Federal Register / Vol. 73, No. 188 / Friday, September 26, 2008 / Proposed Rules 55781 

(b) The term award does not include: 

(1) Technical assistance that provides 

services instead of money. 

(2) Loans. 

(3) Loan guarantees. 

(4) Interest subsidies. 

(5) Insurance. 

(6) Direct appropriations. 

(7) Veterans’ benefits to individuals 

(i.e., any benefit to veterans, their 

families, or survivors by virtue of the 

service of a veteran in the Armed Forces 

of the United States). 

§ 182.610 Controlled substance. 

Controlled substance means a 

controlled substance in schedules I 

through V of the Controlled Substances 

Act (21 U.S.C. 812), and as further 

defined by regulation at 21 CFR 1308.11 

through 1308.15. 

§ 182.615 Conviction. 

Conviction means a finding of guilt 

(including a plea of nolo contendere) or 

imposition of sentence, or both, by any 

judicial body charged with the 

responsibility to determine violations of 

the Federal or State criminal drug 

statutes. 

§ 182.620 Cooperative agreement. 

Cooperative agreement means an 

award of financial assistance that, 

consistent with 31 U.S.C. 6305, is used 

to enter into the same kind of 

relationship as a grant (see definition of 

grant in § 182.650), except that 

substantial involvement is expected 

between the Federal agency and the 

recipient when carrying out the activity 

contemplated by the award. The term 

does not include cooperative research 

and development agreements as defined 

in 15 U.S.C. 3710a. 

§ 182.625 Criminal drug statute. 

Criminal drug statute means a Federal 

or non-Federal criminal statute 

involving the manufacture, distribution, 

dispensing, use, or possession of any 

controlled substance. 

§ 182.630 Debarment. 

Debarment means an action taken by 

a Federal agency to prohibit a recipient 

from participating in Federal 

Government procurement contracts and 

covered nonprocurement transactions. 

A recipient so prohibited is debarred, in 

accordance with the Federal Acquisition 

Regulation for procurement contracts 

(48 CFR part 9, subpart 9.4) and agency 

regulations implementing the OMB 

guidance on nonprocurement 

debarment and suspension (2 CFR part 

180, which implements Executive 

Orders 12549 and 12689). 

§ 182.635 Drug-free workplace. 

Drug-free workplace means a site for 

the performance of work done in 

connection with a specific award at 

which employees of the recipient are 

prohibited from engaging in the 

unlawful manufacture, distribution, 

dispensing, possession, or use of a 

controlled substance. 

§ 182.640 Employee. 

(a) Employee means the employee of 

a recipient directly engaged in the 

performance of work under the award, 

including— 

(1) All direct charge employees; 

(2) All indirect charge employees, 

unless their impact or involvement in 

the performance of work under the 

award is insignificant to the 

performance of the award; and 

(3) Temporary personnel and 

consultants who are directly engaged in 

the performance of work under the 

award and who are on the recipient’s 

payroll. 

(b) This definition does not include 

workers not on the payroll of the 

recipient (e.g., volunteers, even if used 

to meet a matching requirement; 

consultants or independent contractors 

not on the payroll; or employees of 

subrecipients or subcontractors in 

covered workplaces). 

§ 182.645 Federal agency or agency. 

Federal agency or agency means any 

United States executive department, 

military department, government 

corporation, government controlled 

corporation, any other establishment in 

the executive branch (including the 

Executive Office of the President), or 

any independent regulatory agency. 

§ 182.650 Grant. 

Grant means an award of financial 

assistance that, consistent with 31 

U.S.C. 6304, is used to enter into a 

relationship— 

(a) The principal purpose of which is 

to transfer a thing of value to the 

recipient to carry out a public purpose 

of support or stimulation authorized by 

a law of the United States, rather than 

to acquire property or services for the 

Federal Government’s direct benefit or 

use; and 

(b) In which substantial involvement 

is not expected between the Federal 

agency and the recipient when carrying 

out the activity contemplated by the 

award. 

§ 182.655 Individual. 

Individual means a natural person. 

§ 182.660 Recipient. 

