Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Proposed Rules 16685 

paragraph (h) of this AD. Do all applicable 

related investigative and corrective actions 

before further flight. 

(1) For Group 1, Configuration 1 airplanes, 

as identified in Boeing Alert Service Bulletin 

777–57A0069, dated November 5, 2009: 

Before the accumulation of 3,500 total flight 

cycles, or within 500 flight cycles after the 

effective date of this AD, whichever occurs 

later. 

(2) For Group 1, Configuration 2 airplanes 

and Group 2 airplanes, as identified in 

Boeing Alert Service Bulletin 777–57A0069, 

dated November 5, 2009, on which a crack 

was found in the cutout keyway when the 

cutout keyway was changed: Within 1,125 

days after the effective date of this AD. 

Note 1: For Group 1, Configuration 2 

airplanes and Group 2 airplanes, as identified 

in Boeing Alert Service Bulletin 777– 

57A0069, dated November 5, 2009, on which 

no crack was found in the cutout keyway 

when the cutout keyway was changed: No 

further action is required by this AD. 

Exceptions to Service Bulletin 

(h) If any cracking is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 777–57A0069, dated 

November 5, 2009, specifies to contact 

Boeing for appropriate action: Before further 

flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (i) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Send information to ATTN: 

Duong Tran, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle ACO, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6452; fax 

(425) 917–6590. Or, e-mail information to 9- 

ANM-Seattle-ACO-AMOC-Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Issued in Renton, Washington, on March 

25, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–7458 Filed 4–1–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0281; Directorate 

Identifier 2009–NM–184–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300–600 and A310 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: Surface defects were 

visually detected on the rudder of one 

Airbus A319 and one A321 in-service 

aeroplane. Investigation has determined 

that the defects reported on both 

rudders corresponded to areas that had 

been reworked in production. The 

investigation confirmed that the defects 

were the result of de-bonding between 

the skin and honeycomb core. Such 

reworks were also performed on some 

rudders fitted on A310 and A300–600 

aeroplanes. An extended de-bonding, if 

not detected and corrected, may degrade 

the structural integrity of the rudder. 

The loss of the rudder leads to 

degradation of the handling qualities 

and reduces the controllability of the 

aeroplane. 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by May 17, 2010. 

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 

W12–40, 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— 

EAW (Airworthiness Office), 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; e-mail: 

account.airworth-eas@airbus.com; 

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

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, 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; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

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

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; 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–2010–0281; Directorate Identifier 

2009–NM–184–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 have lengthened the 30-day 

comment period for proposed ADs that 

address MCAI originated by aviation 

authorities of other countries to provide 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
16686 Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Proposed Rules 

adequate time for interested parties to 

submit comments. The comment period 

for these proposed ADs is now typically 

45 days, which is consistent with the 

comment period for domestic transport 

ADs. 

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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0002, 

dated January 5, 2010 (referred to after 

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

condition for the specified products. 

The MCAI states: 

Surface defects were visually detected on 

the rudder of one Airbus A319 and one A321 

in-service aeroplane. Investigation has 

determined that the defects reported on both 

rudders corresponded to areas that had been 

reworked in production. The investigation 

confirmed that the defects were the result of 

de-bonding between the skin and honeycomb 

core. Such reworks were also performed on 

some rudders fitted on A310 and A300–600 

aeroplanes. 

An extended de-bonding, if not detected 

and corrected, may degrade the structural 

integrity of the rudder. The loss of the rudder 

leads to degradation of the handling qualities 

and reduces the controllability of the 

aeroplane. 

To address this unsafe condition [this 

EASA AD] requires inspections of specific 

areas and, depending on findings, the 

application of corrective actions for those 

rudders where production reworks have been 

identified. 

This * * * [EASA] AD * * * also requires 

for the vacuum loss hole restoration: 

—A local ultrasonic inspection for reinforced 

area instead of the local thermographic 

inspection, which is maintained for nonreinforced areas, and 

—Additional work performance for rudders 

on which this thermographic inspection 

has been performed in the reinforced area. 

