Federal Register / Vol. 74, No. 135 / Thursday, July 16, 2009 / Proposed Rules 34513 

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: 

328 Support Services GmbH (Formerly, 

AvCraft Aerospace GmbH, Formerly 

Fairchild Dornier GmbH, Formerly 

Dornier Luftfahrt GmbH): Docket No. 

FAA–2009–0616; Directorate Identifier 

2009–NM–070–AD. 

Comments Due Date 

(a) We must receive comments August 17, 

2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all 328 Support 

Services GmbH Dornier Model 328–100 and 

–300 airplanes, certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 25: Equipment/furnishings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

A recent incident has been reported with 

a Dornier 328–100 aeroplane, where the 

right-hand (RH) power lever jammed in 

flight-idle position during the landing rollout. The aeroplane was stopped by excessive 

braking. 

The investigation by the operator revealed 

that the cockpit door locking device Part 

Number 001A252A3914012 had fallen off the 

RH cockpit wall and blocked the RH power/ 

condition lever pulley/cable cluster below 

the door. Although the affected aeroplane 

had been modified, the technical 

investigation showed that a loose Cockpit 

Door Locking device could also occur on 

328–100 and 328–300 aeroplanes with a 

standard installation. 

This condition, if not corrected, could 

cause interference with the engine- and/or 

flight control cables, possibly resulting in 

reduced control of the aeroplane. 

For the reasons described above, this AD 

requires a one-time inspection of the cockpit 

door locking device and the surrounding area 

[for proper installation] and the reporting of 

all findings to the TC [type certificate] 

holder. This AD is considered to be an 

interim action and the retrofit of a new 

design may be implemented later. 

The corrective action is re-torquing the 

attachment screws. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within 3 months after the effective date 

of this AD, do a detailed visual inspection of 

the cockpit door locking device and the 

surrounding area for proper installation, in 

accordance with the Accomplishment 

Instructions of 328 Support Services Service 

Bulletin SB–328–25–485 or SB–328J–25–235, 

both dated January 28, 2009, as applicable. 

(2) If any discrepancy is found during the 

inspection specified in paragraph (f)(1) of 

this AD, before further flight, do the 

corrective action in accordance with the 

Accomplishment Instructions of 328 Support 

Services Service Bulletin SB–328–25–485 or 

SB–328J–25–235, both dated January 28, 

2009, as applicable. 

(3) Submit a report of the findings (both 

positive and negative) of the inspection 

required by paragraph (f)(1) of this AD to the 

Manager, Attention Dept P1, 328 Support 

Services GmbH, Customer Services, P.O.B. 

1252, D–82231 Wessling, Fed. Rep. of 

Germany; Fax +49 (0) 8153 88111–6565, at 

the applicable time specified in paragraph 

(f)(3)(i) or (f)(3)(ii) of this AD. The report 

must include the inspection results, a 

description of any discrepancies found, the 

airplane serial number, and the number of 

landings and flight hours on the airplane. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(ii) If the inspection was accomplished 

prior to the effective date of this AD: Submit 

the report within 30 days after the effective 

date 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 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Standards, 

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: Tom Groves, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–1503; 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, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2009–0082, dated April 7, 2009; 

and 328 Support Services Service Bulletins 

SB–328–25–485 and SB–328J–25–235, both 

dated January 28, 2009; for related 

information. 

Issued in Renton, Washington, on July 6, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–16940 Filed 7–15–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0642; Directorate 

Identifier 2009–NM–001–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 767 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 

Boeing Model 767 series airplanes. This 

proposed AD would require inspections 

for scribe lines in the fuselage skin at 

skin lap joints, the skin at certain 

external approved repairs, the skin 

around external features such as 

antennas, and the skin at decals; and 

related investigative and corrective 

actions if necessary. This proposed AD 


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34514 Federal Register / Vol. 74, No. 135 / Thursday, July 16, 2009 / Proposed Rules 

results from reports of scribe lines found 

at skin lap joints and butt joints, around 

external repairs and antennas, and at 

locations where external decals had 

been cut. We are proposing this AD to 

detect and correct scribe lines, which 

can develop into fatigue cracks in the 

skin and cause sudden decompression 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by August 31, 2009. 

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 20590, 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, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.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 Management Facility between 9 

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

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

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

Washington 98057–3356; telephone 

(425) 917–6577; fax (425) 917–6590. 