Recipient means any individual, 

corporation, partnership, association, 

unit of government (except a Federal 

agency) or legal entity, however 

organized, that receives an award 

directly from a Federal agency. 

§ 182.665 State. 

State means any of the States of the 

United States, the District of Columbia, 

the Commonwealth of Puerto Rico, or 

any territory or possession of the United 

States. 

§ 182.670 Suspension. 

Suspension means an action taken by 

a Federal agency that immediately 

prohibits a recipient from participating 

in Federal Government procurement 

contracts and covered nonprocurement 

transactions for a temporary period, 

pending completion of an investigation 

and any judicial or administrative 

proceedings that may ensue. A recipient 

so prohibited is suspended, in 

accordance with the Federal Acquisition 

Regulation for procurement contracts 

(48 CFR part 9, subpart 9.4) and agency 

regulations implementing the OMB 

guidance on nonprocurement 

debarment and suspension (2 CFR part 

180, which implements Executive 

Orders 12549 and 12689). Suspension of 

a recipient is a distinct and separate 

action from suspension of an award or 

suspension of payments under an 

award. 

[FR Doc. E8–22717 Filed 9–25–08; 8:45 am] 

BILLING CODE 3110–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0018; Directorate 

Identifier 2007–NM–145–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 Series Airplanes and Model 

A300–600 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: The FAA is revising an earlier 

NPRM for an airworthiness directive 

(AD) that applies to all Airbus Model 

A310 series airplanes and Model A300– 

600 series airplanes. The original NPRM 

would have required superseding two 

existing ADs. One existing AD applies 

to certain Airbus Model A310 series 

airplanes and currently requires 

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55782 Federal Register / Vol. 73, No. 188 / Friday, September 26, 2008 / Proposed Rules 

repetitive inspections for cracking of the 

flap transmission shafts, and 

replacement of the transmission shafts if 

necessary. That existing AD also 

provides an optional terminating action 

for the repetitive inspections. The other 

existing AD applies to all Airbus Model 

A310 and A300–600 series airplanes 

and currently requires a one-time 

inspection of the trimmable horizontal 

stabilizer actuator, corrective actions if 

necessary, and follow-on repetitive 

tasks. The original NPRM would have 

added revising the Airworthiness 

Limitations Section of the Instructions 

for Continued Airworthiness to 

incorporate new limitations and 

maintenance tasks for aging systems 

maintenance. The original NPRM 

resulted from the manufacturer’s 

determination that life limitations and 

maintenance tasks are necessary in 

order to ensure continued operational 

safety of the affected airplanes. This 

new action revises the original NPRM 

by reducing the initial compliance 

times. We are proposing this 

supplemental NPRM to prevent reduced 

structural integrity of these airplanes 

due to the failure of system components. 

DATES: We must receive comments on 

this supplemental NPRM by October 21, 

2008. 

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 AD, contact Airbus, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France. 

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: Tom 

Stafford, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1622; 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–2008–0018; Directorate Identifier 

2007–NM–145–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 

The FAA issued a notice of proposed 

rulemaking (NPRM) (the ‘‘original 

NPRM’’) to amend 14 CFR part 39 to 

include an AD that supersedes two 

existing ADs: AD 2006–10–11, 

amendment 39–14595 (71 FR 28254, 

May 16, 2006), which applies to certain 

Airbus Model A310 series airplanes; 

and AD 2006–15–10, amendment 39– 

14690 (71 FR 42021, July 25, 2006), 

which applies to all Airbus Model A310 

and A300–600 series airplanes. The 

original NPRM was published in the 

Federal Register on January 14, 2008 

(73 FR 2197). The original NPRM 

applies to all Airbus Model A310 series 

airplanes and Model A300–600 series 

airplanes. The original NPRM proposed 

to retain the requirements of the existing 

ADs. The original NPRM also proposed 

to add revising the Airworthiness 

Limitations Section (ALS) of the 

Instructions for Continued 

Airworthiness (ICA) to incorporate new 

limitations and maintenance tasks for 

aging systems maintenance. 

