cycles, or 24,600 total flight hours, 

whichever is first. 

(ii) Before the accumulation of 16,000 total 

flight cycles, or within 3,500 flight cycles 

after March 15, 2004 (the effective date of AD 

2004–03–19, Amendment 39–13463 (69 FR 

5922, February 9, 2004), whichever is first. 

(h) Retained Repetitive Inspections 

This paragraph restates the requirements of 

paragraph (c) of AD 2004–03–19, 

Amendment 39–13463 (69 FR 5922, February 

9, 2004). For Model A320–111, –211, and 

–231 airplanes: Repeat the detailed and 

rotating probe inspections specified in 

paragraphs (g)(1) and (g)(2) of this AD at 

intervals not to exceed 10,400 flight cycles or 

24,600 flight hours, whichever is first, until 

the modification specified in paragraph (m) 

of this AD has been done. 

(i) Retained Corrective Action for 

Paragraphs (g) and (h) of This AD 

This paragraph restates the requirements of 

paragraph (d) of AD 2004–03–19, 

Amendment 39–13463 (69 FR 5922, February 

9, 2004), with specific delegation approval 

language. For Model A320–111, –211, and 

–231 airplanes: If any cracking is found 

during any inspection required by paragraph 

(g) or (h) of this AD, prior to further flight, 

either repair the cracking per the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1028, Revision 01, 

dated February 12, 2002; or do the 

modification specified in paragraph (m) of 

this AD. Where Airbus Service Bulletin 

A320–53–1028, Revision 01, dated February 

12, 2002, specifies to contact the 

manufacturer for repair instructions, prior to 

further flight, repair the cracking in 

accordance with a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA); or 

Airbus’s EASA Design Organization 

Approval (DOA); or the Direction Ge ́ne ́rale 

de l’Aviation Civile (or its delegated agent). 

If the cracking is repaired, repeat the 

inspections as required by paragraph (h) of 

this AD. 

(j) New Detailed and Rotating Probe 

Inspections for Model A320–212 Airplanes 

For Model A320–212 airplanes on which 

the modification specified in Airbus Service 

Bulletin A320–53–1027 has not been done as 

of the effective date of this AD: Do the 

applicable inspections specified in paragraph 

(j)(1) or (j)(2) of this AD, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1028, Revision 01, 

dated February 12, 2002. 

(1) For airplanes on which the inspections 

specified in Airbus Service Bulletin A320– 

53–1028 have been done as of the effective 

date of this AD: At the later of the times 

specified in paragraphs (j)(1)(i) and (j)(1)(ii) 

of this AD, do a detailed inspection of the 

transition angle and a rotating probe 

inspection of the pick-up angle in the lower 

part of the center fuselage area for cracking. 

(i) Within 10,400 flight cycles or 24,600 

flight hours, whichever occurs first after 

accomplishing the most recent inspection 

specified in Airbus Service Bulletin A320– 

53–1028. 

(ii) Within 90 days after the effective date 

of this AD. 

(2) For airplanes on which the inspections 

specified in Airbus Service Bulletin A320– 

53–1028 have not been done as of the 

effective date of this AD: At the later of the 

times specified in paragraphs (j)(2)(i) and 

(j)(2)(ii) of this AD, do a detailed inspection 

of the transition angle and a rotating probe 

inspection of the pick-up angle in the lower 

part of the center fuselage area for cracking. 

(i) Before the accumulation of 10,400 total 

flight cycles, or 24,600 total flight hours, 

whichever occurs first. 

(ii) Within 90 days after the effective date 

of this AD. 

(k) New Repetitive Inspections for Model 

A320–212 Airplanes 

For Model A320–212 airplanes: Repeat the 

detailed and rotating probe inspections 

specified in paragraphs (j)(1) and (j)(2) of this 

AD at intervals not to exceed 10,400 flight 

cycles or 24,600 flight hours, whichever 

occurs first, until the modification specified 

in paragraph (m) of this AD has been done. 

(l) New Corrective Action for Model A320– 

212 Airplanes 

For Model A320–212 airplanes: If any 

cracking is found during any inspection 

required by paragraph (j) or (k) of this AD, 

before further flight, do the actions specified 

in either paragraph (l)(1) or (l)(2) of this AD. 

(1) Repair the crack in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1028, Revision 01, 

dated February 12, 2002, except where 

Airbus Service Bulletin A320–53–1028, 

Revision 01, dated February 12, 2002, 

specifies to contact the manufacturer, before 

further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the European Aviation 

Safety Agency (EASA); or Airbus’s EASA 

Design Organization Approval (DOA). After 

the cracking is repaired, repeat the 

inspections required by paragraph (k) of this 

AD. 

(2) Do the modification specified in 

paragraph (m) of this AD. 

(m) New Terminating Modification for All 

Airplanes 

For all airplanes: Before the accumulation 

of 40,000 flight cycles since first flight, or 

within 1,500 flight cycles after the effective 

date of this AD, whichever occurs later, but 

not exceeding 48,000 flight cycles since first 

flight, modify by doing rotating probe 

inspections for cracking of certain fastener 

holes, replacing transition angles if any 

cracking is found in the transition angles, 

repairing if any pick-up angles cracking is 

found, and installing washers between the 

transition pick-up angle and the pin nuts; in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1027, Revision 03, dated February 12, 

2002, except where Airbus Service Bulletin 

A320–53–1027, Revision 03, dated February 

12, 2001, specifies to contact Airbus, before 

further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the European Aviation 

Safety Agency (EASA); or Airbus’s EASA 

Design Organization Approval (DOA). 