The inspections include vacuum loss 

inspections and elasticity laminate 

checker inspections for defects 

including de-bonding between the skin 

and honeycomb core of the rudder, and 

ultrasonic inspections for rudders on 

which temporary restoration with resin 

or permanent vacuum loss hole 

restoration has been performed. The 

corrective action is contacting the 

manufacturer for repair instructions and 

doing the repair. We are considering 

similar rulemaking action on Models 

A319 and A321 airplanes. You may 

obtain further information by examining 

the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued All Operators Telex 

(AOT) A300–55A6047, Revision 02, 

dated October 12, 2009; and AOT A310– 

55A2048, Revision 02, dated October 

12, 2009. 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 AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a Note within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 194 products of U.S. 

registry. We also estimate that it would 

take about 4 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$65,960, or $340 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

Airbus: Docket No. FAA–2010–0281; 

Directorate Identifier 2009–NM–184–AD. 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Proposed Rules 16687 

Comments Due Date 

(a) We must receive comments by May 17, 

2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A300 

B4–601, B4–603, B4–620, B4–622, B4–605R, 

B4–622R, F4–605R, F4–622R, and C4–605R 

Variant F airplanes; and Model A310–203, 

–204, –221, –222, –304, –322, –324, and –325 

airplanes; certificated in any category; 

equipped with carbon fiber reinforced plastic 

rudders having part numbers and serial 

numbers listed in Table 1 of this AD. 

TABLE 1—RUDDER INFORMATION

Rudder part No. Affected rudder 

serial No. 

Core density 

24 kg/m3

A554–71500–016–91 ......................................................................................................................................... HF–1017 ........... Yes. 

A554–71500–016–91 ......................................................................................................................................... HF–1020 ........... No. 

A554–71500–016–91 ......................................................................................................................................... HF–1059 ........... No. 

A554–71500–016–91 ......................................................................................................................................... HF–1061 ........... No. 

A554–71500–016–91 ......................................................................................................................................... HF–1064 ........... No. 

A554–71500–014–00 ......................................................................................................................................... HF–1087 ........... Yes. 

A554–71500–014–00 ......................................................................................................................................... HF–1119 ........... Yes. 

A554–71500–016–00 ......................................................................................................................................... HF–1189 ........... Yes. 

A554–71500–016–00 ......................................................................................................................................... HF–1203 ........... Yes. 

A554–71500–016–00 ......................................................................................................................................... HF–1266 ........... Yes. 

A554–71500–026–00 ......................................................................................................................................... TS–1405 ........... No. 

A554–71710–000–00 ......................................................................................................................................... TS–2001 ........... No. 

A554–71710–000–00 ......................................................................................................................................... TS–2004 ........... No. 

A554–71710–000–00 ......................................................................................................................................... TS–2007 ........... No. 

A554–71710–000–00 ......................................................................................................................................... TS–2009 ........... No. 

A554–71710–000–00 ......................................................................................................................................... TS–2011 ........... No. 

A554–71710–000–00 ......................................................................................................................................... TS–2012 ........... No. 

A554–71710–000–00 ......................................................................................................................................... TS–2013 ........... No. 

A554–71710–000–00 ......................................................................................................................................... TS–2014 ........... No. 

A554–71710–000–00 ......................................................................................................................................... TS–2016 ........... No. 

A554–71710–000–00 ......................................................................................................................................... TS–2017 ........... No. 

A554–71710–000–00 ......................................................................................................................................... TS–2018 ........... No. 

A554–71710–000–00 ......................................................................................................................................... TS–2020 ........... No. 

A554–71710–000–00 ......................................................................................................................................... TS–2021 ........... No. 

A554–71710–000–00 ......................................................................................................................................... TS–2022 ........... No. 

A554–71710–000–00 ......................................................................................................................................... TS–2024 ........... No. 

A554–71710–000–00 ......................................................................................................................................... TS–2025 ........... No. 

A554–71710–000–00 ......................................................................................................................................... TS–2026 ........... No. 

A554–71710–000–00 ......................................................................................................................................... TS–2028 ........... No. 

A554–71710–000–00 ......................................................................................................................................... TS–2029 ........... No. 

A554–71710–002–00 ......................................................................................................................................... TS–2031 ........... No. 

A554–71710–002–00 ......................................................................................................................................... TS–2032 ........... No. 

A554–71710–002–00 ......................................................................................................................................... TS–2035 ........... No. 

A554–71710–002–00 ......................................................................................................................................... TS–2040 ........... No. 

A554–71710–002–00 ......................................................................................................................................... TS–2041 ........... No. 

A554–71710–002–00 ......................................................................................................................................... TS–2044 ........... No. 

A554–71710–002–00 ......................................................................................................................................... TS–2046 ........... No. 

A554–71710–004–00 ......................................................................................................................................... TS–2050 ........... No. 