Actions Since Original NPRM Was 

Issued 

Since the original NPRM was issued, 

we have determined that the initial 

compliance times for the revision 

specified in paragraph (o) of the original 

NPRM need to be reduced. In paragraph 

(o) of the original NPRM, we specified 

that for all tasks ‘‘* * * the initial 

compliance times start from the 

effective date of this AD * * *.’’ 

However, the thresholds specified in 

Airbus A310 ALS Part 4—Aging 

Systems Maintenance, Revision 01, 

dated December 21, 2006; and Airbus 

A300–600 ALS Part 4—Aging Systems 

Maintenance, Revision 01, dated 

December 21, 2006; (which are referred 

to as the appropriate sources of service 

information for accomplishing the 

required actions in paragraph (o) of the 

original NPRM); start from ‘‘* * * the 

initial entry into service of a specific 

maintenance task.’’ 

In order to ensure timely action to 

address the identified unsafe condition, 

we have reduced the initial compliance 

times in order to match the service 

information. We have revised paragraph 

(o) of the supplemental NPRM 

accordingly. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been received on the original NPRM. 

Request To Refer to Latest Revisions of 

Service Bulletins 

Federal Express (FedEx) requests that 

we refer to the latest revision of Airbus 

Service Bulletin A300–27–6044, 

Revision 04, dated September 10, 2001; 

and Airbus Service Bulletin A310–27– 

2089, Revision 02, dated June 28, 2001 

(which are referred to in Table 1 of 

paragraph (k) of the original NPRM as 

the appropriate sources of service 

information for doing the actions 

specified in paragraphs (l), (m), and (n) 

of the original NPRM). FedEx states that 

Airbus Service Bulletin A300–27–6044, 

Revision 05, dated August 29, 2006; and 

Airbus Service Bulletin A310–27–2089, 

Revision 03, dated August 29, 2006; do 

not specify any additional work and 

were primarily issued to adjust the 

service bulletin effectivity as well as to 

provide additional reference data. 

We agree with the commenter to refer 

to Airbus Service Bulletin A300–27– 

6044, Revision 05, dated August 29, 

2006; and Airbus Service Bulletin 

A310–27–2089, Revision 03, dated 

August 29, 2006. We have reviewed the 

service bulletins and determined no 

additional work is required. We have 

revised Table 1 of this supplemental 

NPRM accordingly. 

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Federal Register / Vol. 73, No. 188 / Friday, September 26, 2008 / Proposed Rules 55783 

Request To Clarify Definition of ‘‘New’’ 

FedEx requests that we clarify the 

word ‘‘new’’ specified in paragraph (m) 

of the original NPRM. FedEx states that 

the word ‘‘new’’ pertains to the 

replacement of the trimmable horizontal 

stabilizer actuator (THSA), and the 

replacement could be with a new or 

used (serviceable) THSA provided that 

the THSA has not been operated more 

than 65,000 flight hours or 40,000 flight 

cycles or been in service more than 25 

years since new, whichever occurs first. 

FedEx also states that if an THSA that 

was operated more than 47,000 flight 

hours has been installed, it must be 

inspected in accordance with Airbus 

Service Bulletins A300–27–6044 or 

A310–27–2089 (as specified in 

paragraph (n) of the original NPRM). 

FedEx further states that Airbus is in 

concurrence with FedEx’s comment. 

We agree with the commenter that the 

replacement specified in paragraph (m) 

of this supplemental NPRM could be 

with a new or serviceable THSA. Subpart 4–2 of the Airbus A300–600 and 

A310 ALS Part 4 lists the life limits for 

the operational life of the listed 

components. When a component (e.g., 

the THSA) reaches the earliest of any of 

the life limits in flight hours, flight 

cycles, or calendar time, that component 

has reached the end of its given 

operational life and must be removed 

from the airplane and replaced by 

another unit. It is not necessary that the 

replacement unit/component be ‘‘new.’’ 

The rules of application for the ALS Part 

4 are given in sub-part 4–0 of the ALS. 

It is a requirement that a life-limited 

component not be operated beyond the 

limitation stated in the ALS Part 4–2. 

