17376 Federal Register / Vol. 72, No. 67 / Monday, April 9, 2007 / Rules and Regulations 

during the year, for continued 

justification for such disclosures; 

(4) At the instruction of OMB, 

compile a report to be submitted to the 

Administrator and OMB, and made 

available to the public on request, 

describing the matching activities of 

SBA, including, 

(i) Matching programs in which SBA 

has participated; 

(ii) Matching agreements proposed 

that were disapproved by the Board; 

(iii) Any changes in membership or 

structure of the Board in the preceding 

year; 

(iv) The reasons for any waiver of the 

requirement described below for 

completion and submission of a costbenefit analysis prior to the approval of 

a matching program; 

(v) Any violations of matching 

agreements that have been alleged or 

identified and any corrective action 

taken; and 

(vi) Any other information required 

by OMB to be included in such report; 

(5) Serve as clearinghouse for 

receiving and providing information on 

the accuracy, completeness, and 

reliability of records used in matching 

programs; 

(6) Provide interpretation and 

guidance to SBA offices and personnel 

on the requirements for matching 

programs; 

(7) Review Agency recordkeeping and 

disposal policies and practices for 

matching programs to assure 

compliance with the Privacy Act; and 

(8) May review and report on any SBA 

matching activities that are not 

matching programs. 

(g) Cost-benefit analysis. Except as 

provided in paragraphs (e)(2) and (3) of 

this section, the Data Integrity Board 

shall not approve any written agreement 

for a matching program unless SBA has 

completed and submitted to such Board 

a cost-benefit analysis of the proposed 

program and such analysis demonstrates 

that the program is likely to be cost 

effective. The Board may waive these 

requirements if it determines, in 

writing, and in accordance with OMB 

guidelines, that a cost-benefit analysis is 

not required. Such an analysis also shall 

not be required prior to the initial 

approval of a written agreement for a 

matching program that is specifically 

required by statute. 

(h) Disapproval of matching 

agreements. If a matching agreement is 

disapproved by the Data Integrity Board, 

any party to such agreement may appeal 

to OMB. Timely notice of the filing of 

such an appeal shall be provided by 

OMB to the Committee on 

Governmental Affairs of the Senate and 

the Committee on Government 

Operations of the House of 

Representatives. 

(1) OMB may approve a matching 

agreement despite the disapproval of the 

Data Integrity Board if OMB determines 

that: 

(i) The matching program will be 

consistent with all applicable legal, 

regulatory, and policy requirements; 

(ii) There is adequate evidence that 

the matching agreement will be costeffective; and 

(iii) The matching program is in the 

public interest. 

(2) The decision of OMB to approve 

a matching agreement shall not take 

effect until 30 days after it is reported 

to the committees described in 

paragraph (h) of this section. 

(3) If the Data Integrity Board and the 

OMB disapprove a matching program 

proposed by the Inspector General, the 

Inspector General may report the 

disapproval to the Administrator and to 

the Congress. 

§ 102.41 Other provisions. 

(a) Personnel Records. All SBA 

personnel records and files, as 

prescribed by OPM, shall be maintained 

in such a way that the privacy of all 

individuals concerned is protected in 

accordance with regulations of OPM (5 

CFR parts 293 and 297). 

(b) Mailing Lists. The SBA will not 

sell or rent an individual’s name or 

address. This provision shall not be 

construed to require the withholding of 

names or addresses otherwise permitted 

to be made public. 

(c) Changes in Systems. The SBA 

shall provide adequate advance notice 

to Congress and OMB of any proposal to 

establish or alter any system of records 

in order to permit an evaluation of the 

probable or potential effect of such 

proposal on the privacy and other 

personal or property rights of 

individuals or the disclosure of 

information relating to such individuals, 

and its effect on the preservation of the 

constitutional principles of federalism 

and separation of powers. 

(d) Medical Records. Medical records 

shall be disclosed to the individual to 

whom they pertain. SBA may, however, 

transmit such information to a medical 

doctor named by the requesting 

individual. In regard to medical records 

in personnel files, see also 5 CFR 

297.205. 

