48286 Federal Register / Vol. 73, No. 161 / Tuesday, August 19, 2008 / Rules and Regulations 

§ 33.91 Engine system and component 

tests. 

(a) For those systems or components 

that cannot be adequately substantiated 

in accordance with endurance testing of 

§ 33.87, the applicant must conduct 

additional tests to demonstrate that the 

systems or components are able to 

perform the intended functions in all 

declared environmental and operating 

conditions. 

* * * * * 

Issued in Washington, DC, on July 2, 2008. 

Robert A. Sturgell, 

Acting Administrator. 

[FR Doc. E8–19048 Filed 8–18–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0627; Directorate 

Identifier 2008–CE–033–AD; Amendment 

39–15647; AD 2008–17–09] 

RIN 2120–AA64 

Airworthiness Directives; EADS 

SOCATA Model TBM 700 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

issued 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: 

A rupture of the alternator and vapour 

cycle cooling system pulley drive assembly 

has reportedly been found. Such a failure 

could lead to the loss of the alternator and 

vapour cycle cooling systems and could also 

cause mechanical damage inside the 

powerplant compartment. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

September 23, 2008. 

As of September 23, 2008, the 

Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT

Albert Mercado, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329–

4119; fax: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on June 9, 2008 (73 FR 32495), 

and proposed to supersede AD 2008–

10–13, Amendment 39–15520 (73 FR 

26318, May 9, 2008). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states that: 

A rupture of the alternator and vapour 

cycle cooling system pulley drive assembly 

has reportedly been found. Such a failure 

could lead to the loss of the alternator and 

vapour cycle cooling systems and could also 

cause mechanical damage inside the 

powerplant compartment. 

To address this condition, AD 2008–0063–

E had been published to require a check of 

the pulley drive assembly for leakage and, as 

an interim action, removal of the compressor 

drive belt from the assembly, and adoption 

of a new operational procedure to keep the 

air-conditioning system deactivated. 

This AD retains the requirements of AD 

2008–0063–E which is superseded, 

introduces a mandatory terminating action 

which consists in replacing the original 

pulley drive assembly by a new one of an 

improved design—corresponding to the 

EADS SOCATA modification MOD 70–0231–

21—that permits reinstallation of the 

compressor drive belt. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

21 products of U.S. registry. We also 

estimate that it will take about 10 workhours per product to comply with basic 

requirements of this AD. The average 

labor rate is $80 per work-hour. 

Required parts will cost about $2,912 

per product. 

Based on these figures, we estimate 

the cost of this AD to the U.S. operators 

to be $77,952, or $3,712 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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 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 


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Federal Register / Vol. 73, No. 161 / Tuesday, August 19, 2008 / Rules and Regulations 48287 

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. 

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 the NPRM, 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. 

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: 

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 

removing Amendment 39–15520 (73 FR 

26318, May 9, 2008) and adding the 

following new AD: 

2008–17–09 EADS SOCATA: Amendment 

39–15647; Docket No. FAA–2008–0627; 

Directorate Identifier 2008–CE–033–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective September 23, 2008. 

Affected ADs 

(b) This AD supersedes AD 2008–10–13, 

Amendment 39–15520. 

Applicability 

(c) This AD applies to Models TBM 700 

airplanes, serial numbers 434 through 455, 

certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 24: Electric Power. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

A rupture of the alternator and vapour 

cycle cooling system pulley drive assembly 

has reportedly been found. Such a failure 

could lead to the loss of the alternator and 

vapour cycle cooling systems and could also 

cause mechanical damage inside the 

powerplant compartment. 

To address this condition, AD 2008–0063–

E had been published to require a check of 

the pulley drive assembly for leakage and, as 

an interim action, removal of the compressor 

drive belt from the assembly, and adoption 

of a new operational procedure to keep the 

air-conditioning system deactivated. 

This AD retains the requirements of AD 

2008–0063–E which is superseded, 

introduces a mandatory terminating action 

which consists in replacing the original 

pulley drive assembly by a new one of an 

improved design—corresponding to the 

EADS SOCATA modification MOD 70–0231–

21—that permits reinstallation of the 

compressor drive belt. 

