Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations 78705 

Note 1 to paragraph (g) of this AD: 

Information on additional procedures for the 

modification can be found in Notes 4, 5, and 

6, as applicable, of paragraph 1.D., 

‘‘Compliance’’ of McDonnell Douglas DC–9 

Alert Service Bulletin A53–144, Revision 2, 

dated February 23, 1984. 

(h) Exception to Service Information 

If any crack is found during any inspection 

required by this AD, and McDonnell Douglas 

DC–9 Alert Service Bulletin A53–144, 

Revision 2, dated February 23, 1984, 

specifies to contact the manufacturer for 

appropriate action: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

(i) No Reporting Required 

Sheet 1 of Service Sketch 3109, and Sheet 

7 of Service Sketch 3110B of McDonnell 

Douglas DC–9 Alert Service Bulletin A53– 

144, Revision 2, dated February 23, 1984; 

specify reporting the details of any cracks 

found; however, this AD does not require 

reporting. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 Los Angeles ACO, send 

it to the attention of the person identified in 

paragraph (k) of this AD. 

(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 

Structures Authorized Representative for the 

Boeing Commercial Airplanes Delegation 

Option Authorization Organization who has 

been authorized by the Manager, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and 14 

CFR 25.571, Amendment 45, and the 

approval must specifically refer to this AD. 

(k) Related Information 

For more information about this AD, 

contact Eric Schrieber, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 3960 

Paramount Boulevard, Lakewood, CA 90712– 

4137; phone: (562) 627–5348; fax: (562) 627– 

5210; email: eric.schrieber@faa.gov. 

(l) 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) McDonnell Douglas DC–9 Alert Service 

Bulletin A53–144, Revision 2, dated February 

23, 1984. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, 3855 Lakewood Boulevard, MC 

D800–0019, Long Beach, CA 90846–0001; 

telephone 206–544–5000, extension 2; fax 

206–766–5683; Internet https://

www.myboeingfleet.com. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, Washington. 

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 

December 10, 2013. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–30779 Filed 12–26–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0416; Directorate 

Identifier 2012–NM–144–AD; Amendment 

39–17707; AD 2013–25–11] 

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) 2010–24– 

07 for all Airbus Model A318 series 

airplanes, Model A319 series airplanes, 

Model A320 series airplanes, and Model 

A321 series airplanes. AD 2010–24–07 

required repetitive inspections of the 

80VU rack lower lateral fittings for 

damage, repetitive inspections of the 

80VU rack lower central support for 

cracking, and corrective action if 

necessary. AD 2010–24–07 also 

specified optional terminating action for 

the repetitive inspections. This new AD 

reduces the inspection compliance time, 

adds an inspection of the upper fittings 

and shelves of the 80VU rack, and adds 

airplanes to the applicability. This AD 

was prompted by reports of worn lower 

lateral fittings of the 80VU rack. We are 

issuing this AD to detect and correct 

damage or cracking of the 80VU fittings 

and supports, which could lead to 

possible disconnection of the cable 

harnesses to one or more computers, 

and if occurring during a critical phase 

of flight, could result in reduced control 

of the airplane. 

DATES: This AD becomes effective 

January 31, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 31, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of January 11, 2011 (75 FR 

75878, December 7, 2010). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0416; or in 

person at the U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

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 by adding an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on May 14, 2013 (78 FR 28152), 

and proposed to supersede AD 2010– 

24–07, Amendment 39–16526 (75 FR 

75878, December 7, 2010). The NPRM 

proposed to correct an unsafe condition 

for the specified products. The 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0134, 

dated July 18, 2012 (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: 

Damage to the lower lateral fittings of the 

80VU rack, typically elongated holes, 

migrated bushes, and/or missing bolts have 

been reported on in-service aeroplanes. The 

80VU rack contains computers for flight 

controls, communication and radionavigation. In addition, damage to the lower 


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central support fitting (including cracking) 

has been reported. 

Failure of the 80VU fittings, in 

combination with a high load factor or strong 

vibration, could lead to failure of the rack 

structure and/or computers or rupture/

disconnection of the cable harnesses to one 

or more computers located in the 80VU rack. 

