Federal Register / Vol. 70, No. 192 / Wednesday, October 5, 2005 / Rules and Regulations 58005 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) 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. 

Material Incorporated by Reference 

(l) You must use Boeing Alert Service 

Bulletin 727–53A0227, dated September 16, 

2004, 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 Boeing Commercial Airplanes, P.O. 

Box 3707, Seattle, Washington 98124–2207, 

for a copy of this service information. You 

may review copies at the Docket Management 

Facility, U.S. Department of Transportation, 

400 Seventh Street SW., room PL–401, Nassif 

Building, Washington, DC; on the Internet at 

http://dms.dot.gov; or at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at the NARA, call (202) 741–

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on 

September 26, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19842 Filed 10–4–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21138; Directorate 

Identifier 2004–NM–131–AD; Amendment 

39–14310; AD 2005–20–16] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–100, –200, and –200C Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 737–100, –200, and 

–200C series airplanes. This AD requires 

a one-time detailed inspection for 

cracking of the lugs of the inboard 

attach fittings of the wing leading edge 

slat tracks at slat numbers 2 and 5; prior 

or concurrent actions for certain 

airplanes; repetitive high-frequency 

eddy current (HFEC) inspections for 

cracking of the lug surfaces of those 

inboard attach fittings if necessary; and 

replacement of the attach fittings with 

new, improved fittings. This AD results 

from reports of damage to the lugs of 

certain inboard attach fittings of the 

leading edge slat tracks. We are issuing 

this AD to prevent a lifted slat, which, 

if the airplane performs any non-normal 

maneuver during takeoff or landing at 

very high angles of attack, could lead to 

the loss of the slat and reduced control 

of the airplane. 

DATES: This AD becomes effective 

November 9, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of November 9, 2005. 

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 Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6440; fax (425) 917–6590. 

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 would 

apply to certain Boeing Model 737–100, 

–200, and –200C series airplanes. That 

NPRM was published in the Federal 

Register on May 9, 2005 (70 FR 24335). 

That NPRM proposed to require a onetime detailed inspection for cracking of 

the lugs of the inboard attach fittings of 

the wing leading edge slat tracks at slat 

numbers 2 and 5; prior or concurrent 

actions for certain airplanes; repetitive 

high-frequency eddy current (HFEC) 

inspections for cracking of the lug 

surfaces of those inboard attach fittings 

if necessary; and replacement of the 

attach fittings with new, improved 

fittings. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Support for the NPRM 

One commenter, the manufacturer, 

concurs with the content of the NPRM. 

Request To Disallow Use of Aluminum 

Attach Fittings 

One commenter requests that we 

revise the NPRM to prohibit replacing 

aluminum attach fittings with new 

aluminum fittings after the effective 

date of the AD. The commenter provides 

no justification for this request. 

We do not agree with this request. 

The manufacturer recommends that, 

unless cracked, an aluminum attach 

fitting need not be replaced until 120 

months or 30,000 flight cycles, 

whichever comes first, after the effective 

date of the AD. We have determined 

that the manufacturer recommendation 

is sound and that the repetitive 

inspections of the aluminum fittings 

required by the AD are sufficient to 

maintain safety until the aluminum 

fittings are removed from service. We 

have not changed the AD in this regard. 

Explanation of Change Made to This 

AD 

We have revised the ‘‘Alternative 

Methods of Compliance (AMOCs)’’

paragraph in this AD to clarify the 

delegation authority for Authorized 

Representatives for the Boeing 

Commercial Airplanes Delegation 

Option Authorization. 

Clarification of Alternative Method of 

Compliance (AMOC) Paragraph 

We have revised this action to clarify 

the appropriate procedure for notifying 

the principal inspector before using any 

approved AMOC on any airplane to 

which the AMOC applies. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

that have been submitted, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We have determined that these changes 

58006 Federal Register / Vol. 70, No. 192 / Wednesday, October 5, 2005 / Rules and Regulations 

will neither increase the economic 

burden on any operator nor increase the 

scope of the AD. 

Costs of Compliance 

This AD will affect about 909 

airplanes worldwide. 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 

Parts 

cost 

Cost per 

airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Detailed inspection .......................................................... 1 $65 None $65 522 $33,930. 

HFEC inspection .............................................................. 4 65 None $260, per inspection 

cycle 

522 $135,720, per inspection cycle. 

Replace fitting .................................................................. 2 65 $1,674 $1,804 522 $941,688. 

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: 

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): 

2005–20–16 Boeing: Amendment 39–14310. 

Docket No. FAA–2005–21138; 

Directorate Identifier 2004–NM–131–AD. 

Effective Date 

(a) This AD becomes effective November 9, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 737–

100, –200, and –200C series airplanes; line 

numbers 1 through 1585 inclusive; 

certificated in any category. 

Unsafe Condition 

(d) This AD was prompted by reports of 

damage to the lugs of certain inboard attach 

fittings of the leading edge slat tracks. We are 

issuing this AD to prevent a lifted slat, 

which, if the airplane performs any nonnormal maneuver during takeoff or landing at 

very high angles of attack, could lead to the 

loss of the slat and reduced 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. 

Service Bulletin Reference 

(f) The term ‘‘service bulletin,’’ as used in 

this AD, means the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–57–1273, Revision 2, 

dated October 30, 2003; unless otherwise 

specified in this AD. 