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–2009–0642; Directorate Identifier 

2009–NM–001–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 because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We have received reports indicating 

that scribe lines have been found by 11 

operators on 13 Boeing Model 767 

airplanes. Scribe lines were found at 

skin lap joints, butt joints, around 

external repairs and antennas, and at 

locations where external decals had 

been cut. Many of the scribe lines 

appear to have been made when sealant 

was removed as part of preparing the 

airplane for repainting. The Model 767 

airplanes had accumulated between 

6,300 and 24,600 total flight cycles. 

Although no cracks resulting from 

scribe lines on Model 767 airplanes 

have been reported to Boeing, fatigue 

cracks can develop in the skin at scribe 

line locations. Fatigue cracks, if not 

corrected, could grow large and cause 

sudden decompression of the airplane. 

Related ADs 

This proposed AD is similar to two 

existing ADs. AD 2006–07–12, 

amendment 39–14539 (71 FR 16211, 

March 31, 2006), applies to Boeing 

Model 737–100, –200, –200C, –300, 

–400, and –500 series airplanes. AD 

2007–19–07, amendment 39–15198 (72 

FR 60244, October 24, 2007), applies to 

all Boeing Model 757–200, –200PF, and 

–200CB series airplanes. Those ADs 

require inspections to detect scribe lines 

in the fuselage skin at certain lap joints, 

butt joints, external repair doublers, and 

other areas; and related investigative/ 

corrective actions if necessary. Those 

actions resulted from reports of fuselage 

skin cracks adjacent to the skin lap 

joints on airplanes that had scribe lines. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 767–53A0193, Revision 

1, dated April 9, 2009. The service 

bulletin describes procedures for 

exploratory detailed inspections to 

detect scribe lines along skin lap joints, 

external features, external approved 

repairs, and decals. The service bulletin 

specifies removing paint and sealant 

from affected areas before the initial 

exploratory inspection. The compliance 

times for the exploratory inspections are 

25,000, 37,500, and 50,000 total flight 

cycles (depending on the inspection 

location) plus the first scribe line 

inspection opportunity; or within 4,000 

flight cycles after the date of the service 

bulletin; whichever occurs later. 

The service bulletin specifies related 

investigative actions that include 

performing high frequency eddy current 

or ultrasonic inspections of the scribe 

lines to detect cracks, and the service 

bulletin specifies corrective actions as 

either repairing scribe lines and cracks 

or contacting Boeing for repair 

instructions and making the repair. The 

service bulletin specifies to repair 

cracks before further flight. 

The service bulletin specifies 

repairing scribe lines before further 

flight, except when a limited return to 

service (LRTS) program for qualifying 

scribe lines would allow return to 

service for a limited period before scribe 

lines are repaired. The LRTS program 

includes repetitive inspections to detect 

cracks where scribe lines are found. To 

qualify for an LRTS program, scribe 

lines must meet certain criteria based on 

their depth and location. The service 

bulletin specifies contacting Boeing for 

final repair instructions, which would 

eliminate the need for the repetitive 

inspections of the LRTS program. The 

repetitive interval for the LRTS program 

is 1,500 to 9,000 flight cycles, 

depending on the depth and location of 

the scribe lines and the configuration of 

the airplane. 

The service bulletin notes that certain 

inspections would not be required 

under the following conditions: 

• The airplane had never been 

stripped or repainted. 

• The airplane had never been 

stripped or repainted under the wing-tobody fairings. 

• No sealant had been removed 

except in accordance with the specified 

sealant removal processes as given in 

Appendix A of the service bulletin. 

The service bulletin specifies 

submitting the exploratory inspection 

results to Boeing. 


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Federal Register / Vol. 74, No. 135 / Thursday, July 16, 2009 / Proposed Rules 34515 

FAA’s Determination and Requirements 

of This Proposed AD 

We are proposing this AD because we 

evaluated all relevant information and 

determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. This proposed AD would 

require accomplishing the actions 

specified in the service information 

described previously, except as 

discussed under ‘‘Differences Between 

the Proposed AD and Service Bulletin.’’ 

This proposed AD would also require 

sending the results of the exploratory 

inspections to Boeing. 

Differences Between the Proposed AD 

and Service Bulletin 

The service bulletin specifies to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions in 

one of the following ways: 

• Using a method that we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by an 

Authorized Representative for the 

Boeing Commercial Airplanes 

Delegation Option Authorization 

Organization whom we have authorized 

to make those findings. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 367 airplanes of U.S. 

registry. The following table provides 

the estimated costs for U.S. operators to 

comply with this proposed AD. 