Even though the computer functions are 

duplicated across other racks, multiple 

system failures or (partial) disconnection of 

systems, if occurring during a critical phase 

of flight, could result in reduced control of 

the aeroplane. 

To address this potential unsafe condition, 

EASA issued AD 2007–0276 to require 

repetitive inspections of the lower lateral 

80VU fittings and the lower central 80VU 

support and, depending on findings, the 

accomplishment of corrective actions. 

[EASA] AD 2007–0276 was revised to 

introduce a reinforced lower central support 

as an optional terminating action for the 

repetitive inspections. 

Since issuance of EASA AD 2007–0276R1 

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

2007_0276_R1_superseded.pdf/AD_2007– 

0276R1_1] [which corresponds to FAA AD 

2010–24–07, Amendment 39–16526 (75 FR 

75878, December 7, 2010)], and prompted by 

in-service experience, the previous 

inspection programme has been reassessed. 

New conditions of inspection for a new 

finding on the lower central fitting 

attachment (crack in the lower of the lateral 

flanges), and a new visual inspection of the 

upper fittings and shelves of the 80VU are 

introduced by this inspection programme. In 

addition, the replacement of a cracked lateral 

fitting or central support with a lateral fitting 

or central support having the same part 

number is no longer preferable as corrective 

action. Instead, the installation of the 

reinforced lower central support is now 

defined as optional terminating action for the 

repetitive inspections required by this 

[EASA] AD. 

For the reasons described above, this 

[EASA] AD supersedes EASA AD 2007– 

0276R1 and requires implementation of an 

amended inspection programme with a 

reduced inspection threshold. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0416- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

Request to Change Compliance Time 

United Airlines (UAL) requested that 

we change the compliance time for the 

corrective actions specified in 

paragraphs (m), (o), and (p) of the NPRM 

(78 FR 28152, May 14, 2013) from 

‘‘before further flight’’ to the following. 

• Within one deferral flight cycle, or 

the applicable time given in Paragraph 

E.(2), ‘‘Accomplish Timescale,’’ of 

Airbus Mandatory Service Bulletin 

A320–25A1555, Revision 03, dated 

February 28, 2012, whichever is later. 

• Within 50 flight cycles or at the 

applicable time given in Paragraph E.(2), 

‘‘Accomplish Timescale,’’ of Airbus 

Mandatory Service Bulletin A320– 

25A1555, Revision 03, dated February 

28, 2012, whichever is later. 

UAL stated that the first option would 

give operators a chance to fly a ferry 

flight to a more equipped resourced base 

maintenance station, and that the 

second option would give operators an 

option to create a short-term deferred 

item to plan for its accomplishment by 

creating a formal maintenance task with 

planned allocated resources. 

UAL stated that due to the inspection 

threshold and repeat interval of 500 

flight cycles, it is concerned that the 

inspection will take place at mainly 

airplane line maintenance stations, with 

significant exposure to possible damage 

conditions that require correction before 

further flight. UAL commented that 

typical airplane line stations might not 

have the resources, materials, and 

equipment to perform this type of 

modification, repair, and access. UAL 

also stated that certain corrective 

actions require approximately 57 workhours, which would lead to lengthy outof-service time and costs to the airline. 

We do not agree with UAL’s request 

to extend the compliance time. The 

FAA AD provides a provision for 

operators to apply for a special flight 

permit in accordance with 14 CFR 

21.197, which allows operators to fly 

airplanes to a base where repairs, 

alterations, or maintenance can be 

performed. These airplanes may not 

fully meet applicable airworthiness 

requirements, but are capable of safe 

flight for reasons stated in 14 CFR 

21.197. In developing an appropriate 

compliance time for this final rule, we 

considered the urgency associated with 

the subject unsafe condition, the 

availability of required parts, and the 

practical aspect of accomplishing the 

required corrective actions. Some safety 

issues are more time-sensitive than 

others, so we consider the overall risk 

to the fleet, including the severity of the 

failure and the likelihood of the failure’s 

occurrence in establishing the 

compliance time in this final rule. The 

commenter has not provided sufficient 

substantiation for revising the corrective 

action compliance time for repairing 

certain damage conditions that will 

meet an acceptable level of safety to 

mitigate risk to the fleet. 

