This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

7098 

Vol. 79, No. 25 

Thursday, February 6, 2014 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0012; Directorate 

Identifier 2012–NM–007–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2004–16– 

01, that applies to certain Airbus Model 

A330–200 and –300, and Model A340– 

200 and –300, series airplanes. AD 

2004–16–01 currently requires 

repetitive inspections for cracking of the 

chromed area of the left and right piston 

rods for the main landing gear (MLG) 

retraction actuators, and related 

investigative and corrective actions if 

necessary. Since we issued AD 2004– 

16–01, we have determined that the 

presence of water in the internal volume 

of the piston rod can consequently lead 

to propagation of longitudinal cracking 

in the body of the piston rod. We have 

also determined through sampling that 

certain retraction actuator piston rods of 

the MLG need to be replaced. This 

proposed AD would require repetitive 

draining of any fluid from the retraction 

actuator piston rod internal volume and 

sealing of the vent hole; repetitive 

ultrasonic inspections of the upper end 

of the piston rods, and corrective 

actions if necessary; a one-time 

ultrasonic inspection (longitudinal and 

circumferential) of the full-length of the 

piston rod, and corrective actions if 

necessary; and a terminating 

modification of the left-hand and righthand MLG retraction actuators. We are 

proposing this AD to prevent cracking of 

the piston rods for the MLG retraction 

actuators, which could result in rupture 

of a piston rod, non-damped extension 

of the MLG, high loads on the fully 

extended MLG, and consequent reduced 

structural integrity of the MLG. 

DATES: We must receive comments on 

this proposed AD by March 24, 2014. 

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 SAS— 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@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 by searching for 

and locating Docket No. FAA–2014– 

0012; 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 Operations 

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

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1138; 

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–2014–0012; Directorate Identifier 

2012–NM–007–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On July 23, 2004, we issued AD 2004– 

16–01, Amendment 39–13757 (69 FR 

46979, August 4, 2004). AD 2004–16–01 

requires actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2004–16–01, the 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2011– 

0178R1, dated March 6, 2012, corrected 

March 7, 2012 (for Model A340–200 and 

–300 series airplanes); and EASA AD 

2011–0179R1, dated March 6, 2012 (for 

Model A330–200 and –300 series 

airplanes) (both referred to after this as 

the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’); to correct an unsafe condition 

for the specified products. EASA AD 

2011–0178R1, dated March 6, 2012, 

corrected March 7, 2012, states: 

During an approach phase, the flight crew 

of an A330 aeroplane had to perform a freefall extension of the left-hand (LH) MLG. 

Rupture of the LH MLG retraction actuator 

piston rod was found near the rod attachment 

point. The inspection revealed at the location 

of the rupture the presence of corrosion 

resulting from incorrect application of the 

anticorrosion protection, and circumferential 

cracks resulting from normal operational 

loading effects. 

Since the above rupture, new cases of crack 

propagation along the length of the piston 

rod occurred. These ruptures led to a nondamped extension of the landing gear. Fully 


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extended, the landing gear assembly was 

submitted to high loads jeopardizing its 

structural integrity. 

This condition, if not detected and 

corrected, could lead to MLG failure during 

landing or roll-out and consequent damage to 

the aeroplane and injury to occupants. 

DGAC France issued AD F–2005–098 

(EASA approval 2005–5887) [and AD F– 

2005–099 (EASA approval 2005–5888)] to 

address this unsafe condition [the FAA 

issued AD 2004–16–01, Amendment 39– 

13757 (69 FR 46979, August 4, 2004)]. Since 

that [DGAC France] AD was issued, the 

results of extensive investigation determined 

that the presence of water in the internal 

volume of the piston rod can lead to the 

formation of ice which represents a potential 

source of high magnitude tensile hoop 

stresses in the material of the rod, leading to 

propagation of longitudinal crack in the body 

of the piston rod. 

