Federal Register / Vol. 72, No. 45 / Thursday, March 8, 2007 / Rules and Regulations 10349 

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: 

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 adding the following new 

airworthiness directive (AD): 

2007–05–13 Airbus: Amendment 39–14974. 

Docket No. FAA–2006–26706; 

Directorate Identifier 2006–NM–216–AD. 

Effective Date 

(a) This AD becomes effective April 12, 

2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A319, 

A320, and A321 airplanes identified in 

paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category. This AD 

excludes Airbus Model A319, A320, and 

A321 airplanes identified in paragraph (c)(3) 

of this AD, certificated in any category. 

(1) Including airplanes on which one of the 

following has been incorporated in 

production: Airbus Modification 20065, 

20040, 24495, 24848, 24496, 21895, 21896, 

25905, 25907, 22601, 22602, 27187, 28319, 

28322, 28330, 28335, or 31797. 

(2) Including airplanes on which one of the 

following has been incorporated in service: 

Airbus Service Bulletin A320–25–1132, 

A320–25–1133, A320–25–1145, A320–25–

1175, A320–25–1177, A320–25–1276, A320–

25–1278, A320–28–1134, or A320–28–1141. 

(3) Excluding airplanes on which both 

Airbus Modifications 32244 and 32245, or 

both Airbus Modifications 32316 and 32317, 

have been incorporated in production. 

Unsafe Condition 

(d) This AD results from tests that have 

shown that the attachment points of the YZlatches of the cargo loading system fail under 

maximum loads. We are issuing this AD to 

prevent failure of the attachment points of 

the YZ-latches, which could result in 

unrestrained cargo causing damage to the fire 

protection system, hydraulic system, 

electrical wiring, or other equipment located 

in the forward and aft cargo compartments. 

This damage could adversely affect the 

continued safe flight 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. 

Installation 

(f) Within 36 months after the effective 

date of this AD, install spacer assemblies at 

the attachment points of the YZ-latches of the 

cargo loading system in the forward and aft 

cargo compartments, as applicable, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320–

25–1294, Revision 02, dated September 5, 

2006. 

Credit for Actions Done According to 

Previous Issues of Service Bulletin 

(g) Actions done before the effective date 

of this AD in accordance with Airbus Service 

Bulletin A320–25–1294, dated March 14, 

2003; and Revision 01, dated March 27, 2006; 

are acceptable for compliance with the 

corresponding requirements of paragraph (f) 

of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

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

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(i) European Aviation Safety Agency 

(EASA) airworthiness directive 2006–0184, 

dated July 3, 2006, also addresses the subject 

of this AD. 

Material Incorporated by Reference 

(j) You must use Airbus Service Bulletin 

A320–25–1294, Revision 02, dated 

September 5, 2006, to perform the actions 

that are required by this AD, unless the AD 

specifies otherwise. The Director of the 

Federal Register approved the incorporation 

by reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

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 February 

22, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–3840 Filed 3–7–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26285; Directorate 

Identifier 2006–CE–69–AD; Amendment 39–

14932; AD 2007–04–01] 

RIN 2120–AA64 

Airworthiness Directives; Pacific 

Aerospace Corporation Ltd Model 

750XL Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; correction. 

SUMMARY: This document makes a 

correction to Airworthiness Directive 

(AD) 2007–04–01, which was published 

in the Federal Register on February 14, 

2007 (72 FR 6931), and applies to 

certain Pacific Aerospace Corporation 

Ltd Model 750XL airplanes. AD 2007–

04–01 requires that you inspect the 

rivets in the fuselage roof at STN 180.85, 

BL 19.67, WL 86.2, and replace 

undersize rivets. Current language in 

§ 39.13 [Amended] of AD 2007–04–01 

references ‘‘***’’ instead of ‘‘2007–

04–01.’’ This document corrects that 

paragraph by changing the reference 

from ‘‘***’’ to ‘‘2007–04–01.’’

DATES: The effective date of this AD 

(2007–04–01) remains March 21, 2007. 

FOR FURTHER INFORMATION CONTACT: Karl 

Schletzbaum, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4146; fax: (816) 

329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On February 5, 2007, the FAA issued 

AD 2007–04–01, Amendment 39–14932 

(72 FR 6931, February 14, 2007), which 

applies to certain Pacific Aerospace 


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10350 Federal Register / Vol. 72, No. 45 / Thursday, March 8, 2007 / Rules and Regulations 

Corporation Ltd Model 750XL airplanes. 

AD 2007–04–01 requires you to inspect 

the rivets in the fuselage roof at STN 

180.85, BL 19.67, WL 86.2, and replace 

undersize rivets. Current language in 

§ 39.13 [Amended] of AD 2007–04–01 

references ‘‘***’’ instead of ‘‘2007–

04–01.’’

Need for the Correction 

This correction is needed to specify 

the correct AD number (2007–04–01) for 

AD 2007–04–01. 

