Federal Register / Vol. 72, No. 94 / Wednesday, May 16, 2007 / Proposed Rules 27493 

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: 

Empresa Brasileira de Aeronautica S.A. 

(EMBRAER): Docket No. FAA–2007–

28158; Directorate Identifier 2007–NM–

018–AD. 

Comments Due Date 

(a) We must receive comments by June 15, 

2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to EMBRAER Model 

EMB–135BJ airplanes, certificated in any 

category; except those that have previously 

accomplished EMBRAER Service Bulletin 

145LEG–38–0015 or 145LEG–38–0020. 

Subject 

(d) Water/Waste. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

It has been found cases in which the drain 

mast of the water and waste system does not 

meet the SFAR–88 (Special Federal Aviation 

Regulation No. 88) requirements. In case of 

fuel leakage or fuel vapor release, the 

proximity of this mast with the fuel tank may 

cause fuel ignition, leading to a possible tank 

explosion. 

The MCAI requires replacement of the water 

and waste system drain masts by new ones 

bearing a new part number (P/N). 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within 5,000 flight hours or 4 years 

after the effective date of this AD, whichever 

occurs first, replace the water and waste 

system drain masts with P/N 9402.369.00674 

by new ones bearing a P/N 9402.369.00675, 

according to the detailed instructions and 

procedures described in EMBRAER Service 

Bulletin 145LEG–38–0013, dated March 24, 

2006. 

(2) The accomplishment of the detailed 

instructions and procedures described in 

EMBRAER Service Bulletin 145LEG–38–

0015, dated November 25, 2005; or 145LEG–

38–0020, dated February 3, 2006, are 

acceptable for compliance with the 

requirements of this AD. 

FAA AD Differences 

Note: 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: Todd Thompson, 

Aerospace Engineer; 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 227–1175; fax (425) 227–1149. Before 

using any AMOC approved in accordance 

with § 39.19 on any airplane to which the 

AMOC applies, notify the appropriate 

principal inspector in the FAA Flight 

Standards Certificate Holding District Office. 

(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 Brazilian Airworthiness 

Directive 2007–01–04, effective January 29, 

2007, and the service bulletins listed in Table 

1 of this AD, for related information. 

TABLE 1.—SOURCES OF RELATED INFORMATION

EMBRAER Service Bulletin— Revision level— Dated—

145LEG–38–0005 .............................................. 02 ...................................................................... November 20, 2003. 

145LEG–38–0013 .............................................. Original ............................................................. March 24, 2006. 

145LEG–38–0015 .............................................. Original ............................................................. November 25, 2005. 

145LEG–38–0020 .............................................. Original ............................................................. February 3, 2006. 

Issued in Renton, Washington, on May 7, 

2007. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–9394 Filed 5–15–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28159; Directorate 

Identifier 2006–NM–257–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300–600 Series Airplanes and Model 

A310 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to certain 

Airbus Model A300–600, A310–200, 

and A310–300 series airplanes. The 

existing AD currently requires 

inspecting for certain serial numbers on 

elevators, and doing a detailed 

inspection, visual inspection with a 

low-angle light, and tap-test inspection 

of the upper and lower surfaces of the 

external skins on certain identified 

elevators for any damage (i.e., 

debonding of the graphite fiber 

reinforced plastic/Tedlar film 

protection, bulges, debonding of the 

honeycomb core to the carbon fiber 

reinforced plastic, abnormal surface 

reflections, and torn-out plies), and 

doing corrective actions if necessary. 

This proposed AD would also require 

inspecting for damage of the identified 

elevators in accordance with a new 

repetitive inspection program, at new 

repetitive intervals; and would provide 


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27494 Federal Register / Vol. 72, No. 94 / Wednesday, May 16, 2007 / Proposed Rules 

an optional terminating action for the 

repetitive inspections. This proposed 

AD results from reports of damage 

caused by moisture/water inside the 

elevator. We are proposing this AD to 

detect and correct debonding of the 

skins on the elevators, which could 

cause reduced structural integrity of an 

elevator and reduced controllability of 

the airplane. 

DATES: We must receive comments on 

this proposed AD by June 15, 2007. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9:00 a.m. and 5:00 p.m., 

Monday through Friday, except Federal 

holidays. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

proposed AD. 