Prompted by these findings, EASA issued 

AD 2006–0301, partially retaining the 

requirements of DGAC France AD F–2005– 

099, which was superseded, and to revise the 

inspection requirements as follows: 

a. Extend the repetitive inspections 

interval for the removal of fluid from the 

internal volume of the piston rod using flight 

cycles in lieu of flight hours as this better 

represents the mechanism for the 

accumulation of water within the piston rod. 

b. Remove the preliminary visual 

inspection from the ultrasonic longitudinal 

inspection of the upper end of the piston rod. 

c. Add a new one-time ultrasonic 

longitudinal and circumferential inspection 

of the full piston rod length to eliminate any 

parts that exhibit severe corrosion along the 

internal length of the piston rod. 

d. Require installation of new design 

hollow piston rod Part Number (P/N) 

114256328 (Airbus mod. 52980—SB A340– 

32–4222 Revision 01) without a vent hole, 

thus eliminating moisture ingress as the 

terminating action. 

EASA AD 2006–0301 was later revised: 

—at revision 01, to correct a number of 

typographical errors and to add reference 

to Airbus SB A340–32–4212 Revision 04, 

and 

—at revision 02 to extend the inspections 

threshold from 3 to 6 years in service usage 

for retraction actuator piston rod P/N 

114256321 issue 06 which was reidentified to P/N 114256326 issue 01 in 

accordance with the instructions of Airbus 

SB A340–32–4260. 

More recently, the sampling of piston rod 

P/N 114256326 issue 1 and P/N 114256321 

issue 06 have confirmed the need to replace 

all retraction actuator piston rods with a 

piston rod P/N114256328. 

For the reasons described above, this 

[EASA] AD at original issue retained the 

requirements of EASA AD 2006–0301R2 

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

2006_0301_R2_superseded.pdf/AD_2006- 

0301R2_1), which is superseded, and 

required the replacement of all retraction 

actuator piston rods with a piston rod P/N 

114256328, which constitutes terminating 

action to the repetitive requirements of this 

AD. 

This [EASA] AD is revised to clarify that 

aeroplanes on which Airbus mod. 52980 has 

been embodied in production are not 

required to accomplish the reidentification of 

MLG retraction actuator P/N 114256002–055 

which is mentioned in the accomplishment 

instructions of Airbus SB A340–32–4222 

Revision 03. 

This [EASA] AD has been republished to 

correct a typographical mistake of the 

applicable Airbus SB number in the 

Applicability (in the Note) and in the Reason 

sections of this [EASA] AD. 

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– 

2014–0012. 

Relevant Service Information 

Airbus has issued the following 

service bulletins. 

• Airbus Mandatory Service Bulletin 

A330–32–3173, Revision 05, dated 

September 26, 2008. 

• Airbus Mandatory Service Bulletin 

A330–32–3180, Revision 03, dated 

January 28, 2011. 

• Airbus Mandatory Service Bulletin 

A340–32–4212, Revision 05, dated 

September 26, 2008. 

• Airbus Mandatory Service Bulletin 

A340–32–4222, Revision 03, dated 

January 28, 2011. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

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. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

EASA AD 2011–0178R1, dated March 

6, 2012, corrected March 7, 2012 (for 

Model A340–200 and –300 series 

airplanes); and AD 2011–0179R1, dated 

March 6, 2012 (for Model A330–200 and 

–300 series airplanes); require 

replacement of the retraction actuator 

within 10 flight cycles if the findings of 

the ultrasonic inspection of the 

retraction actuator piston rod end are 

between 75% and 90% FSH (full screen 

height) and between 5 and 7 in time 

base. However, paragraph (n) of this 

proposed AD would require 

replacement of the retraction actuator 

before further flight if the findings of the 

ultrasonic inspection of the retraction 

actuator piston rod end are higher than 

75% and between 5 and 7 in time base. 

EASA AD 2011–0178R1, dated March 

6, 2012, corrected March 7, 2012 (for 

Model A340–200 and –300 series 

airplanes); and AD 2011–0179R1, dated 

March 6, 2012 (for Model A330–200 and 

–300 series airplanes); require 

replacement of the retraction actuator 

within 10 landings if the findings of the 

one-time ultrasonic circumferential 

inspection of the full-length chromed 

part of the piston rod give an indication 

between 75% and 90% FSH and 

between 7 and 9.5 in time base. 

However, paragraph (p)(2) of this 

proposed AD would require 

replacement of the retraction actuator 

before further flight if inspection 

findings are higher than 75% FSH and 

between 7 and 9.5 in time base. 