Steven C. Preston, 

Administrator. 

[FR Doc. 07–1651 Filed 4–6–07; 8:45 am] 

BILLING CODE 8025–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27012; Directorate 

Identifier 2006–NM–188–AD; Amendment 

39–15017; AD 2007–07–15] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–601, A300 B4–603, A300 B4–

605R, A300 C4–605R Variant F, A310–

204, and A310–304 Airplanes Equipped 

With General Electric CF6–80C2 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Airbus Model 

A300 B4–600, B4–600R, C4–605R 

Variant F, and F4–600R (collectively 

called A300–600) series airplanes; and 

Model A310 series airplanes. That AD 

currently requires a one-time inspection 

for damage of the integrated drive 

generator (IDG) electrical harness and 

pyramid arm, and repair if necessary. 

This new AD adds new repetitive 

inspections, which, when initiated, 

terminate the inspection required by the 

existing AD. This new AD also requires 

repairing damage and protecting the 

harness. This new AD also provides for 

optional terminating action for the 

repetitive inspections. This new AD also 

removes certain airplanes from the 

applicability of the existing AD. This 

AD results from a report of structural 

damage on the forward pyramid arm of 

an engine pylon due to chafing of the 

IDG electrical harness against the 

structure of the pyramid arm. We are 

issuing this AD to prevent electrical 

arcing in the engine pylon, which could 

result in loss of the relevant alternating 

current (AC) bus bar, reduced structural 

integrity of the engine pylon, and 

possible loss of control of the airplane. 

DATES: This AD becomes effective May 

14, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of May 14, 2007. 

On May 13, 2004 (69 FR 23090, April 

28, 2004), the Director of the Federal 

Register approved the incorporation by 

reference of Airbus All Operators Telex 

A310–54A2038, dated February 19, 

2004; and Airbus All Operators Telex 

A300–54A6037, dated February 19, 

2004. 


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Federal Register / Vol. 72, No. 67 / Monday, April 9, 2007 / Rules and Regulations 17377 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

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: 

Examining the Docket 

You may examine the airworthiness 

directive (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 street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2004–09–01, amendment 

39–13590 (69 FR 23090, April 28, 2004). 

The existing AD applies to certain 

Airbus Model A300 B4–600, B4–600R, 

C4–605R Variant F, and F4–600R 

(collectively called A300–600) series 

airplanes; and Model A310 series 

airplanes. That NPRM was published in 

the Federal Register on January 26, 

2007 (72 FR 3764). That NPRM 

proposed to require a one-time 

inspection for damage of the integrated 

drive generator (IDG) electrical harness 

and pyramid arm, and repair if 

necessary. That NPRM proposed to add 

new repetitive inspections, which, 

when initiated, would terminate the 

inspection required by the existing AD. 

That NPRM also proposed to require 

repairing damage and protecting the 

harness. That NPRM also proposed to 

provide for optional terminating action 

for the repetitive inspections. That 

NPRM also proposed to remove certain 

airplanes from the applicability of the 

existing AD. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. No comments 

have been received on the NPRM or on 

the determination of the cost to the 

public. 

Change to Applicability 

We have removed Airbus Model 

A310–308 airplanes from the 

applicability of this AD. That model is 

not listed as an FAA-certified model in 

our type certificate data sheets. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD with the change 

described previously. We have 

determined that this change will neither 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. 

ESTIMATED COSTS

Action Work 

hours 

Average 

labor rate 

per hour 

Cost of 

parts Cost per airplane Number of U.S.- registered airplanes Fleet cost 

One-time inspection 

(from AD 2004–09–01).

2 $80 $0 $160 ............................... 100 ................................. $16,000. 

Repetitive inspections 

and harness protection 

(new requirement).

4 80 0 $320, per inspection 

cycle.

100 ................................. $32,000, per inspection 

cycle. 

New optional modification 8 80 2,460 $3,100 ............................ Up to 100 ....................... Up to $310,000. 

