34518 Federal Register / Vol. 74, No. 135 / Thursday, July 16, 2009 / Proposed Rules 

Comments Due Date 

(a) We must receive comments by August 

17, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A310– 

221, –222, –322, –324, and –325 airplanes, 

and Model A300B4–620, B4–622, B4–622R, 

F4–605R, and F4–622R airplanes, all serial 

numbers; certificated in any category; 

equipped with Pratt & Whitney PW4000 or 

JT9D–7R4 series engines. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 78: Engine exhaust. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

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. 

Currently, the Airworthiness Limitation 

Item (ALI) task 54–50–28 for engine pylon T/ 

R hinges requires inspection every [1,200] 

Flight Cycles (FC). An analysis performed by 

Airbus shows that forward and aft T/R door 

latches have been demonstrated successful 

for ESG, with inspection task every 1200 FC. 

However, testing of the T/R door centre latch 

has shown that this does not meet the 

requirements for ESG. 

For the reason described above, this EASA 

AD requires the replacement of the T/R 

centre latches with serialized latches on LH 

[left hand] and RH [right hand] engines and 

repetitive inspections [for cracking] of the 

serialized latches. In addition, this AD 

introduces a life limit of 18000 FC for the 

serialized centre latches. 

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 corrective 

action includes replacing the T/R latch if any 

surface crack is found during any inspection. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Before the accumulation of 30,000 total 

flight cycles since first flight of the airplane, 

or within 1,200 flight cycles after the 

effective date of this AD, whichever occurs 

later: Replace the non-serialized T/R center 

latch LH (left hand) and RH (right hand) 

sides, having part number (P/N) 221D0029– 

11 and P/N 221D0029–13, with a serialized 

T/R center latch having P/N 221D0029–15 in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A300–78–6029 or A310–78–2030, 

both including Appendix 1, both dated 

October 3, 2008; as applicable. 

(2) Within 1,200 flight cycles after 

accomplishing the replacement required by 

paragraph (f)(1) of this AD: Perform an 

inspection for surface cracking of the T/R 

center serialized latches having P/N 

221D0029–15, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–78–6029 

or A310–78–2030, both including Appendix 

1, both dated October 3, 2008; as applicable. 

If any crack is found, before further flight, 

replace the serialized T/R center latch with 

a new serialized T/R center latch in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A300–78–6029 or A310–78–2030, 

both including Appendix 1, both dated 

October 3, 2008; as applicable. Repeat the 

inspection thereafter at intervals not to 

exceed 1,200 flight cycles. 

(3) Before the accumulation of 18,000 total 

flight cycles since accomplishing the most 

recent replacement required by paragraph 

(f)(1) or (f)(2) of this AD: Replace the 

serialized T/R center latch having P/N 

221D0029–15 with a new serialized T/R 

center latch having P/N 221D0029–15 in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A300–78–6029 or A310–78–2030, 

both including Appendix 1, both dated 

October 3, 2008; as applicable. Replacement 

of the center latches does not constitute 

terminating action for the repetitive 

inspections required by paragraph (f)(2) 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 Airplane 

Directorate, 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, 

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 Airworthiness Directive 2008– 

0226, dated December 19, 2008; and Airbus 

Mandatory Service Bulletins A300–78–6029 

and A310–78–2030, both including 

Appendix 1, both dated October 3, 2008; for 

related information. 

Issued in Renton, Washington, on July 2, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–16942 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–2006–25001; Directorate 

Identifier 2006–NM–079–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–600, –700, –700C, –800, 

–900 and –900ER Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for all Boeing Model 737–600, –700, 

–700C, –800, –900 and –900ER series 

airplanes. That supplemental NPRM 

would have required a one-time 

inspection to determine the part 

numbers of the aero/fire seals of the 

blocker doors on the thrust reverser 

torque boxes on the engines, and 

replacing affected aero/fire seals with 

new improved aero/fire seals. This 

action resulted from a report that the top 

3 inches of the aero/fire seals of the 

blocker doors on the thrust reverser 

torque boxes are not fireproof. This 

second supplemental NPRM revises the 

first supplemental NPRM by changing 

the compliance time for the 

replacement. We are proposing this 

second supplemental NPRM to prevent 

a fire in the fan compartment (a fire 

zone) from migrating through the seal to 

a flammable fluid in the thrust reverser 

actuator compartment (a flammable 

fluid leakage zone), which could result 

in an uncontrolled fire. 

DATES: We must receive comments on 

this supplemental NPRM by August 10, 

2009. 


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Federal Register / Vol. 74, No. 135 / Thursday, July 16, 2009 / Proposed Rules 34519 

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, P.O. Box 3707, 

Seattle, Washington 98124–2207; 

telephone 206–544–9990; fax 206–766– 

5682; e-mail DDCS@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: 

Samuel Spitzer, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6510; 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–2006–25001; Directorate Identifier 

2006–NM–079–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 issued a notice of proposed 

rulemaking (NPRM) (the ‘‘first 

supplemental NPRM’’) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to all 

Boeing Model 737–600, –700, –700C, 

–800, and –900 series airplanes. The 

first supplemental NPRM was published 

in the Federal Register on September 3, 

2008 (73 FR 51382). The first 

supplemental NPRM proposed to 

require a one-time inspection to 

determine the part numbers of the aero/ 

fire seals of the blocker doors on the 

thrust reverser torque boxes on the 

engines, and replacing affected aero/fire 

seals with new improved aero/fire seals. 