Thus, for the THSA, as long as none of 

the limits (65,000 flight hours, 40,000 

flight cycles, or 25 years of operation) 

have been exceeded and the component 

is classified ‘‘serviceable,’’ then the 

component can be installed and 

operated on the airplane. Airbus 

Operators Information Telex (OIT) SE 

999.0074/05/BB, dated August 3, 2005, 

provides clarification on these limits. 

We have revised paragraph (m) of this 

supplemental NPRM to clarify that the 

installed part may be ‘‘new’’ or 

‘‘serviceable,’’ and we have added Note 

6 and Note 7 to this supplemental 

NPRM to refer to the OIT for 

clarification of these limits. 

Request To Clarify Starting Point of 25- 

Year Life Limit 

FedEx requests that we clarify the 

starting point for the 25-year life limit 

specified in the Airbus A300–600 and 

A310 ALS Part 4 for THSAs built as 

spare parts and not originally installed 

on airplanes. FedEx suggests that 

operators be required to use the date of 

manufacture of the THSA as 

documented by Goodrich, the original 

equipment manufacturer (OEM) of the 

THSA. FedEx states that it would be 

difficult to determine when the 

component, produced as a spare by 

Goodrich, was first installed on an 

airplane. 

We agree to clarify the starting point 

for the 25-year life limit. The ALS Part 

4 does not provide the calendar limit 

guidance that is provided in Airbus 

Service Information Letter (SIL) 05–008, 

dated July 7, 2006. Airbus issued SIL 

05–008 to give guidance (i.e., a 

calculation method) for life limitations 

in calendar parameters for components 

whose history is partially or completely 

unknown. This calculation method 

could be used by operators when they 

comply with the ALS Parts 4–2 and 4– 

3(a). 

The SIL is intended for use when 

operators cannot retrieve their parts 

history (in flight hours/flight cycles). 

This method provides an estimated 

parts life (flight hours/flight cycles) and 

is very conservative. As suggested in the 

FedEx request, one method employed in 

the life calculation (starting point) is the 

date of manufacture (DOM). The DOM 

is shown in one of the tables and 

examples within the SIL. 

The SIL is not currently referenced in 

the ALS Part 4. However, Airbus has 

issued OIT SE 999.0008/07/LB, dated 

January 16, 2007. Section 4 of the OIT 

advises users of the availability of SIL 

05–008. We have added Note 8 to this 

supplemental NPRM to refer to the OIT 

and SIL for clarification. 

Request To Include New THSA Part 

FedEx requests that we include the 

new configuration of THSA, part 

number (P/N) 47142–323, and its life 

limitation. FedEx states that P/N 47142– 

323 does not have the 25-year life limit 

due to the application of enhanced 

materials and processes used during 

manufacture to reinforce their resistance 

to corrosion. FedEx notes that Airbus 

issued Service Bulletins A300–27–6058 

and A310–27–2100, both dated August 

30, 2007, to introduce this new THSA 

configuration, which does not carry a 

calendar life limit. FedEx further states 

that ALS Part 4 does not address this 

THSA configuration. 

We do not agree to include the new 

THSA part number. We acknowledge 

that Airbus Service Bulletins A300–27– 

6058 (for Model A300–600 airplanes) 

and A310–27–2100 (for Model A310 

airplanes) specify procedures to install 

THSA P/N 47142–323. However, Airbus 

has not published a revised inspection 

task that will apply to P/N 47142–323 

to address the corrosion issue. After this 

task has been published, operators may 

request an alternative method of 

compliance (AMOC) according to the 

provisions of paragraph (r) of this 

supplemental NPRM. We have not 

revised this supplemental NPRM in this 

regard. 