A554–71710–004–00 ......................................................................................................................................... TS–2056 ........... No. 

A554–71710–004–00 ......................................................................................................................................... TS–2058 ........... No. 

A554–71710–004–00 ......................................................................................................................................... TS–2060 ........... No. 

A554–71710–004–00 ......................................................................................................................................... TS–2062 ........... No. 

A554–71710–004–00 ......................................................................................................................................... TS–2065 ........... No. 

A554–71710–004–00 ......................................................................................................................................... TS–2066 ........... No. 

A554–71710–004–00 ......................................................................................................................................... TS–2074 ........... No. 

A554–71710–004–00 ......................................................................................................................................... TS–2075 ........... No. 

A554–71710–004–00 ......................................................................................................................................... TS–2076 ........... No. 

A554–71710–004–00 ......................................................................................................................................... TS–2079 ........... No. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 55: Stabilizers. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Surface defects were visually detected on 

the rudder of one Airbus A319 and one A321 

in-service aeroplane. Investigation has 

determined that the defects reported on both 

rudders corresponded to areas that had been 

reworked in production. The investigation 

confirmed that the defects were the result of 

de-bonding between the skin and honeycomb 

core. Such reworks were also performed on 

some rudders fitted on A310 and A300–600 

aeroplanes. 

An extended de-bonding, if not detected 

and corrected, may degrade the structural 

integrity of the rudder. The loss of the rudder 

leads to degradation of the handling qualities 

and reduces the controllability of the 

aeroplane. 

To address this unsafe condition [this 

EASA AD] requires inspections of specific 

areas and, depending on findings, the 

application of corrective actions for those 

rudders where production reworks have been 

identified. 

This * * * [EASA] AD * * * also requires 

for the vacuum loss hole restoration: 

—A local ultrasonic inspection for reinforced 

area instead of the local thermographic 

inspection, which is maintained for nonreinforced areas, and 

—Additional work performance for rudders 

on which this thermographic inspection 

has been performed in the reinforced area. 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
16688 Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Proposed Rules 

The inspections include vacuum loss 

inspections and elasticity laminate checker 

inspections for defects including de-bonding 

between the skin and honeycomb core of the 

rudder, and ultrasonic inspections for 

rudders on which temporary restoration with 

resin or permanent vacuum loss hole 

restoration has been performed. The 

corrective action is contacting the 

manufacturer for repair instructions and 

doing the repair. We are considering similar 

rulemaking action on Models A319 and A321 

airplanes. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions and Compliance 

(g) For rudders with a honeycomb core 

density of 24 kg/m3, as identified in Table 1 

of this AD, do the actions required in 

paragraphs (g)(1) through (g)(10) of this AD, 

in accordance with Airbus All Operators 

Telex (AOT) A310–55A2048 or A300– 

55A6047, both Revision 02, both dated 

October 12, 2009, as applicable. 

(1) In the reinforced location: Within 8 

months after the effective date of this AD, do 

a vacuum loss inspection to detect defects 

including de-bonding. 

(2) In the trailing edge location: Within 24 

months after the effective date of this AD, do 

an elasticity laminate checker inspection to 

detect defects including de-bonding. 

(3) Repeat the inspection required by 

paragraph (g)(2) of this AD two times at 

intervals not to exceed 4,500 flight cycles, 

but not fewer than 4,000 flight cycles from 

the last inspection. 

(4) In other locations (lower rib/upper 

edge/leading edge/other locations): Within 8 

months after the effective date of this AD, do 

an elasticity laminate checker inspection to 

detect defects including de-bonding. 

(5) Repeat the inspection required by 

paragraph (g)(4) of this AD at intervals not to 

exceed 8 months from the last inspection. 

(6) Within 24 months after the effective 

date of this AD, do a vacuum loss inspection 

on the other locations (lower rib/upper edge/ 

leading edge/other locations) to detect 

defects including de-bonding. 

(7) Accomplishment of the inspection 

required by paragraph (g)(6) of this AD 

terminates the initial and repetitive 

inspections required by paragraphs (g)(4) and 

(g)(5) of this AD. 

(8) If any defect is found during any 

inspection required by paragraph (g)(1), 

(g)(2), (g)(4), or (g)(6) of this AD, before 

further flight, contact Airbus for repair 

instructions and do the repair. 