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 AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

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 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, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 


rwilkins on PROD1PC63 with RULES
17378 Federal Register / Vol. 72, No. 67 / Monday, April 9, 2007 / Rules and Regulations 

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 39–13590 (69 

FR 23090, April 28, 2004) and by adding 

the following new airworthiness 

directive (AD): 

2007–07–15 Airbus: Amendment 39–15017. 

Docket No. FAA–2007–27012; 

Directorate Identifier 2006–NM–188–AD. 

Effective Date 

(a) This AD becomes effective May 14, 

2007. 

Affected ADs 

(b) This AD supersedes AD 2004–09–01. 

Applicability 

(c) This AD applies to Airbus Model A300 

B4–601, A300 B4–603, A300 B4–605R, A300 

C4–605R Variant F, A310–204, and A310–

304 airplanes; certificated in any category; 

equipped with General Electric CF6–80C2 

engines without full-authority digital 

electronic control (FADEC); excluding 

airplanes on which Airbus Modification 

13184 was done in production. 

Unsafe Condition 

(d) This AD results from a report of 

structural damage on the forward pyramid 

arm of an engine pylon due to chafing of the 

integrated drive generator (IDG) electrical 

harness against the structure of the pyramid 

arm. We are issuing this AD to prevent 

electrical arcing in the engine pylon, which 

could result in loss of the relevant alternating 

current (AC) bus bar, reduced structural 

integrity of the engine pylon, and possible 

loss of control 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 Certain Requirements of AD 

2004–09–01 

All Operators Telex Reference 

(f) The term ‘‘All Operators Telex,’’ or 

‘‘AOT,’’ as used in paragraphs (g), (h), and (j) 

of this AD, means the following AOTs, as 

applicable: 

(1) For Model A300 B4–601, A300 B4–603, 

A300 B4–605R, and A300 C4–605R Variant F 

airplanes: Airbus AOT A300–54A6037, dated 

February 19, 2004; and 

(2) For Model A310–204, and A310–304 

airplanes: Airbus AOT A310–54A2038, dated 

February 19, 2004. 

Inspection 

(g) At the applicable time in paragraph 

(g)(1) or (g)(2) of this AD, do a one-time 

detailed inspection for discrepancies of the 

IDG harness, harness bracket, retaining 

fasteners, and pyramid arm, in accordance 

with the applicable AOT. 

(1) For airplanes on which Airbus 

Modification 07591 has not been 

incorporated as of May 13, 2004 (the effective 

date of AD 2004–09–01): Within 10 days after 

May 13, 2004. 

(2) For airplanes on which Airbus 

Modification 07591 has been incorporated as 

of May 13, 2004: Within 600 flight hours after 

May 13, 2004. 

Note 1: For the purposes of this AD, a 

detailed inspection is defined as: ‘‘An 

intensive visual examination of a specific 

structural area, system, installation, or 

assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at intensity deemed appropriate by 

the inspector. Inspection aids such as mirror, 

magnifying lenses, etc., may be used. Surface 

cleaning and elaborate access procedures 

may be required.’’

Related Investigative and Corrective Actions 

for Damaged Electrical Harness 

(h) If any discrepancy in the IDG electrical 

harness, fretting at the convoluted conduits, 

or contact between the IDG electrical harness 

and the pyramid arms is found during the 

inspection required by paragraph (g) of this 

AD: Before further flight, do the applicable 

related investigative actions and corrective 

actions in accordance with the applicable 

AOT. 

Corrective Action for Damaged Electrical 

Harness Bracket, Retaining Fasteners, or 

Pyramid Arm 

(i) If any discrepancy in the electrical 

harness bracket, retaining fasteners, or 

pyramid arm is found during the inspection 

required by paragraph (g) of this AD: Before 

further flight, repair in accordance with a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; 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). After the effective date of this AD, 

repair in accordance with a method approved 

by the FAA or the EASA. 