Request To Allow Additional 

Compliance Time 

FedEx requests that we add a grace 

period of 1,200 flight hours for Task 

Number 274411–12–1. FedEx states that 

the task is contained within Airbus 

A310 ALS Part 4—Aging Systems 

Maintenance, Revision 01, dated 

December 21, 2006; and Airbus A300– 

600 ALS Part 4—Aging Systems 

Maintenance, Revision 01, dated 

December 21, 2006; which were referred 

to in paragraph (o) of the original NPRM 

for the incorporation of new limitations 

and maintenance tasks for aging systems 

maintenance. FedEx states that the task 

establishes a threshold for 

accomplishment at 47,000 flight hours 

or 20 years, whichever occurs first, but 

does not provide a grace period for the 

inspection on actuators that have 

exceeded 20 years in service but not yet 

reached 25 years in service (the 

established life limit of the THSA). 

FedEx suggests a grace period of 1,200 

flight hours to provide sufficient time to 

sequence airplanes through 

maintenance for accomplishment of this 

THSA inspection at the new established 

threshold. 

We agree that a grace period is 

necessary. In accordance with paragraph 

(o) of this supplemental NPRM, 

operators have three months to revise 

the ALS of the ICA to incorporate the 

tasks specified in Airbus A310 ALS Part 

4—Aging Systems Maintenance, 

Revision 01, dated December 21, 2006; 

and A300–600 ALS Part 4—Aging 

Systems Maintenance, Revision 01, 

dated December 21, 2006; as applicable. 

For the initial compliance times for the 

tasks identified in the ALS, we have 

added paragraph (o)(2) of this 

supplemental NPRM to provide a grace 

period of within 3 months after revising 

the ALS of the ICA. 

FAA’s Determination and Proposed 

Requirements of the Supplemental 

NPRM 

The changes discussed above expand 

the scope of the original NPRM; 

therefore, we have determined that it is 

necessary to reopen the comment period 

to provide additional opportunity for 

public comment on this supplemental 

NPRM. 

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55784 Federal Register / Vol. 73, No. 188 / Friday, September 26, 2008 / Proposed Rules 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this supplemental NPRM. 

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspection (required by AD 2006–10–11) .... 1 $80 $80, per inspection 

cycle.

59 $4,720, per inspection cycle. 

Inspection (required by AD 2006–15–10) .... 3 80 $240 .......................... 213 $51,120. 

Repetitive follow-on tasks (required by AD 

2006–15–10).

12 80 $960, per inspection 

cycle.

213 $204,480, per inspection cycle. 

ALS revision (new action) ............................. 1 80 $80 ............................ 213 $17,040. 

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 

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 supplemental NPRM 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 39–14595 (71 

FR 28254, May 16, 2006) and 

amendment 39–14690 (71 FR 42021, 

July 25, 2006) and adding the following 

new airworthiness directive (AD): 

Airbus: Docket No. FAA–2008–0018; 

Directorate Identifier 2007–NM–145–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by October 21, 2008. 

Affected ADs 

(b) This AD supersedes AD 2006–10–11 

and AD 2006–15–10. 

Applicability 

(c) This AD applies to all Airbus Model 

A310 series airplanes; and Model A300–600 

series airplanes; certificated in any category. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance according 

to paragraph (r) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued operational safety of the airplane. 

Unsafe Condition 

(d) This AD results from the 

manufacturer’s determination that life 

limitations and maintenance tasks are 

necessary in order to ensure continued 

operational safety of the affected airplanes. 

We are issuing this AD to prevent reduced 

structural integrity of these airplanes due to 

the failure of system components. 

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 Requirements of AD 2006– 

10–11 

Inspection and Corrective Action 

(f) For Airbus Model A310–203, –204, 

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

airplanes, except for airplanes on which 

Airbus Modification 12247 has been 

embodied in production: At the earlier of the 

compliance times specified in paragraph 

(f)(1) or (f)(2) of this AD, perform a detailed 

inspection for stress corrosion cracking of the 

flight transmission shafts located between the 

power control unit (PCU) and the torque 

limiters in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–27–2092, Revision 02, 

dated April 11, 2005. Thereafter, repeat the 

inspections as required by paragraph (g) of 

this AD. Before further flight, replace any 

cracked transmission shaft discovered during 

any inspection required by this AD with a 

new or reconditioned shaft, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A310–27–2095, 

dated March 29, 2000. Doing an inspection 

in accordance with paragraph (o) or (p) of 

this AD terminates the requirements of this 

paragraph. 