Inspections 

(g) Prior to the accumulation of 7,000 total 

flight cycles or within 12 months after the 

effective date of this AD, whichever occurs 

later, perform a one-time detailed inspection 

for cracking and damage of the inboard attach 

fittings at slats 2 and 5 of the wing leading 

edge in accordance with the service bulletin. 

Note 1: For the purposes of this AD, a 

detailed inspection is ‘‘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.’’

(1) If any crack or damage is found, replace 

the cracked inboard attach fitting in 

accordance with paragraph (h) of this AD. 

(2) If no crack or damage is found, within 

4,500 flight cycles or 18 months after the 

detailed inspection required by paragraph (g) 

of this AD, whichever occurs first, perform a 

high-frequency eddy current (HFEC) 

inspection for cracking of the lugs of the 

inboard attach fittings in accordance with the 

service bulletin. If no crack is found, repeat 

the HFEC inspection at intervals not to 

exceed 4,500 flight cycles. 

Replacement of Fittings 

(h) Replace the aluminum inboard attach 

fittings with new, improved steel fittings at 

the applicable compliance time in paragraph 

(h)(1) or (h)(2) of this AD in accordance with 

the service bulletin. Replacement of any 

aluminum fitting with a new, improved steel 

fitting terminates the one-time detailed 

inspection and the repetitive HFEC 

Federal Register / Vol. 70, No. 192 / Wednesday, October 5, 2005 / Rules and Regulations 58007 

inspections required by paragraph (g) of this 

AD for that fitting. 

(1) If any crack or damage is found during 

any inspection required by paragraphs (g) or 

(i) of this AD, before further flight. 

(2) If no crack or damage is found during 

any inspection required by paragraph (g) or 

(i) of this AD, within 30,000 flight cycles or 

within 120 months after the effective date of 

this AD, whichever occurs first. 

Concurrent Service Bulletin 

(i) For airplanes listed in Group 2 of the 

service bulletin: Prior to or during the onetime detailed inspection for cracking or 

damage required by paragraph (g) of this AD 

or during replacement of the fitting required 

by paragraph (h) of this AD, whichever 

occurs first, perform a detailed inspection on 

slats 2 and 5 for interference of the slat tab 

support clips with the slat track attach 

fittings and trim the support clips to 

eliminate any interference with the attach 

fittings as applicable; in accordance with 

Figure 3 of the Accomplishment Instructions 

of Boeing Service Bulletin 737–57–1080, 

Revision 3, dated September 24, 1992; and 

replace any cracked or damaged aluminum 

attach fitting with a new, improved steel 

fitting in accordance with paragraph (h) of 

this AD. 

Actions Accomplished Per Previous Issue of 

Service Bulletin 

(j) Actions accomplished before the 

effective date of this AD in accordance with 

Boeing Service Bulletin 737–57–1080, dated 

September 10, 1973; Revision 1, dated 

February 25, 1983; or Revision 2, dated 

August 24, 1989; are considered acceptable 

for compliance with the corresponding 

actions specified in paragraph (i) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(2) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplane Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(3) Before using any AMOC approved in 

accordance with 14 CFR 39.19 on any 

airplane to which the AMOC applies, notify 

the appropriate principal inspector in the 

FAA Flight Standards Certificate Holding 

District Office. 

Material Incorporated by Reference 

(l) You must use Boeing Special Attention 

Service Bulletin 737–57–1273, Revision 2, 

dated October 30, 2003; and Boeing Service 

Bulletin 737–57–1080, Revision 3, dated 

September 24, 1992; as applicable; 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 these 

documents in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207, for a copy 

of this service information. You may review 

copies at the Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street SW., room PL–401, Nassif 

Building, Washington, DC; on the Internet at 

http://dms.dot.gov; or at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at the NARA, call (202) 741–

6030, or go to http://www.archives.gov/ 

federal-register/cfr/ibr-locations.html. 

Issued in Renton, Washington, on 

September 26, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19871 Filed 10–4–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–20874; Directorate 

Identifier 2004–NM–279–AD; Amendment 

39–14311; AD 2005–20–17] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A319–100 Series Airplanes; Model 

A320–111 Series Airplanes; Model 

A320–200 Series Airplanes; and Model 

A321–100 and –200 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus airplane models, as specified 

above. This AD requires modifying the 

parking brake system to automatically 

restore the normal brake if the parking 

brake pressure decreases below a certain 

threshold. This AD results from a report 

of failure of the parking brake while the 

airplane was on the holding point of the 

runway before takeoff, leading to a 

runway departure. We are issuing this 

AD to ensure normal braking is 

available to prevent possible runway 

departure in the event of failure of the 

parking brake. 

DATES: This AD becomes effective 

November 9, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 9, 2005. 

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: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2141; 

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 would 

apply to certain Airbus Model A319, 

A320, and A321 series airplanes. That 

NPRM was published in the Federal 

Register on April 6, 2005 (70 FR 17351). 

That NPRM proposed to require 

modifying the parking brake system to 

automatically restore the normal 

parking brake if the parking brake 

pressure decreases below a certain 

threshold. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Support for the NPRM 

Two commenters support the actions 

required by the NPRM. 

Request To Cite Latest Service 

Information 

One commenter asks that we change 

the NPRM to refer to the latest revision 

of Airbus Service Bulletin A320–32–

1201, which is Revision 02, dated 

February 1, 2005. Airbus Service 

Bulletin A320–32–1201, Revision 01, 

dated May 29, 2002, was referenced in 

the NPRM as the appropriate source of 

service information for accomplishing 

the specified modification. The 

commenter states that Revision 02