Under the provisions of paragraph (s) 

of this AD, we will consider requests for 

approval of an extension of the 

compliance time if sufficient data are 

submitted to substantiate that the new 

compliance time would provide an 

acceptable level of safety. We have not 

changed this final rule in this regard. 

Additional Changes to This AD 

We have revised paragraph (o)(1) of 

this final rule to include the option of 

contacting the EASA (or its delegated 

agent) for repair instructions. 

Paragraph (p) of the NPRM (78 FR 

28152, May 14, 2013) incorrectly 

referred to ‘‘paragraphs (m) and (o) of 

this AD’’ for certain special detailed 

inspections. Those special detailed 

inspections are specified in paragraphs 

(l) and (n) of this AD. We have revised 

paragraph (p) of this AD to refer to 

paragraphs (l) and (n) of this AD. 

Conclusion 

We reviewed the available data, 

including the comment received, 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 changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

28152, May 14, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 28152, 

May 14, 2013). 

Costs of Compliance 

We estimate that this AD affects about 

755 products of U.S. registry. 

The actions that are required by AD 

2010–24–07, Amendment 39–16526 (75 

FR 75878, December 7, 2010), and 

retained in this AD, take about 82 workhours per product, at an average labor 

rate of $85 per work hour. Required 

parts cost about $2,592 per product. 

Based on these figures, the estimated 

cost of the currently required actions is 

$9,562 per product. 

We estimate that it takes about 5 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Where the service information 

lists parts costs that are covered under 

warranty, we have assumed that there 

will be no charge for these parts. As we 

do not control warranty coverage for 

affected parties, some parties may incur 

costs higher than estimated here. Based 

on these figures, we estimate the cost of 

this AD on U.S. operators to be 

$320,875, or $425 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 189 work-hours and require parts 

costing $7,047, for a cost of $23,112 per 

product. Where the service information 

lists required parts costs that are 


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covered under warranty, we have 

assumed that there will be no charge for 

these parts. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. We have no way of 

determining the number of products 

that may need these actions. 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0416; 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 AD, the 

MCAI, 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) 

2010–24–07, Amendment 39–16526 (75 

FR 75878, December 7, 2010), and 

adding the following new AD: 

2013–25–11 Airbus: Amendment 39–17707. 

Docket No. FAA–2013–0416; Directorate 

Identifier 2012–NM–144–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective January 31, 2014. 

(b) Affected ADs 

This AD supersedes AD 2010–24–07, 

Amendment 39–16526 (75 FR 75878, 

December 7, 2010). 

(c) Applicability 

This AD applies to 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; all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/Furnishings; 

and Code 53, Fuselage. 

(e) Reason 

This AD was prompted by reports of worn 

lower lateral fittings of the 80VU rack. We are 

issuing this AD to detect and correct damage 

or cracking of the 80VU fittings and supports, 

which could lead to possible disconnection 

of the cable harnesses to one or more 

computers, and if occurring during a critical 

phase of flight, could result in reduced 

control 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 Repetitive Inspections of the 

80VU Rack Lower Lateral Fittings 

This paragraph restates the requirements of 

paragraph (g) of AD 2010–24–07, 

Amendment 39–16526 (75 FR 75878, 

December 7, 2010). Except for Model A318– 

121 and –122 airplanes, and except for 

airplanes on which Airbus Modification 

34804 has been embodied in production, or 

on which Airbus Service Bulletins A320–25– 

1557 and A320–53–1215 have been done in 

service, prior to the accumulation of 24,000 

total flight cycles, or within 500 flight cycles 

after January 11, 2011 (the effective date of 

AD 2010–24–07), whichever occurs later: Do 

a special detailed inspection of the 80VU 

rack lower lateral fittings for damage (e.g., 

broken fitting, missing bolts, migrated 

bushings, material burr, or rack in contact 

with the fitting) of the 80VU rack lower 

lateral fittings, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–25A1555, 

Revision 02, dated November 5, 2008. Repeat 

the inspection thereafter at the interval 

specified in paragraph (g)(1) or (g)(2) of this 

AD, as applicable. Modifying the 80VU lower 

lateral fittings, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–25–1557, Revision 02, 

dated November 5, 2008, terminates the 

inspection requirements of this paragraph. 