FOR FURTHER INFORMATION CONTACT: Tom 

Stafford, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–1622; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include the docket 

number ‘‘Docket No. FAA–2007–28159; 

Directorate Identifier 2006–NM–257–

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the proposed AD. We will consider all 

comments received by the closing date 

and may amend the proposed AD in 

light of those comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed AD. 

Using the search function of that web 

site, anyone can find and read the 

comments in any of our dockets, 

including the name of the individual 

who sent the comment (or signed the 

comment on behalf of an association, 

business, labor union, etc.). You may 

review the DOT’s complete Privacy Act 

Statement in the Federal Register 

published on April 11, 2000 (65 FR 

19477–78), or you may visit http:// 

dms.dot.gov. 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System receives them. 

Discussion 

On December 15, 2005, we issued AD 

2005–26–17, amendment 39–14438 (70 

FR 77301, December 30, 2005), for 

certain Airbus Model A300–600, A310–

200, and A310–300 series airplanes. 

That AD requires inspecting for certain 

serial numbers on elevators, and doing 

a detailed inspection, visual inspection 

with a low-angle light, and tap-test 

inspection of the upper and lower 

surfaces of the external skins on certain 

identified elevators for any damage (i.e., 

debonding of the GFRP (graphite fiber 

reinforced plastic)/Tedlar film 

protection, bulges, debonding of the 

honeycomb core to the carbon fiber 

reinforced plastic, abnormal surface 

reflections, and torn-out plies), and 

doing corrective actions if necessary. 

That AD resulted from reports of 

debonded skins on the elevators. We 

issued that AD to detect and correct 

debonding of the skins on the elevators, 

which could cause reduced structural 

integrity of an elevator and reduced 

controllability of the airplane. 

Actions Since Existing AD Was Issued 

The preamble to AD 2005–26–17 

specified that we considered the 

requirements ‘‘interim action’’ and that 

the manufacturer was developing a 

modification to address the unsafe 

condition. That AD explained that we 

may consider further rulemaking if a 

modification is developed, approved, 

and available. The manufacturer now 

has developed such a modification, and 

we have determined that further 

rulemaking is indeed necessary; this 

proposed AD follows from that 

determination. 

In addition, the European Aviation 

Safety Agency (EASA), which is the 

Technical Agent for the Member States 

of the European Union, has issued 

EASA airworthiness directive 2006–

0289, dated November 2, 2006, which 

renders mandatory a new scheduled 

inspection program to address the 

unsafe condition. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A300–55–6039 (for Model A300–600 

series airplanes) and Service Bulletin 

A310–55–2040 (for Model A310 series 

airplanes), both including Appendix 01, 

both dated June 7, 2006. The service 

bulletins describe procedures for 

determining the serial number of the 

elevator. For elevators with an affected 

serial number, the service bulletins 

describe procedures for the following 

actions: 

• A repetitive detailed visual 

inspection of the external surfaces of the 

GRFP/Tedlar film protection on the 

upper and lower skin panels to detect 

damage (breaks, disbonding, bulges, 

cracks, plies torn out or peeled off, 

discontinuity) of the film. For any 

damage, the service bulletins specify the 

related investigative action of a local 

tap-test for disbonding of the bulge and 

the surrounding area. The service 

bulletins specify the corrective action 

for disbonding as removing any 

disbonded GFRP/Tedlar film before 

doing the thermographic inspection. 

• A repetitive thermographic 

inspection of the upper and lower skin 

panels to detect any potential water 

indication inside the panel’s 

honeycomb core; and related 

investigative and corrective actions if 

necessary. 

• Related investigative and corrective 

actions following the thermographic 

inspection are: 

Æ For no water indication: Evaluation 

of the external GFRP/Tedlar film 

protection for damage (debonding, 

bulges, cracks, or plies torn out or 

peeled off), and repair with pore filler 

if necessary. 

Æ For water indication: A tap-test on 

the area to detect damage and 

honeycomb debonding; do a damage 

and repair evaluation according to 

instructions in the structural repair 

manual (SRM); evaluation of the 

external GFRP/Tedlar film for damage 

according to the SRM; and repair with 

pore filler and/or replacement of the 

honeycomb core if necessary, or the 

optional terminating action (described 


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below). If any damage exceeds certain 

limits specified in the SRM, the service 

bulletins specify contacting Airbus for 

repair instructions. 

• Reporting inspection results to 

Airbus. 

• Repairing the external GFRP/Tedlar 

film with pore filler. 