TABLE—ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts Cost per 

product 

Number of 

U.S.- 

registered 

airplanes 

Fleet cost 

Exploratory Inspections ................ 340 $80 None ............................................. $27,200 367 $9,982,400 

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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance 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: 

Boeing: Docket No. FAA–2009–0642; 

Directorate Identifier 2009–NM–001–AD. 

Comments Due Date 

(a) We must receive comments by August 

31, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 767– 

200, –300, –300F, and –400ER series 

airplanes, certificated in any category, as 

identified in Boeing Alert Service Bulletin 

767–53A0193, Revision 1, dated April 9, 

2009. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from reports of scribe 

lines found at skin lap joints, butt joints, 

around external repairs and antennas, and at 

locations where external decals had been cut. 

We are issuing this AD to detect and correct 

scribe lines, which can develop into fatigue 

cracks in the skin and cause sudden 

decompression of the airplane. 

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. 

Inspection 

(g) At the applicable times specified in 

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

Alert Service Bulletin 767–53A0193, 

Revision 1, dated April 9, 2009, except as 

provided in paragraph (h) of this AD, do 

detailed exploratory inspections for scribe 

lines of skin lap joints, butt joints, around 

external repairs and antennas, and at 

locations where external decals may have 

been cut. Do all applicable related 

investigative and corrective actions at the 

times specified in the service bulletin, by 

accomplishing all actions specified in the 

Accomplishment Instructions of the service 

bulletin, except as provided by paragraph (i) 

of this AD. 

Note 1: The inspection exemptions noted 

in paragraph 1.E. of Boeing Alert Service 

Bulletin 767–53A0193, Revision 1, dated 

April 9, 2009, apply to this AD. 

Exceptions to Service Bulletin Specifications 

(h) Where Boeing Alert Service Bulletin 

767–53A0193, Revision 1, dated April 9, 

2009, specifies a compliance time after ‘‘the 


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original issue date on this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(i) Where Boeing Alert Service Bulletin 

767–53A0193, Revision 1, dated April 9, 

2009, specifies to contact Boeing for 

appropriate action, accomplish applicable 

actions before further flight using a method 

approved in accordance with the procedures 

specified in paragraph (l) of this AD. 

Report 

(j) At the applicable time specified in 

paragraph (j)(1) or (j)(2) of this AD: Submit 

a report of the findings (both positive and 

negative) of the inspections required by 

paragraph (g) of this AD. Operators may use 

the reporting form contained in Appendixes 

B and C, as applicable, of Boeing Alert 

Service Bulletin 767–53A0193, Revision 1, 

dated April 9, 2009. Send the report to 

Boeing Commercial Airplanes, P.O. Box 

3707, Seattle, Washington 98124–2207. The 

report must contain, at a minimum, the 

inspection results, a description of any 

discrepancies found, the airplane serial 

number, and the number of flight cycles and 

flight hours on the airplane. 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 contained in this AD and has 

assigned OMB Control Number 2120–0056. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

Credit for Actions Accomplished Previously 

(k) Actions accomplished previously in 

accordance with Boeing Alert Service 

Bulletin 767–53A0193, dated November 25, 

2008, are considered acceptable for 

compliance with the applicable actions 

specified in this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(l)(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: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6577; fax (425) 

917–6590. Or, e-mail information to 9-ANMSeattle-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 an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who 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 July 2, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–16872 Filed 7–15–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0613; Directorate 

Identifier 2009–NM–013–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310–221, –222, –322, –324, and –325 

Airplanes, and Model A300B4–620, B4– 

622, B4–622R, F4–605R, and F4–622R 

Airplanes, Equipped With Pratt & 

Whitney PW4000 or JT9D–7R4 Series 

Engines 

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: 

During the year 2000, life extension 

exercise programs were launched for Airbus 

A310 and A300–600 aircraft. Certification of 

Extended Service Goal (ESG) is based on 

analysis, except for fan cowl and thrust 

reverser (T/R) latches, which are always 

certified by tests. 

* * * testing of the T/R door centre latch has 

shown that this does not meet the 

requirements for ESG. 

* * * * * 

The unsafe condition is possible failure 

of the T/R latch and detachment of the 

T/R from the airplane, which could 

result in structural damage and 

consequent reduced controllability of 

the airplane. 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 August 17, 2009. 

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 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. 

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 


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