Doing the initial inspection specified in 

paragraph (l) of this AD terminates the 

requirements of this paragraph. 

(1) For airplanes on which the 80VU rack 

lower lateral fittings have not been replaced 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–25A1555, Revision 02, dated 

November 5, 2008: Repeat the inspection 

thereafter at intervals not to exceed 4,500 

flight cycles. 

(2) For airplanes on which the 80VU rack 

lower lateral fittings have been replaced in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–25A1555, Revision 02, dated 

November 5, 2008: Do the next inspection 

within 24,000 flight cycles after doing the 

replacement and repeat the inspection 

thereafter at intervals not to exceed 4,500 

flight cycles. 

(h) Retained Corrective Actions With 

Additional New Corrective Actions 

This paragraph restates the requirements of 

paragraph (h) of AD 2010–24–07, 

Amendment 39–16526 (75 FR 75878, 

December 7, 2010), with new corrective 

actions. If any damage is found during any 

inspection required by paragraph (g) of this 

AD, do all applicable corrective actions 

(inspection and/or repair), in accordance 

with the Accomplishment Instructions and 

timeframes in Airbus Mandatory Service 

Bulletin A320–25A1555, Revision 02, dated 

November 5, 2008; or in accordance with and 

at the time specified in paragraph (q) of this 

AD. As of the effective date of this AD, if any 


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damage is found, do all applicable corrective 

actions in accordance with and at the times 

specified in paragraph (q) of this AD. 

(i) Retained Repetitive Inspections of the 

80VU Rack Lower Central Support 

This paragraph restates the requirements of 

paragraph (i) of AD 2010–24–07, Amendment 

39–16526 (75 FR 75878, December 7, 2010). 

Except for airplanes on which Airbus 

Modification 34804 has been embodied in 

production or on which Airbus Service 

Bulletins A320–25–1557 and A320–53–1215 

have been done in service, prior to the 

accumulation of 24,000 total flight cycles, or 

within 500 flight cycles after January 11, 

2011 (the effective date of AD 2010–24–07), 

whichever occurs later: Do a special detailed 

inspection of the 80VU rack lower central 

support for cracking, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–25A1555, 

Revision 02, dated November 5, 2008. Repeat 

the inspection thereafter at the interval 

specified in paragraph (i)(1) or (i)(2) of this 

AD, as applicable. Replacing the pyramid 

fitting on the 80VU rack with a new, 

reinforced fitting, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1215, dated 

November 5, 2008, terminates the inspection 

requirements of this paragraph. Doing the 

initial inspection specified in paragraph (n) 

of this AD terminates the requirements of this 

paragraph. 

(1) For airplanes on which the 80VU rack 

lower central support has not been repaired 

or replaced using Airbus Mandatory Service 

Bulletin A320–25A1555 or Airbus Service 

Bulletin A320–25–1557: Repeat the 

inspection thereafter at the interval specified 

in paragraph (i)(1)(i) or (i)(1)(ii) of this AD, 

as applicable. 

(i) For airplanes on which the lower central 

support has accumulated 30,000 total flight 

cycles or more: At intervals not to exceed 500 

flight cycles. 

(ii) For airplanes on which the lower 

central support has accumulated fewer than 

30,000 total flight cycles: At intervals not to 

exceed 4,500 flight cycles, without exceeding 

30,750 total flight cycles on the support for 

the first repetitive inspection. 

(2) For airplanes on which the 80VU rack 

lower central support has been repaired or 

replaced using Airbus Mandatory Service 

Bulletin A320–25A1555 or Airbus Service 

Bulletin A320–25–1557: Do the next 

inspection within 24,000 flight cycles after 

the repair or replacement and thereafter 

repeat the inspection at the interval specified 

in paragraph (i)(1)(i) or (i)(1)(ii) of this AD, 

as applicable. 