Airbus has also issued Service 

Bulletin A300–55–6040 (for Model 

A300–600 series airplanes) and Service 

Bulletin A310–55–2041 (for Model 

A310 series airplanes), both dated June 

5, 2006. The service bulletins describe 

procedures for replacing the external 

GFRP/Tedlar film with an application of 

pore filler on the whole elevator 

external surface. Doing this replacement 

eliminates the need for the repetitive 

inspections. 

Accomplishing the actions specified 

in the service information is intended to 

adequately address the unsafe 

condition. The EASA mandated the 

service information and issued EASA 

airworthiness directive 2006–0289, 

dated November 2, 2006, to ensure the 

continued airworthiness of these 

airplanes in the European Union. 

FAA’s Determination and Requirements 

of the Proposed AD 

These airplane models are 

manufactured in France and type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. As described in FAA Order 

8100.14A, ‘‘Interim Procedures for 

Working with the European Community 

on Airworthiness Certification and 

Continued Airworthiness,’’ dated 

August 12, 2005, the EASA has kept the 

FAA informed of the situation described 

above. We have examined the EASA’s 

findings, evaluated all pertinent 

information, and determined that AD 

action is necessary for airplanes of this 

type design that are certificated for 

operation in the United States. 

This proposed AD would supersede 

AD 2005–26–17 and would retain the 

requirements of the existing AD. This 

proposed AD would also require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Difference between the Proposed AD 

and the EASA Airworthiness Directive.’’

Difference Between the Proposed AD 

and the EASA Airworthiness Directive 

The EASA airworthiness directive 

specifies to contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions using 

a method that we or the EASA (or its 

delegated agent) approve. In light of the 

type of repair that would be required to 

address the unsafe condition, and 

consistent with existing bilateral 

airworthiness agreements, we have 

determined that, for this proposed AD, 

a repair we or the EASA approve would 

be acceptable for compliance with this 

proposed AD. 

Changes to Existing AD 

We have clarified the applicability of 

the existing AD to more closely match 

the language of the applicability of the 

EASA airworthiness directive. 

Paragraph (g) of the existing AD 

specifies making repairs or doing 

alternative inspections using a method 

approved by either the FAA or the 

Direction Ge ́ne ́rale de l’Aviation Civile 

(DGAC) (or its delegated agent). The 

EASA has assumed responsibility for 

the airplane models subject to this 

proposed AD. Therefore, we have 

revised paragraph (g) of this proposed 

AD to specify making repairs or doing 

alternative inspections using a method 

approved by the FAA, the DGAC (or its 

delegated agent), or the EASA (or its 

delegated agent). 

Clarification of Inspection Terminology 

In this proposed AD, the ‘‘detailed 

visual inspection’’ specified in the 

Airbus service bulletin is referred to as 

a ‘‘detailed inspection.’’ We have 

included the definition for a detailed 

inspection in a note in the proposed AD. 

Interim Action 

We consider this proposed AD 

interim action. We are currently 

considering requiring the optional 

terminating action of replacing the 

external GFRP/Tedlar film with an 

application of pore filler on the whole 

elevator external surface, which would 

constitute terminating action for the 

repetitive inspections required by this 

AD action. 

Costs of Compliance 

This proposed AD would affect about 

142 airplanes of U.S. registry. The 

following table provides the estimated 

costs for U.S. operators to comply with 

this proposed AD. The average labor 

rate is $80 per work hour. 

ESTIMATED COSTS

Action Work hours Parts Cost per airplane Fleet cost 

Inspection for serial number (required by AD 2005–

26–17).

1 ..................................... $0 ....... $80 ................................. $11,360. 

Repetitive inspections (required by AD 2005–26–

17).

3 ..................................... 0 ......... $240, per inspection 

cycle.

$34,080, per inspection 

cycle. 

New repetitive inspection program (new proposed 

action).

Between 8 and 12 .......... 0 ......... Between $640 and $960, 

per inspection cycle.

Between $90,880 and 

$136,320, per inspection cycle. 

Replacement (optional terminating/new proposed 

action).

48 ................................... 90 ....... $3,930 ............................ $558,060. 

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 have determined that this 

proposed AD would not have federalism 

implications under Executive Order 


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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 that the 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. See the ADDRESSES section 

for a location to examine the regulatory 

evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, 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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–14438 (70 

FR 77301, December 30, 2005) and 

adding the following new airworthiness 

directive (AD): 

Airbus: Docket No. FAA–2007–28159; 

Directorate Identifier 2006–NM–257–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by June 15, 2007. 