(1) Within 2,000 flight hours after the last 

flap asymmetry protection test performed in 

accordance with Airbus A310 Maintenance 

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Federal Register / Vol. 73, No. 188 / Friday, September 26, 2008 / Proposed Rules 55785 

Planning Document (MPD) Task 275600–01– 

1. 

(2) Within 8,000 flight cycles after the last 

flap asymmetry protection test performed in 

accordance with Airbus A310 MPD Task 

275600–02–1 or 800 flight cycles after June 

20, 2006 (the effective date of AD 2006–10– 

11), whichever comes later. 

Note 2: Airbus Service Bulletin A310–27– 

2092, Revision 02, dated April 11, 2005, 

refers to Lucas Liebherr Service Bulletin 

551A–27–624, Revision 1, dated August 18, 

2000, as an additional source of service 

information for accomplishing the 

inspections. 

Note 3: Airbus Service Bulletin A310–27– 

2092, Revision 02, refers to Airbus Service 

Bulletin A310–27–2095, dated March 29, 

2000, as a source of service information for 

replacing the flap transmission shafts. 

Note 4: Airbus Service Bulletin A310–27– 

2095 refers to Lucas Liebherr Service Bulletin 

551A–27–M551–05, dated January 12, 2000, 

as an additional source of service information 

for replacing the flap transmission shafts. 

Repetitive Inspections 

(g) Repeat the inspection required by 

paragraph (f) of this AD at the applicable 

times specified in paragraphs (g)(1), (g)(2), 

and (g)(3) of this AD. Doing an inspection in 

accordance with paragraph (o) or (p) of this 

AD terminates the requirements of this 

paragraph. 

(1) Before further flight after any 

occurrence of jamming of the flap 

transmission system. 

(2) At intervals not to exceed 2,000 flight 

hours after each flap asymmetry protection 

test performed in accordance with Airbus 

A310 MPD Task 275600–01–1. 

(3) At intervals not to exceed 8,000 flight 

cycles after each flap asymmetry protection 

test performed in accordance with Airbus 

A310 MPD Task 275600–02–1. 

Optional Terminating Action 

(h) Replacing any flap transmission shaft 

with a new or reconditioned transmission 

shaft in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–27–2095, dated March 

29, 2000, ends the inspections required by 

paragraphs (f) and (g) of this AD for that 

transmission shaft only. 

Actions Performed Using Previously Issued 

Service Information 

(i) Actions performed in accordance with 

Airbus Service Bulletin A310–27–2092, 

dated April 9, 1999; or Revision 01, dated 

December 11, 2001; are considered 

acceptable for compliance with the 

corresponding requirements of paragraphs (f) 

and (g) of this AD. 

No Reporting 

(j) Although Airbus Service Bulletin A310– 

27–2092, Revision 02, dated April 11, 2005, 

specifies to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

Restatement of Requirements of AD 2006– 

15–10 

Service Bulletin References 

(k) Unless otherwise specified in this AD, 

the term ‘‘service bulletin,’’ as used in 

paragraphs (l), (m), and (n) of this AD, means 

the applicable required service bulletin 

identified in Table 1 of this AD. The service 

bulletins refer to Goodrich Actuation 

Systems Service Bulletin 47142–27–11, 

Revision 3, dated April 25, 2005, as an 

additional source of service information for 

the required actions. 

TABLE 1—SERVICE BULLETINS

Required Airbus Service Bulletin 

Approved Airbus Service Bulletin version for 

actions done before the effective date of this 

AD 

Airbus airplane model 

A300–27–6044, Revision 04, dated September 

10, 2001; or A300–27–6044, Revision 05, 

dated August 29, 2006.

A300–27–6044, Revision 02, dated August 

26, 2000; or Revision 03, dated June 28, 

2001.

A300 B4–601, B4–603, B4–620, and B4–622. 

A300 B4–605R and B4–622R. 

A300 F4–605R and F4–622R. 

A300 C4–605R Variant F. 

A310–27–2089, Revision 02, dated June 28, 

2001; or A310–27–2089, Revision 03, dated 

August 29, 2006.