(j) Retained Corrective Actions for 

Paragraph (i) of This AD 

This paragraph restates the requirements of 

paragraph (j) of AD 2010–24–07, Amendment 

39–16526 (75 FR 75878, December 7, 2010). 

If any crack is found during any inspection 

required by paragraph (i) of this AD: Before 

further flight, replace the pyramid fitting on 

the 80VU rack with a new, reinforced fitting, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1215, dated November 5, 2008. Doing this 

replacement terminates the inspection 

requirements of paragraph (i) of this AD. 

(k) Retained Optional Terminating Action 

This paragraph restates the requirements of 

paragraph (k) of AD 2010–24–07, 

Amendment 39–16526 (75 FR 75878, 

December 7, 2010). Doing the actions 

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

this AD terminates the repetitive inspections 

required by this AD. 

(1) Replacing the pyramid fitting on the 

80VU rack with a new, reinforced fitting, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1215, dated November 5, 2008. 

(2) Modifying the 80VU lower lateral 

fittings, in accordance with Airbus Service 

Bulletin A320–25–1557, Revision 02, dated 

November 5, 2008. 

(l) New Requirement of This AD: Repetitive 

Inspection of Lower Lateral Support Fittings 

Except for airplanes on which Airbus 

Modification 34804 has been embodied in 

production, or on which the 80VU rack lower 

lateral support has been modified, as 

specified in the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–25–1557, dated June 14, 2007; 

Revision 01, dated February 7, 2008; or 

Revision 02, dated November 5, 2008: At the 

latest of the applicable times specified in 

paragraphs (l)(1) through (l)(4) of this AD, do 

a special detailed (borescope) inspection of 

the 80VU rack lower lateral fittings for 

damage (e.g., broken fitting, missing bolts, 

migrated bushings, material burr, or rack in 

contact with the fitting), in accordance with 

the Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–25A1555, 

Revision 03, dated February 28, 2012. Repeat 

the inspection thereafter at intervals not to 

exceed 500 flight cycles until the terminating 

action specified in paragraph (k) of this AD 

is done. Doing the initial inspection specified 

in this paragraph terminates the requirements 

of paragraph (g) of this AD. 

(1) Before the accumulation of 20,000 total 

flight cycles from the airplane first flight, or 

within 750 flight cycles after the effective 

date of this AD, whichever occurs later, 

without exceeding 24,000 total flight cycles. 

(2) Within 20,000 flight cycles after the 

most recent repair or replacement of the 

80VU rack lower lateral fittings was done, as 

specified in the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–25A1555, dated June 24, 2007; 

Revision 01, dated February 18, 2008; or 

Revision 02, dated November 5, 2008. 

(3) Within 500 flight cycles after the 

effective date of this AD, without exceeding 

4,500 flight cycles after the most recent 

inspection of the 80VU rack lower lateral 

fittings was done, as specified in the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–25A1555, 

dated June 14, 2007; Revision 01, dated 

February 18, 2008; or Revision 02, dated 

November 5, 2008. 

(4) Within 500 flight cycles after the 

effective date of this AD. 

(m) New Requirement of This AD: Corrective 

Action for Damage of Lower Lateral Support 

Fittings 

If any damage is found during any 

inspection required by paragraph (l) of this 

AD: At the applicable time given in 

paragraph E.(2)., ‘‘Accomplishment 

Timescale,’’ in Airbus Mandatory Service 

Bulletin A320–25A1555, Revision 03, dated 

February 28, 2012, accomplish the applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–25A1555, 

Revision 03, dated February 28, 2012; except 

where this service information specifies to 

contact Airbus for further instructions, before 

further flight, contact either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent) for instructions; and do 

those instructions. 

(n) New Requirement of This AD: Repetitive 

Inspection on Lower Central Support 

Except for airplanes on which Airbus 

Modification 34804 has been embodied in 

production, or on which the 80VU rack lower 

central support has been modified, as 

specified in the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1215, dated November 5, 2008: At the 

latest of the applicable times specified in 

paragraphs (n)(1) through (n)(6) of this AD, 

do a special detailed (borescope) inspection 

of the 80VU rack lower central support for 

cracking, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–25A1555, 

Revision 03, dated February 28, 2012. Repeat 

the inspection thereafter at intervals not to 

exceed 500 flight cycles until the terminating 

action specified in paragraph (k) of this AD 

is done. Doing the initial inspection specified 

in this paragraph terminates the requirements 

of paragraph (i) of this AD. 