Affected ADs 

(b) This AD supersedes AD 2005–26–17. 

Applicability 

(c) This AD applies to Airbus Model A300–

600 series airplanes and Model A310 series 

airplanes, certificated in any category, 

equipped with carbon fiber reinforced plastic 

(CFRP) elevator skin panels, modified in 

accordance with Airbus Service bulletin 

A310–55–2019 or A300–55–6016 (Airbus 

modification 10861) with graphite fiber 

reinforced plastic (GFRP)/Tedlar film as 

external protection, with part numbers (P/Ns) 

and serial numbers (S/Ns) identified in 

Airbus Service Bulletin A300–55–6039 or 

A310–55–2040, both dated June 7, 2006. 

Unsafe Condition 

(d) This AD results from reports of damage 

caused by moisture/water inside the elevator. 

We are issuing this AD to detect and correct 

debonding of the skins on the elevators, 

which could cause reduced structural 

integrity of an elevator and reduced 

controllability of the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of the Requirements of AD 

2005–26–17 

Inspection for Serial Number, Repetitive 

Inspections, and Corrective Actions 

(f) Within 600 flight hours after February 

3, 2006 (the effective date of AD 2005–26–

17), inspect to determine if the S/N of the 

elevator is listed in Airbus All Operators 

Telex (AOT) A300–600–55A6032, dated June 

23, 2004, or Airbus Service Bulletin A300–

55–6039, dated June 7, 2006 (for Model 

A300–600 series airplanes); or in Airbus AOT 

A310–55A2033, dated June 23, 2004, or 

Airbus Service Bulletin A310–55–2040, 

dated June 7, 2006 (for Model A310 series 

airplanes). 

(1) If the S/N does not match any S/N on 

either AOT or service bulletin S/N list, no 

further action is required by this paragraph. 

(2) If the S/N matches a S/N listed in an 

AOT or service bulletin, before further flight, 

do the actions listed in Table 1 of this AD, 

and any corrective action as applicable, in 

accordance with Airbus AOT A300–600–

55A6032, dated June 23, 2004; or Airbus 

AOT A310–55A2033, dated June 23, 2004; as 

applicable. Repeat the inspections thereafter 

at intervals not to exceed 600 flight hours 

until the inspection required by paragraph (j) 

of this AD is accomplished. Do applicable 

corrective actions before further flight. 

TABLE 1.—REPETITIVE INSPECTIONS

Do a— Of the— For any—

Detailed inspection ............... Elevator upper and lower external skin surfaces ........... Damage (i.e., breaks in the graphite fiber reinforced 

plastic (GFRP)/Tedlar film protection, debonded 

GFRP/Tedlar film protection, bulges, torn-out plies). 

Visual inspection with a lowangle light.Elevator upper and lower external skin surfaces ........... Differences in the surface reflection. 

Tap-test inspection ............... Upper and lower external skin surfaces of the honeycomb core panels in the elevator.Honeycomb core that has debonded from the carbon 

fiber reinforced plastic (CFRP). 

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.’’

Repair Approval 

(g) Where the AOT specified in paragraph 

(f) of this AD says to contact the 

manufacturer for repair instructions, or an 

alternative inspection method: Before further 

flight, repair or do the alternative inspection 

method according to a method approved by 

either the Manager, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate; or the Direction Ge ́ne ́rale de 

l’Aviation Civile (DGAC) (or its delegated 

agent), or the European Aviation Safety 

Agency (EASA) (or its delegated agent). 

Parts Installation 

(h) As of February 3, 2006, no carbon fiber 

elevator having part number (P/N) 

A55276055000 (left-hand side) or P/N 

A55276056000 (right-hand side) may be 

installed on any airplane unless it is 

inspected according to paragraph (f) of this 

AD; or according to paragraph (j) of this AD. 

No Reporting Required for AOT Inspections 

(i) Although the AOTs referenced in 

paragraph (f) of this AD specify to submit 

inspection reports to the manufacturer, this 

AD does not include that requirement. 