Actions and Compliance 

(f) Unless already done, do the following 

before further flight after May 9, 2008 (the 

compliance date retained from AD 2008–10–

13): 

(1) Position to ‘‘OFF’’ the air-conditioning 

‘‘AIR COND’’ switch. 

(2) Inspect for oil leakage in the pulley 

drive assembly by following EADS SOCATA 

Service Bulletin (SB) No. 70–156 

Amendment 1, dated March 2008. 

(i) If any leak is found, before further flight 

after the inspection, replace the pulley drive 

assembly part number (P/N) 

T700G215504900000 with P/N 

T700G215505710000 following EADS 

SOCATA Service Bulletin (SB) No. 70–156 

Amendment 1, dated March 2008. 

(ii) If no leak is found, before further flight, 

remove the compressor drive belt from the 

pulley drive assembly following either EADS 

SOCATA Service Bulletin (SB) No. 70–156, 

original issue; or EADS SOCATA Service 

Bulletin (SB) No. 70–156, Amendment 1; 

both dated March 2008. 

(3) The air-conditioning ‘‘AIR COND’’

switch must be in the ‘‘OFF’’ position and 

the compressor drive belt must remain 

removed until the pulley drive assembly part 

number (P/N) T700G215504900000 is 

replaced with P/N T700G215505710000 

following EADS SOCATA Service Bulletin 

(SB) No. 70–156 Amendment 1, dated March 

2008. This replacement must be done before 

further flight if any leak is found and may be 

done at any time as terminating action to this 

AD. 

(g) Within the next 12 months after 

September 23, 2008 (the effective date of this 

AD), unless already done, replace the pulley 

drive assembly P/N T700G215504900000 

with P/N T700G215505710000 and reinstall 

the compressor drive belt, following EADS 

SOCATA Service Bulletin (SB) No. 70–156 

Amendment 1, dated March 2008. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(h) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Albert Mercado, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4119; fax: (816) 329–

4090. 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) 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 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Special Flight Permit 

(i) Under 14 CFR 39.23, we are limiting the 

special flight permits for the check of 

equipment of this AD under the following 

condition: The air-conditioning ‘‘AIR COND’’

switch is set to the ‘‘OFF’’ position. 

Related Information 

(j) Refer to MCAI European Aviation Safety 

Agency (EASA) Emergency AD No.: 2008–

0067–E, dated April 3, 2008, and EADS 

SOCATA Service Bulletin (SB) No. 70–156 

Amendment 1, dated March 2008, for related 

information. 

Material Incorporated by Reference 

(k) You must use EADS SOCATA Service 

Bulletin (SB) No. 70–156, original issue; or 

EADS SOCATA Service Bulletin (SB) No. 70–

156, Amendment 1; both dated March 2008, 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact EADS SOCATA—Direction 

des Services, 65921 Tarbes Cedex 9, France; 

telephone: +33 (0)5 62 41 73 00; fax: +33 (0)5 

62 41 7–54; or in the United States contact 

EADS SOCATA North America, Inc., North 

Perry Airport, 7501 South Airport Road, 

Pembroke Pines, Florida 33023; telephone: 

(954) 893–1400; fax: (954) 964–4141. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Room 506, Kansas City, 

Missouri 64106; 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/ 

code_of_federal_regulations/ 

ibr_locations.html 


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48288 Federal Register / Vol. 73, No. 161 / Tuesday, August 19, 2008 / Rules and Regulations 

Issued in Kansas City, Missouri, on August 

7, 2008. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E8–18813 Filed 8–18–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–29174; Directorate 

Identifier 2007–NM–125–AD; Amendment 

39–15641; AD 2008–17–03] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–100, –200, –200C, –300, 

–400, and –500 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes. 

This AD requires repetitive inspections 

to detect cracking of the body station 

303.9 frame, and corrective action if 

necessary. This AD also provides for 

optional terminating action for the 

repetitive inspections. This AD results 

from reports of cracks found at the 

cutout in the web of body station frame 

303.9 inboard of stringer 16L. We are 

issuing this AD to detect and correct 

such cracking, which could prevent the 

left forward entry door from sealing 

correctly, and could cause in-flight 

decompression of the airplane. 