(1) Before the accumulation of 20,000 total 

flight cycles from the airplane first flight, or 

within 750 flight cycles after the effective 

date of this AD, whichever occurs later, 

without exceeding 24,000 total flight cycles. 

(2) Within 20,000 flight cycles after the 

most recent repair or replacement of the 

80VU rack lower central support was done, 

as specified in the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–25A1555, dated June 14, 2007; 

Revision 01, dated February 18, 2008; or 

Revision 02, dated November 5, 2008. 

(3) Within 20,000 flight cycles after 

modification of the 80VU rack lower central 

support was done, as specified in the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–25–1557, dated June 

14, 2007; or Revision 01, dated February 07, 

2008. 

(4) For airplanes on which, as of the 

effective date of this AD, the 80VU rack 

lower central support has accumulated fewer 

than 30,000 total flight cycles: Within 500 

flight cycles after the effective date of this 

AD, without exceeding 4,500 flight cycles 

after the most recent inspection of the 80VU 

rack lower central support was done, as 

specified in the Accomplishment 

Instructions of Airbus Mandatory Service 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations 78709 

Bulletin A320–25A1555, dated June 24, 2007; 

Revision 01, dated February 18, 2008; or 

Revision 02, dated November 5, 2008. 

(5) For airplanes on which, as of the 

effective date of this AD, the 80VU rack 

lower central support has accumulated 

30,000 total flight cycles or more: Within 500 

flight cycles after the most recent inspection 

of the 80VU rack lower central support was 

done, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–25A1555, 

dated June 14, 2007; Revision 01, dated 

February 18, 2008; or Revision 02, dated 

November 5, 2008. 

(6) Within 500 flight cycles after the 

effective date of this AD. 

(o) New Requirement of This AD: Corrective 

Action for Damage to Lower Central Support 

If any cracking is found during any 

inspection required by paragraph (n) of this 

AD: Before further flight do the actions in 

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

(1) If kits 25A1555A01 thru A05 are 

available, contact the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the European Aviation 

Safety Agency (EASA) (or its delegated 

agent); for instructions and do the repair. 

(2) Do the actions specified in paragraph 

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

(p) New Requirement of This AD: Repetitive 

Inspection of Upper Fittings and Shelves 

Concurrently with each special detailed 

inspection required by paragraphs (l) and (n) 

of this AD: Do a general visual inspection for 

damage (cracking or deformation) of the 

upper fittings and shelves of the 80VU rack, 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–25A1555, Revision 03, dated 

February 28, 2012. If any damage is found: 

Before further flight, repair the damage using 

a method approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA (or its 

delegated agent). 

(q) New Requirement of This AD: Corrective 

Action for Previous Findings 

For airplanes that have been inspected 

before the effective date of this AD as 

specified in Airbus Service Bulletin A320– 

25A1555, dated June 14, 2007; Airbus 

Mandatory Service Bulletin A320–25A1555, 

Revision 01, dated February 18, 2008; or 

Airbus Mandatory Service Bulletin A320– 

25A1555, Revision 02, dated November 5, 

2008; and on which damage of the fittings 

was found, except for airplanes specified in 

paragraph (q)(1) or (q)(2) of this AD: At the 

applicable time given in paragraph E.(2)., 

‘‘Accomplishment Timescale,’’ of Airbus 

Mandatory Service Bulletin A320–25A1555, 

Revision 03, dated February 28, 2012, 

accomplish the applicable corrective actions, 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–25A1555, Revision 03, dated 

February 28, 2012, except where this service 

information specifies to contact Airbus for 

further instructions, before further flight, 

contact either the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or EASA (or its delegated 

agent); for instructions and follow those 

instructions. Accomplishing the actions 

required by this paragraph terminates the 

requirements of paragraph (h) of this AD. 