We have determined that, because of 

the safety implications and 

consequences associated with those 

findings, the actuator must be replaced 

before further flight. These differences 

have been coordinated with EASA. 

Costs of Compliance 

We estimate that this proposed AD 

affects 24 Model A330–200 and –300 

series airplanes of U.S. registry. There 

are no Model A340–200 and –300 series 

airplanes of U.S. registry. 

We estimate that it would take about 

67 work-hours per product to comply 

with the basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Required parts 

would cost about $56,000 per product (2 

actuators). Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $1,480,680, or 

$61,695 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 38 work-hours and require parts 

costing $56,000 (2 actuators), for a cost 

of $59,230 per product. We have no way 

of determining the number of aircraft 

that might need these actions. 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 


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requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this proposed AD is 2120– 

0056. The paperwork cost associated 

with this proposed AD has been 

detailed in the Costs of Compliance 

section of this document and includes 

time for reviewing instructions, as well 

as completing and reviewing the 

collection of information. Therefore, all 

reporting associated with this proposed 

AD is mandatory. Comments concerning 

the accuracy of this burden and 

suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591, ATTN: Information 

Collection Clearance Officer, AES–200. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This proposed 

regulation is within the scope of that 

authority because it addresses an unsafe 

condition that is likely to exist or 

develop on products identified in this 

rulemaking action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2004–16–01, Amendment 39–13757 (69 

FR 46979, August 4, 2004), and adding 

the following new AD: 

Airbus: Docket No. FAA–2014–0012; 

Directorate Identifier 2012–NM–007–AD. 

(a) Comments Due Date 

We must receive comments by March 24, 

2014. 

(b) Affected ADs 

This AD supersedes AD 2004–16–01, 

Amendment 39–13757 (69 FR 46979, August 

4, 2004). 

(c) Applicability 

This AD applies to Airbus Model A330– 

201, –202, –203, –223, –243, –301, –302, 

–303, –321, –322, –323, –341, –342, and –343 

airplanes; and Model A340–211, –212, and 

–213, –311, –312, and –313 airplanes; 

certificated in any category; all manufacturer 

serial numbers, except for those airplanes 

that have had Airbus Modification 52980 

incorporated in production on both main 

landing gear (MLG) units, or airplanes that 

have had Airbus Modification 54500 

incorporated in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Reason 

This AD was prompted by reports of the 

piston rods for the MLG retraction actuators 

rupturing during flight. We are issuing this 

AD to prevent cracking of the piston rods for 

the MLG retraction actuators, which could 

result in rupture of a piston rod, non-damped 

extension of the MLG, high loads on the fully 

extended MLG, and consequent reduced 

structural integrity of the MLG. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Detailed Inspections 

At the applicable time specified in 

paragraph (g)(1) or (g)(2) of this AD: Do a 

detailed inspection for cracking of the visible 

chromed area of the MLG retraction actuator 

piston rods in the fully extended position, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–32–3173, Revision 05, dated 

September 26, 2008 (for Model A330 series 

airplanes); or Airbus Mandatory Service 

Bulletin A340–32–4212, Revision 05, dated 

September 26, 2008 (for Model A340–200 

and –300 series airplanes). Repeat the 

inspection thereafter at intervals not to 

exceed 8 days until the actions required by 

paragraphs (j) and (o) of this AD are 

accomplished. 

(1) For MLG retraction actuator piston rods 

that have not had a detailed inspection 

accomplished as of the effective date of this 

AD, as described in any applicable service 

information specified in paragraph (h)(1) or 

(h)(2) of this AD: At the applicable time 

specified in paragraph (g)(1)(i) or (g)(1)(ii) of 

this AD. 

(i) For MLG retraction actuator piston rods 

having part number (P/N) 114256309, or 

P/N 114256321 issue 03: Do the inspection 

within 60 days after the effective date of this 

AD, or before the MLG retraction actuator has 

been in service 36 months, whichever occurs 

later. 

(ii) For MLG retraction actuator piston rods 

having P/N 114256326 issue 01, or P/N 

114256321 issue 06: Do the inspection within 

60 days after the effective date of this AD, or 

before the MLG retraction actuator has been 

in service 72 months, whichever occurs later. 