DATES: This AD is effective September 

23, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 23, 2008. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. 

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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Howard Hall, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6430; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to 

certain Boeing Model 737–100, –200, 

–200C, –300, –400, and –500 series 

airplanes. That NPRM was published in 

the Federal Register on September 13, 

2007 (72 FR 52314). That NPRM 

proposed to require repetitive 

inspections to detect cracking of the 

body station 303.9 frame, and corrective 

action if necessary. That NPRM also 

proposed optional terminating action for 

the repetitive inspections. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Support for the NPRM 

Boeing concurs with the NPRM. 

Request To Delay Final Rule 

The Air Transport Association (ATA), 

on behalf of its member United Airlines, 

requests that we delay issuing the final 

rule until kits (to repair cracks or to 

terminate the repetitive inspections) are 

readily available from Boeing. Only 

Boeing kits are specified; Boeing kit 

65C37763–8 is under parts management 

control by Boeing. 

We disagree with the request to delay 

issuing the final rule. To delay this 

action would be inappropriate, since we 

have determined that an unsafe 

condition exists, and that inspections 

must be conducted in a timely manner 

to ensure continued safety. Boeing is 

aware of the pending AD. We have been 

advised that kits are currently available 

from Boeing Spares, and that Boeing has 

already made forecasts to ensure 

continued kit availability. Operators 

that order out-of-stock kits from Boeing 

can request permission from Boeing 

Spares to manufacture the kits. We have 

been advised that Boeing Spares will 

provide the drawings and specifications 

required to make kits. The kits related 

to this AD are made up of simple parts 

that should be easy for operators to 

fabricate. We have not changed the final 

rule regarding this issue. 

Request To Allow Existing Repairs as 

Terminating Action 

Continental requests that we revise 

the NPRM to allow existing FAAapproved repairs (in the inspection area 

specified in the NPRM) as terminating 

action for the proposed repetitive 

inspections. The commenter notes that 

the service bulletin has no provisions 

for inspecting existing FAA-approved 

repairs. 

While certain previously installed 

repairs might be acceptable as a 

terminating action for the AD 

inspections, we cannot classify all 

previously installed repairs—even ones 

approved by the FAA—as terminating 

action unless the repair is properly 

evaluated in light of the requirements of 

this AD. Paragraph (j) of the final rule 

provides operators the opportunity to 

request approval of specific repair 

configurations as terminating action. 

Such a request should include data/ 

rationale to show that the repair 

configuration provides an acceptable 

level of safety without continued 

inspections. We have not changed the 

final rule regarding this issue. 

Request To Extend Grace Period 

Continental Airlines requests that we 

revise the NPRM to extend the grace 

period for the initial inspection (for 

airplanes that have exceeded the 

specified flight-cycle threshold). The 

commenter requests an extension from 

2,250 flight cycles to 4,500 flight cycles 

to coincide with a scheduled heavy 

maintenance check. The commenter 

asserts that the proposed grace period 

would not give operators adequate time 

to comply with the AD without added 

financial and logistical burden on the 

airlines. The commenter refers to AD 

2005–20–03, amendment 39–14296 (70 

FR 56361, September 27, 2005). That 

AD also applies to Boeing Model 737–

100, –200, –200C, –300, –400, and –500 

series airplanes. That AD requires 

repetitive inspections of the intercostal 

webs, attachment clips, and stringer 

splice channels for cracks; and 

corrective action if necessary. The 

commenter states that the inspection 

area is the same for AD 2005–20–03 and 

the subject NPRM. The grace period for 

that AD is 4,500 flight cycles, so 

extending the grace period in the NPRM 

to 4,500 flight cycles will provide an 

acceptable safety level in this AD. 

We agree with the commenter’s 

request and rationale. We have revised 

paragraph (h) in this final rule 

accordingly. We have coordinated this 

change with Boeing. 


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