A310–27–2089, Revision 01, dated August 

25, 2000.

A310–203, –204, –221, and –222 

A310–304, –322, –324, and –325. 

Inspection 

(l) At the applicable time specified in 

paragraph (l)(1) or (l)(2) of this AD, do a 

detailed inspection of specified components 

of the trimmable horizontal stabilizer 

actuator (THSA) in accordance with 

paragraph 1.E.(2)(a) and the Accomplishment 

Instructions of the applicable service 

bulletin. Repair any discrepancy before 

further flight in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the European Aviation 

Safety Agency (EASA) (or its delegated 

agent). TRW Aeronautical Systems/Lucas 

Aerospace Component Maintenance Manual 

27–44–13, dated September 14, 2001, is one 

acceptable method for the repair. Doing an 

inspection in accordance with paragraph (o) 

or (p) of this AD terminates the requirements 

of this paragraph. 

(1) If the flight hours accumulated on the 

THSA can be positively determined: Inspect 

at the earlier of: 

(i) Before the accumulation of 47,000 total 

flight hours on the THSA, or within 600 

flight hours after August 29, 2006 (the 

effective date of AD 2006–15–10), whichever 

occurs later. 

(ii) Within 25 years since the THSA was 

new or within 600 flight hours after August 

29, 2006, whichever occurs later. 

(2) If the flight hours accumulated on the 

THSA cannot be positively determined: 

Inspect before the accumulation of 47,000 

total flight hours on the airplane, or within 

600 flight hours after August 29, 2006, 

whichever occurs later. 

Note 5: 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 mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’ 

Follow-on Repetitive Tasks 

(m) After the inspection required by 

paragraph (l) of this AD: Do the repetitive 

tasks in accordance with the 

Accomplishment Instructions and at the 

times specified in paragraph 1.E.(2)(b) of the 

service bulletin, as applicable, except as 

provided by paragraph (n) of this AD. The 

repetitive tasks are valid only until the THSA 

operational life exceeds 65,000 flight hours, 

40,000 flight cycles, or 25 years, whichever 

occurs first. Before the THSA is operated 

beyond these extended life goals, it must be 

replaced with a new or serviceable THSA, 

except as required by paragraph (n) of this 

AD. Doing an inspection in accordance with 

paragraph (o) or (p) of this AD terminates the 

requirements of this paragraph. 

Note 6: Refer to Airbus Operators 

Information Telex (OIT) SE 999.0074/05/BB, 

dated August 3, 2005, for additional 

information on the THSA life limits. 

THSA Replacement 

(n) For any THSA, whether discrepant or 

not, that is replaced with a new or 

serviceable THSA: Within 47,000 flight hours 

or 25 years, whichever occurs first, after the 

THSA is replaced, do the applicable tasks 

specified in paragraph 1.E.(2)(a) and the 

Accomplishment Instructions of the 

applicable service bulletin. Thereafter repeat 

the tasks within the repetitive intervals 

specified in paragraph 1.E.(2)(b) of the 

applicable service bulletin. Doing the 

corresponding tasks in accordance with 

mstockstill on PROD1PC66 with PROPOSALS

55786 Federal Register / Vol. 73, No. 188 / Friday, September 26, 2008 / Proposed Rules 

paragraph (o) or (p) of this AD terminates the 

requirements of this paragraph. 