(9) If no defects are found during any 

inspection required by paragraphs (g)(1) and 

(g)(6) of this AD, before further flight, restore 

the vacuum loss holes with temporary 

restoration with self-adhesive patches, 

temporary restoration with resin, or 

permanent restoration with resin and surface 

protection, and repeat the inspection 

required by paragraph (g)(3) of this AD at 

intervals not to exceed 4,500 flight cycles 

until permanent restoration is completed. 

(10) If any defect is found during any 

inspection required by paragraphs (g)(1), 

(g)(2), (g)(4), and (g)(6) of this AD, at the 

applicable time in paragraph (g)(10)(i) or 

(g)(10)(ii) of this AD: Report the inspection 

results to Airbus SAS, SEER1/SEER2/SEER3, 

Customer Services, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; fax 

+33 (0) 5 61 93 28 73; or e-mail to 

region1.StructureRepairSupport@airbus.com, 

region2.StructureRepairSupport@airbus.com, 

or 

region3.StructureRepairSupport@airbus.com. 

(i) Inspections done before the effective 

date of this AD: Within 30 days after the 

effective date of this AD. 

(ii) Inspections done on or after the 

effective date of this AD: Within 30 days after 

accomplishment of the inspection. 

(11) If no defect is found during any 

inspection required by paragraphs (g)(1), 

(g)(2), (g)(4), and (g)(6) of this AD, at the 

applicable time in (g)(10)(i) or (g)(10)(ii): 

Report the inspection results to Airbus SAS, 

Jean-Luc BOITEUX, SEES1, Customer 

Services, fax (0) 5 61 93 36 14; or e-mail to 

jean-luc.j.boiteux@airbus.com. 

(h) For rudders not having a honeycomb 

core density of 24 kg/m3, as identified in 

Table 1 of this AD, do the actions required 

in paragraph (h)(1) through (h)(10) of this AD 

in accordance with Airbus AOT A310– 

55A2048 or AOT A300–55A6047, both 

Revision 02, both dated October 12, 2009, as 

applicable. 

(1) In the reinforced location: Within 8 

months after the rudder has accumulated 

13,000 flight cycles since first installation, or 

within 8 months after the effective date of 

this AD, whichever occurs later, do a vacuum 

loss inspection to detect defects including 

de-bonding. 

(2) In the trailing edge location: Within 24 

months after the rudder has accumulated 

13,000 flight cycles since first installation, or 

within 24 months after the effective date of 

this AD, whichever occurs later, do an 

elasticity laminate checker inspection to 

detect defects including de-bonding. 

(3) Repeat the inspection required by 

paragraph (h)(2) of this AD two times at 

intervals not to exceed 4,500 flight cycles, 

but not fewer than 4,000 flight cycles from 

the last inspection. 

(4) In other locations (lower rib/upper 

edge/leading edge/other locations): Within 8 

months after the rudder has accumulated 

13,000 flight cycles since first installation, or 

within 8 months after the effective date of 

this AD, whichever occurs later, do an 

elasticity laminate checker inspection to 

detect defects including de-bonding. 

(5) Repeat the inspection required by 

paragraph (h)(4) of this AD at intervals not 

to exceed 8 months from the last inspection. 

(6) Within 24 months after the rudder has 

accumulated 13,000 flight cycles since first 

installation, or within 24 months after the 

effective date of this AD, whichever occurs 

later, do a vacuum loss inspection on the 

other locations (lower rib/upper edge/leading 

edge/other location) to detect defects 

including de-bonding. 

(7) Accomplishment of the inspection 

required by paragraph (h)(6) of this AD 

terminates the initial and repetitive 

inspections required by paragraphs (h)(4) and 

(h)(5) of this AD. 

(8) If any defect is found during any 

inspection required by paragraph (h)(1), 

(h)(2), (h)(4), or (h)(6) of this AD, before 

further flight, contact Airbus for repair 

instructions and do the repair. 

(9) If no defects are found during the 

inspections required by paragraphs (h)(1) and 

(h)(6) of this AD, before further flight, restore 

the vacuum loss holes with the temporary 

restoration with self adhesive patches, 

temporary restoration with resin, or 

permanent restoration with resin and surface 

protection, and repeat the inspection 

required by paragraph (h)(3) of this AD at 

intervals not to exceed 4,500 flight cycles 

until permanent restoration is completed. 