(1) Airplanes on which Airbus 

Modification 34804 has been embodied in 

production. 

(2) Airplanes on which the terminating 

action specified in paragraph (k) of this AD 

has been done. 

(r) Credit for Previous Actions 

This paragraph restates the credit given in 

paragraph (l) of AD 2010–24–07, Amendment 

39–16526 (75 FR 75878, December 7, 2010). 

(1) This paragraph provides credit for 

actions required by paragraphs (g), (h), and 

(i) of this AD, if those actions were performed 

before January 11, 2011 (the effective date of 

AD 2010–24–07, Amendment 39–16526 (75 

FR 75878, December 7, 2010)), using the 

service bulletins specified in paragraph 

(r)(1)(i) or (r)(1)(ii) of this AD. 

(i) Airbus Mandatory Service Bulletin 

A320–25A1555, Revision 01, dated February 

18, 2008, which is not incorporated by 

reference in this AD. 

(ii) Airbus Service Bulletin A320– 

25A1555, dated June 14, 2007, which is not 

incorporated by reference in this AD. 

(2) This paragraph provides credit for 

actions required by paragraphs (g) and (k)(2) 

of this AD, if those actions were performed 

before January 11, 2011 (the effective date of 

AD 2010–24–07, Amendment 39–16526 (75 

FR 75878, December 7, 2010)), using the 

service bulletins specified in paragraph 

(r)(2)(i) or (r)(2)(ii) of this AD. 

(i) Airbus Service Bulletin A320–25–1557, 

dated June 14, 2007, which is not 

incorporated by reference in this AD. 

(ii) Airbus Service Bulletin A320–25–1557, 

Revision 01, dated February 7, 2008, which 

is not incorporated by reference in this AD. 

(s) 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 

2010–24–07, Amendment 39–16526 (75 FR 

75878, December 7, 2010), are approved as 

AMOCs for the corresponding provisions of 

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 Design Approval 

Holder with a State of Design Authority’s 

design organization approval, as applicable). 

For a repair method to be approved, the 

repair approval must specifically refer to this 

AD. You are required to ensure the product 

is airworthy before it is returned to service. 

(t) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information European 

Aviation Safety Agency Airworthiness 

Directive 2012–0134, dated July 18, 2012, for 

related information. You may examine the 

MCAI in the AD docket on the Internet at 

http://www.regulations.gov/ 

#!documentDetail;D=FAA-2013-0416-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the addresses specified in 

paragraphs (u)(5) and (u)(6) of this AD. 

(u) 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. 

(3) The following service information was 

approved for IBR on January 31, 2014. 

(i) Airbus Mandatory Service Bulletin 

A320–25A1555, Revision 03, dated February 

28, 2012. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on January 11, 2011 (75 FR 

75878, December 7, 2010). 

(i) Airbus Mandatory Service Bulletin 

A320–25A1555, Revision 02, excluding 

Appendix 1, dated November 5, 2008. 

(ii) Airbus Service Bulletin A320–25–1557, 

Revision 02, dated November 5, 2008. 

(iii) Airbus Service Bulletin A320–53– 

1215, dated November 5, 2008. 

(5) 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. 

(6) 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. 

(7) 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. 


tkelley on DSK3SPTVN1PROD with RULES
78710 Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations 

Issued in Renton, Washington, on 

December 4, 2013. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–30066 Filed 12–26–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0340; Directorate 

Identifier 2010–SW–081–AD; Amendment 

39–17630; AD 2013–21–06] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Eurocopter Deutschland GmbH 

(Eurocopter) Model EC135 P1, EC135 

P2, EC135 P2+, EC135 T1, EC135 T2, 

EC135 T2+, and MBB–BK 117 C–2 

helicopters with a certain external 

mounted hoist system (hoist) with boom 

support assembly (boom) installed. This 

AD requires inspecting the boom for a 

crack and, if a crack exists, replacing the 

boom with an airworthy boom. Until the 

boom is inspected, this AD requires, 

before further flight, and thereafter 

before the first flight of each day, 

checking the hoist for a crack. This AD 

was prompted by cracks found on the 

boom during a pre-flight check of a hoist 

on an MBB–BK 117 C–2 helicopter. The 

actions of this AD are intended to detect 

a crack and prevent failure of the boom, 

loss of the boom and attached loads, and 

subsequent loss of helicopter control. 