No Reporting Requirement for Paragraph (g) 

of this AD 

(j) Although the referenced AOTs describe 

procedures for submitting certain 

information to the manufacturer, no report is 

required for the inspection required by 

paragraph (g) of this AD. 

New Requirements of this AD 

Repetitive Inspections 

(k) Within 6 months after the effective date 

of this AD, and thereafter at intervals not to 

exceed 12 months: Do a detailed inspection 

for damage of the IDG harness and the pylon 

pyramid arms, and protect the harness. Do 

the actions in accordance with Airbus 

Service Bulletin A300–24–6097, dated March 

3, 2006 (for Model A300 B4–601, A300 B4–

603, A300 B4–605R, and A300 C4–605R 

Variant F airplanes); or A310–24–2100, dated 

March 3, 2006 (for Model A310–204, and 

A310–304 airplanes). The initial inspection 

terminates the requirements of paragraph (g) 

of this AD. If any discrepancy is found: 

Before further flight, repair in accordance 

with the applicable service bulletin; except, 

where the service bulletin specifies to contact 

the manufacturer for repair instructions, this 

AD requires repair using a method approved 

by either the Manager, International Branch, 

ANM–116; or the EASA (or its delegated 

agent). 

Report 

(l) At the applicable times specified in 

paragraphs (l)(1) and (l)(2) of this AD, submit 

a report of the findings (both positive and 

negative) of each inspection required by 

paragraph (k) of this AD. Send the report to 

Airbus Customer Services Directorate, 

Department AI/SE–E43, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France. The report must include the 

information specified in Appendix 01 of 

Airbus Service Bulletin A300–24–6097 or 

A310–24–2100, both dated March 3, 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) For each inspection done after the 

effective date of this AD: Send the report 

within 30 days after the inspection. 

(2) If an inspection was done before the 

effective date of this AD: Send the report 

within 30 days after the effective date of this 

AD. 

Optional Terminating Action 

(m) Replacement of the bracket feeder on 

the pylons terminates the requirements of 

this AD if the bracket feeder is replaced in 

accordance with Airbus Service Bulletin 

A300–54–6038, dated May 12, 2006 (for 

Model A300 B4–601, A300 B4–603, A300 

B4–605R, and A300 C4–605R Variant F 

airplanes); or A310–54–2039, dated May 12, 

2006 (for Model A310–204, and A310–304 

airplanes); as applicable. 

Alternative Methods of Compliance (AMOCs) 

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

ANM–116, 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. 

Related Information 

(o) EASA airworthiness directive 2006–

0155, dated June 1, 2006, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(p) You must use the service information 

identified in Table 1 of this AD to perform 

the actions that are required by this AD, 

unless the AD specifies otherwise. 


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Federal Register / Vol. 72, No. 67 / Monday, April 9, 2007 / Rules and Regulations 17379 

TABLE 1.—REQUIRED MATERIAL

INCORPORATED BY REFERENCE

Airbus Service information Date 

All Operators Telex 

A300–54A6037.

February 19, 2004. 

All Operators Telex 

A310–54A2038.

February 19, 2004. 

Service Bulletin A300–

24–6097, including 

Appendix 01.

March 3, 2006. 

Service Bulletin A310–

24–2100, including 

Appendix 01.

March 3, 2006. 

You must use the service information 

identified in Table 2 of this AD to perform 

the optional terminating action, if 

accomplished, unless the AD specifies 

otherwise. 

TABLE 2.—OPTIONAL MATERIAL

INCORPORATED BY REFERENCE

Airbus Service information Date 

Service Bulletin A300–

54–6038.

May 12, 2006. 

Service Bulletin A310–

54–2039.

May 12, 2006. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information identified in Table 3 

of this AD in accordance with 5 U.S.C. 552(a) 

and 1 CFR part 51. 

TABLE 3.—NEW MATERIAL

INCORPORATED BY REFERENCE

Airbus Service Bulletin Date 

A300–24–6097, including Appendix 01.March 3, 2006. 

A300–54–6038 ............. May 12, 2006. 