(2) For MLG retraction actuator piston rods 

having P/N 114256309, P/N 114256321 issue 

03, P/N 114256326 issue 01, or P/N 

114256321 issue 06, that have had a detailed 

inspection accomplished as of the effective 

date of this AD, as described in the 

applicable service information specified in 

paragraph (h)(1) or (h)(2) of this AD: Inspect 

within 8 days after the effective date of this 

AD. 

(h) Service Information To Determine 

Airplane Configuration for Paragraph (g) of 

This AD 

(1) For Model A330 airplanes: 

(i) Airbus Mandatory Service Bulletin 

A330–32–3173, Revision 01, dated June 16, 

2004; 

(ii) Airbus Mandatory Service Bulletin 

A330–32–3173, Revision 02, dated May 11, 

2005; 

(iii) Airbus Mandatory Service Bulletin 

A330–32–3173, Revision 03, dated March 13, 

2006; 

(iv) Airbus Mandatory Service Bulletin 

A330–32–3173, Revision 04, dated June 12, 

2006; or 

(v) Airbus Mandatory Service Bulletin 

A330–32–3173, Revision 05, dated 

September 26, 2008. 

(2) For Model A340–200 and –300 series 

airplanes: 

(i) Airbus Mandatory Service Bulletin 

A340–32–4212, Revision 01, dated June 16, 

2004; 

(ii) Airbus Mandatory Service Bulletin 

A340–32–4212, Revision 02, dated May 11, 

2005; 


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(iii) Airbus Mandatory Service Bulletin 

A340–32–4212, Revision 03, dated March 13, 

2006; 

(iv) Airbus Mandatory Service Bulletin 

A340–32–4212, Revision 04, dated June 12, 

2006; or 

(v) Airbus Mandatory Service Bulletin 

A340–32–4212, Revision 05, dated 

September 26, 2008. 

(i) Corrective Action for Cracking 

If any cracking is found during any 

inspection required by paragraph (g) of this 

AD: Before further flight, replace the MLG 

retraction actuator with a new or serviceable 

part, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–32–3173, 

Revision 05, dated September 26, 2008 (for 

Model A330 series airplanes); or Airbus 

Mandatory Service Bulletin A340–32–4212, 

Revision 05, dated September 26, 2008 (for 

Model A340–200 and –300 series airplanes). 

(j) Repetitive Fluid Draining and Vent Hole 

Sealing 

At the applicable time specified in 

paragraph (j)(1) or (j)(2) of this AD: Drain any 

fluid from the retraction actuator piston rod 

internal volume and seal the vent hole, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–32–3173, Revision 05, dated 

September 26, 2008 (for Model A330 series 

airplanes); or Airbus Mandatory Service 

Bulletin A340–32–4212, Revision 05, dated 

September 26, 2008 (for Model A340–200 

and –300 series airplanes). Repeat the 

draining and sealing thereafter at intervals 

not to exceed 1,000 flight cycles or 24 

months, whichever occurs first. 

(1) For MLG retraction actuator piston rods 

that have not been inspected and have not 

had the fluid drained as of the effective date 

of this AD, as described in the applicable 

service information specified in paragraph 

(k)(1) or (k)(2) of this AD: At the applicable 

time specified in paragraph (j)(1)(i) or 

(j)(1)(ii) of this AD. 

(i) For MLG retraction actuator piston rods 

having P/N 114256309, or P/N 114256321 

issue 03: Do the draining and sealing within 

60 days after the effective date of this AD or 

before the MLG retraction actuator has been 

in service 36 months, whichever occurs later. 

(ii) For MLG retraction actuator piston rods 

having P/N 114256326 issue 01, or P/N 

114256321 issue 06: Do the draining and 

sealing within 60 days after the effective date 

of this AD or before the MLG retraction 

actuator has been in service 72 months, 

whichever occurs later. 

(2) For MLG retraction actuator piston rods 

having P/N 114256309, P/N 114256321 issue 

03, P/N 114256326 issue 01, or P/N 

114256321 issue 06, that have been inspected 

and the fluid drained as of the effective date 

of this AD, as described in the applicable 

service information specified in paragraph 

(k)(1) or (k)(2) of this AD: Do the draining 

and sealing at the later of the times specified 

in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD. 

(i) Within 1,000 flight cycles or 24 months, 

whichever occurs first, from the last 

inspection and fluid drainage accomplished 

in accordance with the actions required in 

paragraph (j) of this AD. 