DATES: This AD is effective January 31, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of January 31, 2014. 

ADDRESSES: For service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at http:// 

www.eurocopter.com/techpub, and 

contact UTC Aerospace Systems 

(formerly the Goodrich Corporation), 

2727 East Imperial Highway, Brea, CA 

92821; telephone (714) 984–1461; fax 

714–984–1675, or at www.goodrich.com. 

You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

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 AD, the foreign 

authority’s ADs, any incorporated-byreference service information, the 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

Office (phone: 800–647–5527) is U.S. 

Department of Transportation, Docket 

Operations Office, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Matt 

Wilbanks, Aviation Safety Engineer, 

Rotorcraft Certification Office, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

matt.wilbanks@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On April 15, 2013, at 78 FR 22209, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 by 

adding an AD that would apply to 

Eurocopter Model EC135 P1, EC135 P2, 

EC135 P2+, EC135 T1, EC135 T2 and 

EC135 T2+ helicopters with a Goodrich 

Corporation (Goodrich) hoist with a 

boom, Part Number (P/N) 44301–500, 

44307–500, or 44307–500–1 installed, 

and Model MBB–BK 117 C–2 

helicopters with a Goodrich hoist with 

boom P/N 44307–500 installed. The 

NPRM proposed to require dye 

penetrant inspecting the boom for a 

crack and, if a crack exists, replacing the 

boom with an airworthy boom. Until the 

inspection is completed, the NPRM 

proposed to require, before the first 

flight of each day, a visual check of the 

hoist for a crack. The NPRM proposed 

to allow an owner/operator (pilot) 

holding at least a private pilot certificate 

to conduct that check. The performance 

of the check would be required to be 

entered into the aircraft’s maintenance 

records showing compliance with this 

AD in accordance with applicable 

regulations. This authorization marks an 

exception to our standard maintenance 

regulations. The proposed requirements 

were intended to detect a crack and 

prevent failure of the boom, loss of the 

boom and attached loads, and 

subsequent loss of helicopter control. 

The NPRM was prompted by AD No. 

2010–0154, dated August 13, 2010, 

issued by the European Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Union. EASA issued AD No. 

2010–0154 to correct an unsafe 

condition for Eurocopter Model MBB– 

BK 117 C–2, EC135, and EC635 series 

helicopters. EASA AD No. 2010–0154 

supersedes EASA AD No. 2009–0093–E, 

dated April 17, 2009. EASA advises that 

cracks were detected on the boom, P/N 

44307–500, during a pre-flight check of 

the hoist on a Model MBB–BK 117 C– 

2 helicopter. EASA advises that this 

condition, if not detected and corrected, 

would impair the structural strength of 

the boom and could lead to failure of 

the boom. EASA advises that this could 

result in the loss of the boom and 

attached loads. According to EASA, 

boom P/Ns 44301–500 and 44307–500– 

1 are of similar design to P/N 44307– 

500, and therefore are also subject to 

this unsafe condition. As a result, EASA 

issued Emergency AD No. 2009–0093–E 

to require repetitive visual checks of the 

affected boom and removal or 

replacement of the boom when cracks 

are found. 

EASA advises that since AD No. 

2009–0093–E was issued, further 

technical investigation determined that 

torque values that were too high have 

been applied. EASA advises that 

Goodrich Corporation, the manufacturer 

of the affected booms, had developed an 

inspection that would determine the 

need for further action. As a result, 

EASA superseded its AD to include a 

new inspection to detect damage, by 

issuing EASA AD No. 2010–0154. EASA 

AD states that if no damage is found 

during this new inspection, that 

constitutes terminating action. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the NPRM 

(78 FR 22209, April 15, 2013). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Germany 

and are approved for operation in the 

United States. Pursuant to our bilateral 

agreement with Germany, EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs and that air 


tkelley on DSK3SPTVN1PROD with RULES