A310–24–2100, including Appendix 01.March 3, 2006. 

A310–54–2039 ............. May 12, 2006. 

(2) On May 13, 2004 (69 FR 23090, April 

28, 2004), the Director of the Federal Register 

approved the incorporation by reference of 

Airbus All Operators Telex A310–54A2038, 

dated February 19, 2004; and Airbus All 

Operators Telex A300–54A6037, dated 

February 19, 2004. 

(3) Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, for a 

copy of this service information. You may 

review copies at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal-register/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on March 

28, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–6450 Filed 4–6–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–20944; Directorate 

Identifier 2003–NE–64–AD; Amendment 39–

15018; AD 2007–08–01] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company CT7–5, –7, and –9 

Series Turboprop Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

General Electric Company (GE) CT7–

5A2, –5A3, –7A, –7A1, –9B, –9B1, and 

–9B2, –9C, –9C3, –9D, and –9D2 

turboprop engines, with certain part 

number (P/N) and serial number stage 2 

turbine aft cooling plates installed. That 

AD currently requires a onetime eddy 

current inspection (ECI) of boltholes in 

certain P/N stage 2 turbine aft cooling 

plates. This AD expands the population 

of affected CT7 turboprop engine 

models, but reduces the number of 

cooling plates affected. It also requires 

a onetime ECI of boltholes in certain P/ 

N stage 2 turbine aft cooling plates with 

specific serial numbers. This AD results 

from the manufacturer expanding the 

list of affected engine models and 

identifying the affected stage 2 turbine 

aft cooling plates by serial number. We 

are issuing this AD to prevent 

separation of the stage 2 turbine aft 

cooling plate, resulting in uncontained 

engine failure and damage to the 

airplane. 

DATES: This AD becomes effective May 

14, 2007. The Director of the Federal 

Register approved the incorporation by 

reference of certain publications listed 

in the regulations as of May 14, 2007. 

ADDRESSES: You can get the service 

information identified in this AD from 

General Electric Aircraft Engines CT7 

Series Turboprop Engines, 1000 

Western Ave, Lynn, MA 01910; 

telephone (781) 594–3140, fax (781) 

594–4805. 

You may examine the AD docket on 

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

Room PL–401 on the plaza level of the 

Nassif Building, 400 Seventh Street, 

SW., Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Mark Bouyer, Engine Certification 

Office, FAA, Engine and Propeller 

Directorate, 12 New England Executive 

Park, Burlington, MA 01803; telephone 

(781) 238–7755; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to GE CT7–5A2, –5A3, –7A, 

–7A1, –9B, –9B1, and –9B2 turboprop 

engines, with certain P/N and serial 

number stage 2 turbine aft cooling plates 

installed. We published the proposed 

AD in the Federal Register on March 31, 

2006 (71 FR 16248). That action 

proposed to expand the population of 

affected CT7 turboprop engine models 

required to undergo a onetime ECI of 

boltholes in certain P/N stage 2 turbine 

aft cooling plates. That action also 

proposed to reduce the number of 

cooling plates affected by identifying 

the serial numbers. 

Examining the AD Docket 

You may examine the docket that 

contains the AD, any comments 

received, and any final disposition in 

person at the Docket Management 

Facility between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The Docket Office (telephone 

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

level of the Department of 

Transportation Nassif Building at the 

street address stated in ADDRESSES. 

Comments will be available in the AD 

docket shortly after the DMS receives 

them. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Clarification of ECI Requirements 

GE suggests that we clarify paragraph 

(f) of this AD to limit the required ECI 

to stage 2 turbine aft cooling plates that 

are being returned to service. This 

change would eliminate any 

requirement to ECI cooling plates that 

are not going to be reused. We agree. If 

the cooling plate is not going to be 

reused, there is no need to ECI it 

immediately after it is removed. 

Paragraph (h) of this AD requires an ECI 

of all cooling plates affected by this AD 

before they are returned to service. We 

made the clarification to paragraph (f). 


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