New Requirements of This AD 

Revised Inspection Program 

(j) For airplanes with affected S/Ns 

identified in paragraph (f) of this AD: Except 

as provided by paragraph (k) of this AD, 

within 2,000 flight cycles or 18 months after 

the effective date of this AD, whichever 

occurs earlier, do a detailed inspection of the 

external surfaces of the GRFP/Tedlar film 

protection on the upper and lower skin 

panels to detect damage of the film, and a 


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thermographic inspection of the upper and 

lower skin panels to detect any potential 

water indication inside the panel’s 

honeycomb core; do all applicable related 

investigative/corrective actions before further 

flight; and repair the external GFRP/Tedlar 

film with pore filler. Do all actions in 

accordance with the Accomplishment 

Instructions of Service Bulletin A300–55–

6039 (for Model A300–600 series airplanes), 

or Service Bulletin A310–55–2040 (for Model 

A310 series airplanes); both including 

Appendix 01, both dated June 7, 2006. 

Repeat the inspections thereafter at intervals 

not to exceed 2,000 flight cycles or 18 

months, whichever occurs earlier. Where the 

service bulletin says to contact the 

manufacturer for repair instructions: Before 

further flight, repair or do the alternative 

inspection method according to a method 

approved by either the Manager, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate; or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent). Doing the inspections in 

accordance with this paragraph terminates 

the repetitive inspection requirements of 

paragraph (f) of this AD. 

(k) The maximum time between the 

inspection required by paragraph (f) of this 

AD and the first inspection done in 

accordance with paragraph (j) of this AD 

must be no greater than: For the 

thermographic inspection, 2,500 flight hours 

after the last thermographic inspection done 

in accordance with the applicable AOT 

specified in paragraph (f) of this AD; and for 

the tap test, 600 flight hours after the last tap 

test inspection done in accordance with 

paragraph (f) of this AD. 

Report 

(l) Submit a report of the findings (both 

positive and negative) of the inspections 

required by paragraph (j) of this AD to 

Airbus, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France, at the 

applicable time specified in paragraph (l)(1) 

or (l)(2) of this AD. The report must include 

the information in Appendix 01 of Airbus 

Service Bulletin A300–55–6039, or Service 

Bulletin A310–55–2040, both dated June 7, 

2006, as applicable. 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 after the 

effective date of this AD: Submit the report 

within 30 days after the inspection. 

(2) 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. 

Optional Terminating Action 

(m) Replacing the external GFRP/Tedlar 

film with an application of pore filler on the 

whole elevator external surface in accordance 

with Airbus Service Bulletin A300–55–6040 

(for Model A300–600 series airplanes), or 

Service Bulletin A310–55–2041 (for Model 

A310 series airplanes), both dated June 5, 

2006, terminates the repetitive inspection 

requirements of paragraph (j) of this AD, 

provided the replacement is done before 

further flight after accomplishment of Service 

Bulletins A310–55–2040 and A300–55–6039, 

both dated June 7, 2006. 

Alternative Methods of Compliance (AMOCs) 

(n)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

(3) Alternative methods of compliance, 

approved previously in accordance with AD 

2005–26–17, are approved as alternative 

methods of compliance with the 

corresponding provisions of this AD. 

Related Information 

(o) EASA airworthiness directive 2006–

0289, dated November 2, 2006, also 

addresses the subject of this AD. 

Issued in Renton, Washington, on May 7, 

2007. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–9391 Filed 5–15–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28160; Directorate 

Identifier 2007–NM–006–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 757–200 and 757–300 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Boeing Model 757–200 and 757–

300 series airplanes. This proposed AD 

would require installing a copper 

bonding jumper between a ground and 

the clamp on the tube of the forward 

and aft gray water composite drain 

masts. This proposed AD results from a 

report of charred insulation blankets 

and burned wires around the forward 

gray water composite drain mast found 

during an inspection of the forward 

cargo compartment on a Model 767–

300F airplane. We are proposing this 

AD to prevent a fire near a composite 

drain mast and possible disruption of 

the electrical power system due to a 

lightning strike on a composite drain 

mast, which could result in the loss of 

several functions essential for safe 

flight. 

DATES: We must receive comments on 

this proposed AD by July 2, 2007. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

Contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for the service 

information identified in this proposed 

AD. 

FOR FURTHER INFORMATION CONTACT: 

Dave Webber, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6451; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include the docket 

number ‘‘FAA–2007–28160; Directorate 

Identifier 2007–NM–006–AD’’ at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the proposed AD. We will consider all 

comments received by the closing date 

and may amend the proposed AD in 

light of those comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed AD. 


ycherry on PROD1PC64 with PROPOSALS