Correction of Publication 

■ Accordingly, the publication of 

February 14, 2007 (72 FR 6931), of 

Amendment 39–14932; AD 2007–04–01, 

which was the subject of FR Doc. E7–

2318, is corrected as follows: 

Section 39.13 [Corrected] 

■ On page 6932, in the second column, 

in § 39.13 [Amended], in the third line, 

remove ‘‘***’’ and add ‘‘2007–04–01’’

in its place. 

■ Action is taken herein to correct this 

reference in AD 2007–04–01 and to add 

this AD correction to section 39.13 of 

the Federal Aviation Regulations (14 

CFR 39.13). 

The effective date remains March 21, 

2007. 

Issued in Kansas City, Missouri, on March 

2, 2007. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E7–4130 Filed 3–7–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27023; Directorate 

Identifier 98–ANE–47–AD; Amendment 39–

14978; AD 2007–05–17] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney JT9D Series Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

Pratt & Whitney (PW) JT9D series 

turbofan engines. That AD currently 

requires revisions to the Airworthiness 

Limitations Section (ALS) of the 

manufacturer’s Instructions for 

Continued Airworthiness (ICA) to 

include required enhanced inspection of 

selected critical life-limited parts at 

each piece-part opportunity. This AD 

modifies the JT9D series engines ALS 

sections of the manufacturer’s manuals 

and an air carrier’s approved continuous 

airworthiness maintenance program to 

incorporate additional inspection 

requirements. This AD results from the 

need to require enhanced inspection of 

selected critical life-limited parts of 

JT9D series turbofan engines. We are 

issuing this AD to prevent critical lifelimited rotating engine part failure, 

which could result in an uncontained 

engine failure and damage to the 

airplane. 

DATES: This AD becomes effective April 

12, 2007. 

ADDRESSES: 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 Riley, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803–

5299; telephone (781) 238–7758, fax 

(781) 238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to PW JT9D series turbofan 

engines. We published the proposed AD 

in the Federal Register on November 2, 

2005 (70 FR 66300). That action 

proposed to modify the JT9D series 

engines ALS sections of the 

manufacturer’s manuals and an air 

carrier’s approved continuous 

airworthiness maintenance program to 

incorporate additional inspection 

requirements. PW has added mandatory 

eddy current inspections (ECIs) for the 

web cooling holes in high pressure 

turbine (HPT) stage 1 disks installed in 

engine models JT9D–7R4D, –7R4D1, 

–7R4E, and –7R4E1, and for web tie-rod 

holes in HPT stage 2 disks installed in 

JT9D–3A, –7, –7A, –7H, –7AH, –7F, –7J, 

–20, and –20J engines. The mandatory 

inspections are needed to identify those 

critical rotating parts with conditions, 

which if allowed to continue in service, 

could result in uncontained failures. 

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 Docket Office 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. 

Request To Delete ECIs for JT9D–59A, 

–70A, –7Q, and –7Q3 Engines 

One commenter, Japan Airlines, 

requests that we delete the ECIs for 

JT9D–59A, –70A, –7Q, and –7Q3 

engines from the table in the proposed 

AD compliance section. The commenter 

points out that the proposed AD 

preamble paragraph entitled ‘‘FAA’s 

Determination and Requirements of the 

Proposed AD’’ does not include ECIs for 

JT9D–59A, –70A, –7Q, and –7Q3 

engines. 

We do not agree. We inadvertently 

omitted listing the requirement of ECI of 

the HPT stage 1 disk web cooling holes 

on JT9D–59A, –70A, –7Q, and –7Q3 

engines, under the proposed AD 

preamble paragraph entitled ‘‘FAA’s 

Determination and Requirements of the 

Proposed AD’’. The proposed AD 

compliance section and the compliance 

section in this AD, correctly list those 

engine models. We did not change the 

AD. 

Request To Wait To Issue the AD 

Japan Airlines requests that we wait 

to issue the AD until Pratt & Whitney 

provides the ECI procedure to the 

operators. The commenter states that the 

JT9D–7 Engine Manual Section 72–51–

02, Inspection 05, has not been 

published yet. 

We do not agree. Although the ECI 

procedure was not published in the 

JT9D–7 Engine Manual as of December 

26, 2005 when the comment was sent, 

it was incorporated into the JT9D–7 

Engine Manual on February 15, 2006. 

We do not need to wait to issue the AD. 

Request To Revise Engine Manual 

Japan Airlines requests that we 

recommend to Pratt & Whitney to revise 

the JT9D engine manual to remove the 

specific manufacturer’s name of the ECI 

equipment required to perform ECIs, 

and to only list the technical 

specifications required to perform the 

ECIs. The commenter states that 

operators may not own the ECI 

equipment specified in the Pratt & 

Whitney JT9D engine manual, but may 

have similar equipment capable of 

performing the inspections. 


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