Actions Since First Supplemental 

NPRM Was Issued 

Since we issued the first 

supplemental NPRM, we have 

determined that it is necessary to 

change the compliance time for the 

replacement action in paragraph (h) 

from ‘‘within 60 months or 8,200 flight 

cycles after the effective date of this 

AD,’’ to ‘‘prior to further flight after 

doing the actions specified in paragraph 

(g) of this AD.’’ Our intent in the first 

supplemental NPRM was to require 

replacement of an affected aero/fire seal 

before further flight after identification. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received on the 

first supplemental NPRM. Boeing 

supports the NPRM. 

Additional Changes to Supplemental 

NPRM 

For clarification purposes, we have 

revised paragraph (h) of this second 

supplemental NPRM to change ‘‘as 

having an affected P/N’’ to ‘‘to have a 

non-fireproof seal.’’ 

We have also added new paragraph 

(d) in this supplemental NPRM to 

identify the Air Transport Association 

of America code. 

FAA’s Determination and Proposed 

Requirements of the Second 

Supplemental NPRM 

We are proposing this second 

supplemental NPRM 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. 

Certain changes described above expand 

the scope of the first supplemental 

NPRM. As a result, we have determined 

that it is necessary to reopen the 

comment period to provide additional 

opportunity for the public to comment 

on this second supplemental NPRM. 

Costs of Compliance 

There are about 2,442 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD. 

ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts Cost per airplane 

Number of 

U.S.- 

registered 

airplanes 

Fleet cost 

Inspection for part number ........... 1 $80 None ............................................. $80 803 $64,240 

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 


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34520 Federal Register / Vol. 74, No. 135 / Thursday, July 16, 2009 / Proposed Rules 

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–2006–25001; 

Directorate Identifier 2006–NM–079–AD. 

Comments Due Date 

(a) We must receive comments by August 

10, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Boeing Model 

737–600, –700, –700C, –800, –900, and 

–900ER series airplanes, certificated in any 

category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 78: Engine exhaust. 

Unsafe Condition 

(e) This AD results from a report that the 

top 3 inches of the aero/fire seals of the 

blocker doors on the thrust reverser torque 

boxes are not fireproof. The Federal Aviation 

Administration is issuing this AD to prevent 

a fire in the fan compartment (a fire zone) 

from migrating through the seal to a 

flammable fluid in the thrust reverser 

actuator compartment (a flammable fluid 

leakage zone), which could result in an 

uncontrolled fire. 

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 To Determine Part Number (P/N) 

(g) Within 60 months or 8,200 flight cycles 

after the effective date of this AD, whichever 

occurs first: Perform a one-time detailed 

inspection to determine the color of the aero/ 

fire seals of the blocker doors on the thrust 

reverser torque boxes on the engines. For any 

aero/fire seal having a completely grey color 

(which is the color of seals with P/N 

315A2245–1 or 315A2245–2), with no red at 

the upper end of the seal, do the actions 

specified in paragraph (h) of this AD. For any 

aero/fire seal having a red color at the upper 

end of the seal (which indicates a different 

part number), no further action is required by 

this AD. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the part number of the correct 

aero/fire seals (P/N 315A2245–7 or –8) can be 

conclusively determined to be installed from 

that review. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirrors, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’ 

Replace the Aero/Fire Seals 

(h) For any aero/fire seal identified during 

the inspection/records check in paragraph (g) 

of this AD to have a non-fireproof seal: Prior 

to further flight after doing the actions 

specified in paragraph (g) of this AD, replace 

the aero/fire seals of the blocker doors on the 

thrust reverser torque boxes on the engines 

with new, improved aero/fire seals in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–78–1074, Revision 1, 

dated September 15, 2005. 

Credit for Actions Done Using Previous 

Service Information 

(i) Replacements done before the effective 

date of this AD in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–78– 

1074, dated April 7, 2005, are acceptable for 

compliance with the requirements of 

paragraph (h) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Seattle Aircraft 

Certification Office, 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: Samuel Spitzer, 

Aerospace Engineer, Propulsion Branch, 

ANM–140S, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

917–6510; fax (425) 917–6590. Or, e-mail 

information to 9-ANM-Seattle-ACO-AMOCRequests@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. 

Issued in Renton, Washington, on July 6, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–16943 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–2009–0611; Directorate 

Identifier 2008–NM–165–AD] 

RIN 2120–AA64 

Airworthiness Directives; 

Construcciones Aeronauticas, S.A. 

(CASA), Model C–212–CB, C–212–CC, 

C–212–CD, and C–212–CE 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: 


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