Accomplishment of this modification 

terminates the repetitive inspections required 

by paragraphs (h) and (k) of this AD. 

(n) Terminating Modification 

For airplanes on which Airbus 

Modification 21202 has been embodied in 

production: No actions are required by this 

AD. 


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Federal Register / Vol. 79, No. 187 / Friday, September 26, 2014 / Rules and Regulations 57757 

(o) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraph (j) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–53–1028, dated March 1, 

1994, which was incorporated by reference in 

AD 98–12–18, Amendment 39–10573 (63 FR 

31345, June 9, 1998). 

(2) This paragraph provides credit for the 

action specified in paragraph (m) of this AD, 

if that action was performed before the 

effective date of this AD using the service 

information specified in paragraph (o)(2)(i), 

(o)(2)(ii), or (o)(2)(iii) of this AD, which is not 

incorporated by reference in this AD. 

(i) Airbus Service Bulletin A320–53–1027, 

dated March 1, 1994. 

(ii) Airbus Service Bulletin A320–53–1027, 

Revision 1, dated September 5, 1994. 

(iii) Airbus Service Bulletin A320–53– 

1027, Revision 2, dated June 8, 1995 (which 

was incorporated by reference in AD 98–12– 

18, Amendment 39–10573 (63 FR 31345, 

June 9, 1998)). 

(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. 

(i) 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. 

(ii) AMOCs approved previously in 

accordance with AD 2004–03–19, 

Amendment 39–13463 (69 FR 5922, February 

9, 2004), are approved as AMOCs for the 

corresponding provisions of this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(q) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0137, dated July 9, 2013, for 

related information. You may examine the 

MCAI in the AD docket on the Internet at 

http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0291-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD is available at the addresses specified 

in paragraphs (r)(4) and (r)(5) of this AD. 

(r) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on March 15, 2004 (69 FR 

5922, February 9, 2004). 

(i) Airbus Service Bulletin A320–53–1027, 

Revision 03, dated February 12, 2002. 

(ii) Airbus Service Bulletin A320–53–1028, 

Revision 01, dated February 12, 2002. 

(4) 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. 

(5) You may view this 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. 

(6) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 12, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–22469 Filed 9–25–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2014–0713; Airspace 

Docket No. 14–AWA–1] 

RIN 2120–AA66 

Amendment of Class B Airspace; 

Washington Tri-Area, DC 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; technical 

amendment. 

SUMMARY: This action amends the 

description of Area D of the Washington 

Tri-Area Class B airspace area to include 

exclusion of restricted area R–4001C 

from the Class B airspace when the 

restricted area is active. The remainder 

of the Class B description is not affected 

by this change. 

DATES: Effective date: 0901 UTC 

September 26, 2014. The Director of the 

Federal Register approves this 

incorporation by reference action under 

1 CFR part 51, subject to the annual 

revision of FAA Order 7400.9 and 

publication of conforming amendments. 

ADDRESSES: FAA Order 7400.9Y, 

Airspace Designations and Reporting 

Points, and subsequent amendments can 

be viewed online at http://www.faa.gov/ 

air_traffic/publications/. The Order is 

also available for inspection at the 

National Archives and Records 

Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030 or 

go to http://archives.gov/federal_

register/code_of_federal-regulations/ibr_

locations.html. 

FAA Order 7400.9, Airspace 

Designations and Reporting Points, is 

published yearly and effective on 

September 15. For further information, 

you can contact the Airspace Policy and 

Regulations Group, Federal Aviation 

Administration, 800 Independence 

Avenue SW., Washington, DC 20591; 

telephone: 202–267–8783. 

FOR FURTHER INFORMATION CONTACT: Paul 

Gallant, Airspace Policy and 

Regulations Group, Office of Airspace 

Services, Federal Aviation 

Administration, 800 Independence 

Avenue SW., Washington, DC 20591; 

telephone: (202) 267–8783. 

SUPPLEMENTARY INFORMATION: 

Background 

On May 23, 2014, the FAA published 

a final rule establishing restricted area 

R–4001C at Aberdeen Proving Ground, 

MD (79 FR 29661). R–4001C was formed 

by further subdividing small sections of 

existing restricted areas R–4001A and 

R–4001B that currently extend into Area 

D of the Washington, DC, Tri-Area Class 

B airspace area. The description of Area 

D excludes the airspace in restricted 

areas R–4001A and B from the Class B 

airspace. This change simply updates 

that description to add R–4001C (which 

is imbedded within R–4001A and R– 

4001B) to the exclusionary language. 

Aeronautical charts have been updated 

to reflect this information. 

The Rule 

The FAA is amending Title 14 Code 

of Federal Regulations (14 CFR) part 71 

to update the description of Area D in 

the Washington Tri-Area Class B 


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