(ii) Within 60 days after the effective date 

of this AD. 

(k) Service Information To Determine 

Configuration for Paragraph (j) of This AD 

(1) For Model A330 airplanes: 

(i) Airbus Mandatory Service Bulletin 

A330–32–3173, Revision 02, dated May 11, 

2005; 

(ii) Airbus Mandatory Service Bulletin 

A330–32–3173, Revision 03, dated March 13, 

2006; 

(iii) Airbus Mandatory Service Bulletin 

A330–32–3173, Revision 04, dated June 12, 

2006; or 

(iv) Airbus Mandatory Service Bulletin 

A330–32–3173, Revision 05, dated 

September 26, 2008. 

(2) For Model A340–200 and –300 series 

airplanes: 

(i) Airbus Mandatory Service Bulletin 

A340–32–4212, Revision 02, dated May 11, 

2005; 

(ii) Airbus Mandatory Service Bulletin 

A340–32–4212, Revision 03, dated March 13, 

2006; 

(iii) Airbus Mandatory Service Bulletin 

A340–32–4212, Revision 04, dated June 12, 

2006; or 

(iv) Airbus Mandatory Service Bulletin 

A340–32–4212, Revision 05, dated 

September 26, 2008. 

(l) Ultrasonic Inspection 

At the applicable time specified in 

paragraph (l)(1) or (l)(2) of this AD: Do an 

ultrasonic longitudinal inspection for 

cracking of the retraction actuator piston rod 

end, in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–32–3173, Revision 05, dated 

September 26, 2008 (for Model A330 series 

airplanes); or Airbus Mandatory Service 

Bulletin A340–32–4212, Revision 05, dated 

September 26, 2008 (for Model A340–200 

and -300 series airplanes). 

(1) For MLG retraction actuator piston rods 

that have not had a non-destructive test 

(NDT) inspection as of the effective date of 

this AD, as described in the applicable 

service information specified in paragraph 

(m)(1) or (m)(2) of this AD: At the applicable 

time specified in paragraph (l)(1)(i) or 

(l)(1)(ii) of this AD. 

(i) For MLG retraction actuator piston rods 

having P/N 114256309, or P/N 114256321 

issue 03: Do the inspection within 60 days 

after the effective date of this AD, or before 

the MLG retraction actuator has been in 

service 36 months, whichever occurs later. 

(ii) For MLG retraction actuator piston rods 

having P/N 114256326 issue 01, or P/N 

114256321 issue 06: Do the inspection within 

60 days after the effective date of this AD, or 

before the MLG retraction actuator has been 

in service 72 months, whichever occurs later. 

(2) For MLG retraction actuator piston rods 

having P/N 114256309, P/N 114256321 issue 

03, P/N 114256326 issue 01, or P/N 

114256321 issue 06, that have had an NDT 

inspection as of the effective date of this AD, 

as described in the applicable service 

information specified in paragraph (m)(1) or 

(m)(2) of this AD: Do the inspection at the 

later of the times specified in paragraphs 

(l)(2)(i) and (l)(2)(ii) of this AD. 

(i) Within 1,400 flight hours, 250 flight 

cycles, or 4 months, whichever occurs first 

after the date of the last ultrasonic 

longitudinal inspection performed as 

described in the applicable service 

information specified in paragraph (m)(1) or 

(m)(2) of this AD. 

(ii) Within 60 days after the effective date 

of this AD. 

(m) Service Information To Determine 

Configuration for Paragraph (l) of This AD 

(1) For Model A330 airplanes: 

(i) Airbus Mandatory Service Bulletin 

A330–32–3173, dated December 17, 2003; 

(ii) Airbus Mandatory Service Bulletin 

A330–32–3173, Revision 01, dated June 16, 

2004; 

(iii) Airbus Mandatory Service Bulletin 

A330–32–3173, Revision 02, dated May 11, 

2005; 

(iv) Airbus Mandatory Service Bulletin 

A330–32–3173, Revision 03, dated March 13, 

2006; 

(v) Airbus Mandatory Service Bulletin 

A330–32–3173, Revision 04, dated June 12, 

2006; or 

(vi) Airbus Mandatory Service Bulletin 

A330–32–3173, Revision 05, dated 

September 26, 2008. 