New Requirements of This AD 

Revise Airworthiness Limitations Section 

(ALS) To Incorporate Limitations and 

Maintenance Tasks for Aging Systems 

Maintenance 

(o) Within 3 months after the effective date 

of this AD, revise the ALS of the Instructions 

for Continued Airworthiness (ICA) to 

incorporate Airbus A310 ALS Part 4—Aging 

Systems Maintenance, Revision 01, dated 

December 21, 2006; or Airbus A300–600 ALS 

Part 4—Aging Systems Maintenance, 

Revision 01, dated December 21, 2006; as 

applicable. For all tasks identified in Airbus 

A310 ALS Part 4—Aging Systems 

Maintenance, Revision 01; and Airbus A300– 

600 ALS Part 4—Aging Systems 

Maintenance, Revision 01; do the tasks at the 

later of the times specified in paragraphs 

(o)(1) and (o)(2) of this AD, except as 

provided by paragraph (p) of this AD. The 

repetitive inspections must be accomplished 

thereafter at the interval specified in Airbus 

A310 ALS Part 4—Aging Systems 

Maintenance, Revision 01; and Airbus A300– 

600 ALS Part 4—Aging Systems 

Maintenance, Revision 01. Doing an 

inspection required by this paragraph 

terminates the corresponding inspection 

required by paragraph (f), (g), (l), (m), or (n) 

of this AD. 

(1) At the initial compliance times 

(thresholds) specified in the applicable ALS 

Part 4—Aging Systems Maintenance, with 

the compliance times starting from the later 

of the times specified in paragraphs (o)(1)(i) 

and (o)(1)(ii) of this AD. 

(i) Since first flight of the airplane. 

(ii) Since the applicable part was new or 

refurbished if the part’s life (in flight hours, 

flight cycles, landings, or calendar time, as 

applicable) can be conclusively determined. 

(2) Within 3 months after doing the 

revision of the ALS of the ICA required by 

paragraph (o) of this AD. 

Note 7: Refer to Airbus OIT SE 999.0074/ 

05/BB, dated August 3, 2005, for additional 

information on the THSA life limits. 

Note 8: Refer to Airbus OIT SE 999.0008/ 

07/LB, dated January 16, 2007; and Airbus 

Service Information Letter (SIL) 05–008, 

Revision 1, dated February 21, 2007; for 

additional information on the THSA life 

limits and calculation method for unknown 

history of parts. 

(p) For airplanes on which any life 

limitation/maintenance task has been 

complied with in accordance with the 

requirements of paragraph (f), (g), (l), (m), or 

(n) of this AD (e.g., AD 2006–10–11 or AD 

2006–15–10), the last accomplishment of 

each limitation/task must be retained as a 

starting point for the accomplishment of each 

corresponding limitation/task interval now 

introduced in Airbus A310 ALS Part 4— 

Aging Systems Maintenance, Revision 01, 

dated December 21, 2006; and A300–600 

ALS Part 4—Aging Systems Maintenance, 

Revision 01, dated December 21, 2006; as 

applicable. Doing an inspection required by 

this paragraph terminates the corresponding 

inspection required by paragraph (f), (g), (l), 

(m), or (n) of this AD. 

(q) Except as provided by paragraph (r) of 

this AD: After accomplishing the actions 

specified in paragraphs (o) and (p) of this AD, 

no alternative inspection, inspection 

intervals, or limitations may be used. 

Alternative Methods of Compliance (AMOCs) 

(r)(1) 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: Tom Stafford, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

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

227–1149. Before using any approved AMOC 

on any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(2) AMOCs approved previously in 

accordance with AD 2006–10–11 are not 

approved as AMOCs with this AD. 

(3) AMOCs approved previously in 

accordance with AD 2006–15–10 are not 

approved as AMOCs with this AD. 

Related Information 

(s) EASA airworthiness directive 2007– 

0092, dated April 10, 2007, also addresses 

the subject of this AD. 

Issued in Renton, Washington, on 

September 18, 2008. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–22632 Filed 9–25–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1020; Directorate 

Identifier 2008–CE–053–AD] 

RIN 2120–AA64 

Airworthiness Directives; Vulcanair 

S.p.A. Model P68 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (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: 

The Safe Fatigue Limits (SFL) of the Wing 

Structure in the P68 Series aircraft have been 

redefined from the current 8,500 Flight Hours 

to a new value to be calculated up to a 

maximum of 17,500 Flight Hours. This has 

been developed by Vulcanair under Change 

No. MOD.P68/79 Rev. 1 and approved by 

EASA with No. EASA.A.C.02482 on 07 June 

2006. 

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 October 27, 2008. 

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. 

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: 

Sarjapur Nagarajan, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4145; fax: (816) 329–4090. 

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–2008–1020; Directorate Identifier 

2008–CE–053–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 

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