(10) If any defect is found during any 

inspection required by paragraphs (h)(1), 

(h)(2), (h)(4), and (h)(6) of this AD, at the 

applicable time in paragraph (h)(10)(i) or 

(h)(10)(ii) of this AD: Report the inspection 

results to Airbus SAS, SEER1/SEER2/SEER3, 

Customer Services, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; fax 

+33 (0) 5 61 93 28 73; or e-mail to 

region1.StructureRepairSupport@airbus.com, 

region2.StructureRepairSupport@airbus.com, 

or 

region3.StructureRepairSupport@airbus.com. 

(i) Inspections done before the effective 

date of this AD: Within 30 days after the 

effective date of this AD. 

(ii) Inspections done on or after the 

effective date of this AD: Within 30 days after 

accomplishment of the inspection. 

(11) If no defect is found during any 

inspection required by paragraphs (h)(1), 

(h)(2), (h)(4), and (h)(6) of this AD, at the 

applicable time in (h)(10)(i) or (h)(10)(ii): 

Report the inspection results to Airbus SAS, 

Jean-Luc BOITEUX, SEES1, Customer 

Services, fax (0) 5 61 93 36 14; or e-mail to 

jean-luc.j.boiteux@airbus.com. 

(i) Actions done before the effective date of 

this AD, in accordance with the service 

information listed in Table 2 of this AD, are 

acceptable for compliance with the 

requirements of paragraphs (g) and (h) of this 

AD for the areas inspected, for any rudder 

listed in Table 1 of this AD. 

(j) Additional areas requiring inspection for 

all airplanes are defined in Airbus AOT 

A310–55A2048 or AOT A300–55A6047, both 

Revision 02, both dated October 12, 2009, as 

applicable. For these additional areas, do the 

actions required in paragraphs (g) and (h) of 

this AD, as applicable, at the times specified 

in those paragraphs. For all areas, do the 

repetitive inspections required by paragraphs 

(g) and (h) of this AD as applicable at the 

times specified in those paragraphs. 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Proposed Rules 16689 

TABLE 2—CREDIT SERVICE INFORMATION

Airbus AOT— Revision— Dated— 

A300–55A6047 ............................................................ Original ........................................................................ May 11, 2009. 

A300–55A6047 ............................................................ 01 ................................................................................ July 8, 2009. 

A310–55A2048 ............................................................ Original ........................................................................ May 11, 2009. 

A310–55A2048 ............................................................ 01 ................................................................................ July 8, 2009. 

(k) For rudders on which temporary 

restoration with resin or permanent vacuum 

loss hole restoration has been done in 

accordance with the applicable service 

bulletin in Table 2 of this AD, as required in 

paragraph (g)(9) or (h)(9) of this AD, before 

the effective date of this AD: Within 4,500 

flight cycles from the restoration date, do an 

ultrasonic inspection for defects, including 

debonding of the reinforced area, in 

accordance with Airbus AOT A310–55A2048 

or AOT A300–55A6047, both Revision 02, 

both dated October 12, 2009, as applicable. 

If any defect is found, before further flight, 

contact Airbus for repair instructions and do 

the repair. 

(l) After the effective date of this AD, no 

person may install any rudder listed in Table 

1 of this AD on any airplane, unless the 

rudder has been inspected and all applicable 

corrective actions have been done in 

accordance with paragraph (g) or (h) of this 

AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(m) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

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

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2125; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards 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). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(n) Refer to MCAI European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2010–0002, dated January 5, 2010; 

and Airbus AOT A310–55A2048, Revision 

02, dated October 12, 2009, or Airbus AOT 

A300–55A6047, Revision 02, dated October 

12, 2009; for related information. 

Issued in Renton, Washington, on March 

25, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–7459 Filed 4–1–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0279; Directorate 

Identifier 2009–NM–148–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318, A319, A320, and A321 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: Surface defects were 

visually detected on the rudder of one 

A319 and one A321 in-service 

aeroplane. Investigation has determined 

that the defects reported on both 

rudders corresponded to areas that had 

been reworked in production. The 

investigation confirmed that the defects 

were a result of de-bonding between the 

skin and honeycomb core. An extended 

de-bonding, if not detected and 

corrected, may degrade the structural 

integrity of the rudder. The loss of the 

rudder leads to degradation of the 

handling qualities and reduces the 

controllability of the aeroplane. 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by May 17, 2010. 

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 W12–40, 1200 New Jersey 

Avenue, SE., Washington, DC, between 

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

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus, 

Airworthiness Office—EAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; fax +33 5 61 93 44 51; 

e-mail: account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. You may review 

copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington. For 

information on the availability of this 

material at the FAA, call 425–227–1221 

or 425–227–1152. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

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

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 


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