(2) For Model A340–200 and –300 series 

airplanes: 

(i) Airbus Mandatory Service Bulletin 

A340–32–4212, dated December 17, 2003; 

(ii) Airbus Mandatory Service Bulletin 

A340–32–4212, Revision 01, dated June 16, 

2004; 

(iii) Airbus Mandatory Service Bulletin 

A340–32–4212, Revision 02, dated May 11, 

2005; 

(iv) Airbus Mandatory Service Bulletin 

A340–32–4212, Revision 03, dated March 13, 

2006; 

(v) Airbus Mandatory Service Bulletin 

A340–32–4212, Revision 04, dated June 12, 

2006; or 

(vi) Airbus Mandatory Service Bulletin 

A340–32–4212, Revision 05, dated 

September 26, 2008. 

(n) Corrective Action for Ultrasonic 

Inspection; Repetitive Interval 

(1) If the finding of the inspection required 

by paragraph (l) of this AD gives an 

indication of 75% or higher of full screen 

height (FSH) and between 5 and 7 in time 

base: Before further flight, replace the MLG 

retraction actuator with a new or serviceable 

part, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–32–3173, 

Revision 05, dated September 26, 2008 (for 

Model A330 series airplanes); or Airbus 

Mandatory Service Bulletin A340–32–4212, 

Revision 05, dated September 26, 2008 (for 

Model A340–200 and –300 series airplanes). 

(2) If the finding of the inspection required 

by paragraph (l) of this AD gives an 

indication of less than 75% FSH and between 

5 and 7 in time base: Repeat the inspection 

required by paragraph (l) of this AD 

thereafter at intervals not to exceed 1,400 

flight hours, 250 flight cycles, or 4 months, 

whichever occurs first. 


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7102 Federal Register / Vol. 79, No. 25 / Thursday, February 6, 2014 / Proposed Rules 

(o) One-Time Ultrasonic Inspections of the 

Full-Length of the Piston Rod 

At the applicable time specified in 

paragraph (o)(1) or (o)(2) of this AD: Do a 

full-length ultrasonic longitudinal and a fulllength circumferential inspection of the 

chromium-plated area of the piston rod for 

cracking, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–32–3173, 

Revision 05, dated September 26, 2008 (for 

Model A330 series airplanes); or Airbus 

Mandatory Service Bulletin A340–32–4212, 

Revision 05, dated September 26, 2008 (for 

Model A340–200 and –300 series airplanes). 

(1) For MLG retraction actuator piston rods 

having P/N 114256309, or P/N 114256321 

issue 03: Inspect at the later of the times 

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

of this AD. 

(i) Within 1,750 flight hours, 315 flight 

cycles, or 5 months after the effective date of 

this AD, whichever occurs first. 

(ii) Before the MLG retraction actuator has 

been in service 36 months. 

(2) For MLG retraction actuator piston rods 

having P/N 114256326 issue 01, or P/N 

114256321 issue 06: Inspect at the later of the 

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

(o)(2)(ii) of this AD. 

(i) Within 1,750 flight hours, 315 flight 

cycles, or 5 months after the effective date of 

this AD, whichever occurs first. 

(ii) Before the MLG retraction actuator has 

been in service 72 months. 

(p) Corrective Action for One-time 

Ultrasonic Inspections of the Full-Length of 

the Piston Rod 

(1) If the finding of the full-length 

ultrasonic longitudinal inspection required 

by paragraph (o) of this AD gives an 

indication of 75% or higher FSH and 

between 5 and 7 in time base: Before further 

flight, replace the MLG retraction actuator 

with a new or serviceable part, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–32– 

3173, Revision 05, dated September 26, 2008 

(for Model A330 series airplanes); or Airbus 

Mandatory Service Bulletin A340–32–4212, 

Revision 05, dated September 26, 2008 (for 

Model A340–200 and –300 series airplanes). 

(2) If the finding of the full-length 

ultrasonic circumferential inspection 

required by paragraph (o) of this AD gives an 

indication of 75% or higher FSH and 

between 7 and 9.5 in time base: Before 

further flight, replace the MLG retraction 

actuator with a new or serviceable part, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–32–3173, Revision 05, dated 

September 26, 2008 (for Model A330 series 

airplanes); or Airbus Mandatory Service 

Bulletin A340–32–4212, Revision 05, dated 

September 26, 2008 (for Model A340–200 

and –300 series airplanes). 

(q) Reporting Requirement 

Report the results (regardless of findings) 

of the detailed inspection, the fluid drain/

seal of the retraction actuator piston rod, the 

one-time ultrasonic longitudinal inspection 

of the upper end of the piston rod, and the 

one-time full-length ultrasonic 

circumferential inspection required by this 

AD, and the findings of the actions required 

by this AD that cause an actuator to be 

replaced, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–32–3173, 

Revision 05, dated September 26, 2008 (for 

Model A330 series airplanes); or Airbus 

Mandatory Service Bulletin A340–32–4212, 

Revision 05, dated September 26, 2008 (for 

Model A340–200 and –300 series airplanes). 

Submit the report to Airbus Customer 

Services Directorate, Attention: SEDCC1 

Technical Data and Documentation Services 

fax: (+33) 5 61 93 28 06; email: sb.reporting@

airbus.com, or via your resident customer 

support office. Submit the report at the 

applicable time specified in paragraph (q)(1) 

or (q)(2) of this AD. 

(1) If the actions requiring reporting, as 

specified in paragraph (q) of this AD, are 

done on or after the effective date of this AD: 

Submit the report within 90 days after those 

actions have been done. 

(2) If the actions requiring reporting, as 

specified in paragraph (q) of this AD, were 

done before the effective date of this AD: 

Submit the report within 90 days after the 

effective date of this AD. 

(r) Terminating Actions for Repetitive 

Detailed Inspections 

Accomplishment of the initial drainage of 

the fluid from the piston, as required by 

paragraph (j) of this AD, the full-length 

ultrasonic longitudinal inspection, and the 

full-length circumferential inspection, as 

required by paragraph (o) of this AD, 

constitutes terminating action for the 

repetitive detailed inspections required by 

paragraph (g) of this AD, provided no crack 

is found during the inspections. 

(s) Terminating Modification 

Within 48 months after the effective date 

of this AD: Modify the left-hand and righthand MLG retraction actuators, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–32– 

3180, Revision 03, dated January 28, 2011 

(for Model A330 series airplanes); or Airbus 

Mandatory Service Bulletin A340–32–4222, 

Revision 03, dated January 28, 2011 (for 

Model A340–200 and –300 series airplanes). 

Accomplishment of the modification 

required by this paragraph terminates the 

repetitive requirements of this AD for the 

MLG retraction actuator that is modified. 

(t) Exception to Re-Identification of the MLG 

Retraction Actuator 

The re-identification of the MLG retraction 

actuator having P/N 114256002–055, which 

is described in Airbus Mandatory Service 

Bulletin A330–32–3180, Revision 03, dated 

January 28, 2011 (for Model A330 series 

airplanes); or Airbus Mandatory Service 

Bulletin A340–32–4222, Revision 03, dated 

January 28, 2011 (for Model A340–200 and 

–300 series airplanes); is not required on 

airplanes that have Airbus modification 

52980 embodied in production. 

(u) Optional Parts Installation 

Installation of retraction actuator piston 

rod having P/N 114256323, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A330–32–3174, 

Revision 02, dated September 16, 2005 (for 

Model A330 series airplanes); or Airbus 

Service Bulletin A340–32–4213, Revision 01, 

dated September 16, 2005 (for Model A340– 

200 and –300 series airplanes); constitutes an 

acceptable method of compliance with the 

requirements of paragraphs (g), (j), (l), and (o) 

of this AD for that installed MLG retraction 

actuator. 

(v) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install a piston rod having P/N 

114256309, or 114256321, or 114256326 

issue 01 for the MLG retraction actuator on 

any airplane, unless the part meets the 

applicable requirements of this AD at the 

specified times and intervals. 

(w) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraphs (g), (j), (l), and 

(o) of this AD, if those actions were 

performed before the effective date of this AD 

using the service information specified in 

paragraphs (w)(1)(i) through (w)(1)(ix) of this 

AD. 

(i) Airbus Mandatory Service Bulletin 

A330–32–3173, dated December 17, 2003; 

(for Model A330 series airplanes). 

(ii) Airbus Mandatory Service Bulletin 

A330–32–3173, Revision 01, dated June 16, 

2004 (for Model A330 series airplanes). 

(iii) Airbus Mandatory Service Bulletin 

A330–32–3173, Revision 02, dated May 11, 

2005 (for Model A330 series airplanes). 

(iv) Airbus Mandatory Service Bulletin 

A330–32–3173, Revision 03, dated March 13, 

2006 (for Model A330 series airplanes). 

(v) Airbus Mandatory Service Bulletin 

A330–32–3173, Revision 04, dated June 12, 

2006 (for Model A330 series airplanes). 

(vi) Airbus Mandatory Service Bulletin 

A340–32–4212, dated December 17, 2003 (for 

Model A340–200 and –300 series airplanes). 

(vii) Airbus Mandatory Service Bulletin 

A340–32–4212, Revision 01, dated June 16, 

2004 (for Model A340–200 and –300 series 

airplanes). 

(viii) Airbus Mandatory Service Bulletin 

A340–32–4212, Revision 02, dated May 11, 

2005; Revision 03, dated March 13, 2006 (for 

Model A340–200 and –300 series airplanes). 

(ix) Airbus Mandatory Service Bulletin 

A340–32–4212, Revision 04, dated June 12, 

2006 (for Model A340–200 and –300 series 

airplanes). 

(2) This paragraph provides credit for the 

actions required by paragraph (s) of this AD, 

if the modification was done before the 

effective date of this AD using the service 

bulletins specified in paragraphs (u)(2)(i) 

through (u)(2)(iv) of this AD. 

(i) Airbus Service Bulletin A330–32–3180, 

Revision 01, dated August 15, 2005 for Model 

A330 series airplanes). 

(ii) Airbus Mandatory Service Bulletin 

A330–32–3180, Revision 02, dated April 4, 

2007 (for Model A330 series airplanes). 

(iii) Airbus Service Bulletin A340–32– 

4222, Revision 01, dated August 15, 2005 (for 

Model A340–200 and –300 series airplanes). 

(iv) Airbus Mandatory Service Bulletin 

A340–32–4222, Revision 02, dated April 4, 

2007 (for Model A340–200 and –300 series 

airplanes). 


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Federal Register / Vol. 79, No. 25 / Thursday, February 6, 2014 / Proposed Rules 7103 

(3) This paragraph provides credit for the 

actions required by paragraph (s) of this AD, 

if the modification was done before the 

effective date of this AD using Airbus Service 

Bulletin A340–32–4222, dated September 20, 

2004; and re-identified using Airbus Service 

Bulletin A340–32–4222, Revision 01, dated 

August 15, 2005, or Airbus Mandatory 

Service Bulletin A340–32–4222, Revision 02, 

dated April 4, 2007. 

(x) 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1138; 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. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent, or the DAH with a 

State of Design Authority’s design 

organization approval). For a repair method 

to be approved, the repair approval must 

specifically refer to this AD. You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(y) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2011–0178R1, dated March 6, 2012 

(corrected March 7, 2012); and 2011–0179R1, 

dated March 6, 2012; for related information. 

These MCAIs may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2014–0012. 

(2) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

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

Issued in Renton, Washington, on January 

29, 2014. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–02522 Filed 2–5–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0053; Directorate 

Identifier 2013–NM–174–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 777 

airplanes. This proposed AD was 

prompted by reports of corroded, 

migrated, or broken spring pins of the 

girt bar floor fitting; in one case the 

broken pins prevented a door escape 

slide from deploying during a 

maintenance test. This proposed AD 

would require replacing the existing 

spring pins at each passenger entry door 

at both girt bar floor fittings with new 

spring pins. We are proposing this AD 

to prevent broken or migrated spring 

pins of the girt bar floor fittings, which 

could result in improper deployment of 

the escape slide/raft and consequent 

delay and injury during evacuation of 

passengers and crew from the cabin in 

the event of an emergency. 

DATES: We must receive comments on 

this proposed AD by March 24, 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 Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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, Washington. 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– 

0053; 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 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Ana 

Martinez Hueto, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6592; 

fax: 425–917–6591; email: 

ana.m.hueto@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 


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