Federal Register / Vol. 71, No. 8 / Thursday, January 12, 2006 / Rules and Regulations 1947 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22289; Directorate 

Identifier 2005–NM–101–AD; Amendment 

39–14446; AD 2006–01–07] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–100, 747–100B, 747–200B, 

747–200C, 747–200F, 747–400F, 747SR, 

and 747SP 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 747–100, 747–100B, 747–

200B, 747–200C, 747–200F, 747–400F, 

747SR, and 747SP series airplanes, 

without a stretched upper deck or 

stretched upper deck modification. This 

AD requires detailed and highfrequency eddy current inspections for 

cracks of each affected tension tie and 

of the surrounding structure, and related 

investigative and corrective actions if 

necessary. This AD results from a report 

of a crack in the tension tie at the body 

station 820 frame connection, and 

cracks found on the Boeing 747SR 

fatigue-test airplane in both the tension 

ties and frames at the tension tie to 

frame connections at body stations 800, 

820, and 840. We are issuing this AD to 

find and fix cracks in the tension ties, 

which could lead to cracks in the skin 

and body frame and result in rapid inflight depressurization of the airplane. 

DATES: This AD becomes effective 

February 16, 2006. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of February 16, 2006. 

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: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 917–6437; 

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 747–100, 

747–100B, 747–200B, 747–200C, 747–

200F, 747–400F, 747SR, and 747SP 

series airplanes, without a stretched 

upper deck or stretched upper deck 

modification. That NPRM was 

published in the Federal Register on 

September 6, 2005 (70 FR 52945). That 

NPRM proposed to require detailed and 

high-frequency eddy current inspections 

for cracks at the outboard ends of each 

affected tension tie and of the 

surrounding structure, and related 

investigative and corrective actions if 

necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Request to Remove References to 

‘‘Outboard Ends’’

The commenter, the airplane 

manufacturer, requests that we remove 

the phrase ‘‘at the outboard ends’’ when 

referring to the tension ties and their 

surrounding structure. The commenter 

states that making this change would 

clarify that the inspection of the affected 

tension ties is from end to end. The 

commenter states that this change is 

consistent with Boeing Special 

Attention Service Bulletin 747–53–

2502, dated April 21, 2005, which 

specifies inspections from end to end of 

each applicable tension tie. The 

commenter requests that we remove the 

reference ‘‘at the outboard ends’’ from 

the title of the NPRM, the ‘‘Summary’’

section, the ‘‘Relevant Service 

Information’’ section, and paragraph (f). 

We agree with the commenter. It is 

our intention that operators inspect the 

affected tension ties and their 

surrounding structure in accordance 

with the special attention service 

bulletin. We carried over the phrase ‘‘at 

the outboard ends’’ from the ‘‘Action’’

and ‘‘Description’’ paragraphs of the 

special attention service bulletin. To 

avoid confusion, we have removed all 

appearances of this phrase from the 

final rule. We have changed paragraph 

(f) and the ‘‘Summary’’ section. We have 

not changed the ‘‘Relevant Service 

Information’’ section since that section 

of the preamble does not reappear in the 

final rule. We have also not changed the 

title of the NPRM because we do not 

give titles to NPRMs. We have retained 

the reference to the outboard ends in the 

‘‘Discussion’’ section of the final rule 

because that section quotes the NPRM 

as it appeared originally in the Federal 

Register. 

Request to Correct Paragraph Citations 

The same commenter notes that there 

are two typographical errors in 

paragraph (g) of the NPRM, the 

Alternative Methods of Compliance 

(AMOCs)’’ paragraph. The commenter 

points out that the references to 

paragraphs (g)(1)(i) and (g)(2)(ii) should 

refer to paragraphs (g)(3)(i) and (g)(3)(ii). 

We agree with the commenter. As 

noted below under ‘‘Clarification of 

AMOC Paragraph,’’ we have also 

clarified paragraph (g) of the final rule 

to add a new paragraph (g)(2). 

Therefore, we have corrected the 

references in the final rule as requested, 

but the new references are to paragraphs 

(g)(4)(i) and (g)(4)(ii). 

Clarification of 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 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Interim Action 

We consider this proposed AD 

interim action. The manufacturer is 

currently developing a modification that 

will address the unsafe condition 

identified in this AD. Once this 

modification is developed, approved, 

and available, we may consider 

additional rulemaking. 

Costs of Compliance 

There are about 458 airplanes of the 

affected design in the worldwide fleet. 

This AD affects about 141 airplanes of 


rwilkins on PROD1PC63 with RULES
1948 Federal Register / Vol. 71, No. 8 / Thursday, January 12, 2006 / Rules and Regulations 

U.S. registry. The inspections take about 

8 work hours per tension tie location. 

There are between 8 and 12 tension tie 

locations on each airplane, depending 

on the airplane’s configuration. The 

average labor rate is $65 per work hour. 

Based on these figures, the estimated 

cost of the AD for U.S. operators is 

between $586,560 and $879,840, or 

between $4,160 and $6,240 per airplane, 

per inspection cycle. 

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): 

2006–01–07 Boeing: Amendment 39–14446. 

Docket No. FAA–2005–22289; 

Directorate Identifier 2005–NM–101–AD. 

Effective Date 

(a) This AD becomes effective February 16, 

2006. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 747–

100, 747–100B, 747–200B, 747–200C, 747–

200F, 747–400F, 747SR, and 747SP series 

airplanes, certificated in any category; 

without a stretched upper deck or stretched 

upper deck modification; as identified in 

Boeing Special Attention Service Bulletin 

747–53–2502, dated April 21, 2005. 

Unsafe Condition 

(d) This AD results from a report of a crack 

in the tension tie at the body station 820 

frame connection, and cracks found on the 

Boeing 747SR fatigue-test airplane in both 

the tension ties and frames at the tension tie 

to frame connections at body stations 800, 

820, and 840. We are issuing this AD to find 

and fix cracks in the tension ties, which 

could lead to cracks in the skin and body 

frame and result in rapid in-flight 

depressurization 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. 

Repetitive Inspections and Corrective 

Actions 

(f) At the applicable time in paragraph 

(f)(1) or (f)(2) of this AD: Do detailed and 

high-frequency eddy current inspections for 

cracking of each affected tension tie and of 

the surrounding structure. If any cracking is 

found: Before further flight, do all applicable 

corrective and related investigative actions. 

Do all actions in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53–

2502, dated April 21, 2005. Where the special 

attention service bulletin specifies to contact 

Boeing for repair instructions: Before further 

flight, repair the area using a method 

approved in accordance with paragraph (g) of 

this AD. 

(1) For airplanes identified in the special 

attention service bulletin as Groups 1, 3, and 

6 airplanes: Do the first inspections before 

the accumulation of 20,000 total flight cycles, 

or within 1,000 flight cycles after the 

effective date of this AD, whichever occurs 

later; and repeat the inspections thereafter at 

intervals not to exceed 4,000 flight cycles. 

(2) For airplanes identified in the special 

attention service bulletin as Group 2, 4, and 

5 airplanes: Do the first inspections before 

the accumulation of 17,000 total flight cycles, 

or within 1,000 flight cycles after the 

effective date of this AD, whichever occurs 

later; and repeat the inspections thereafter at 

intervals not to exceed 3,000 flight cycles. 

Alternative Methods of Compliance 

(AMOCs) 

(g)(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) 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. 

(3) 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 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) Certain actions required by paragraph 

(f) of this AD are AMOCs for certain 

requirements in the ADs identified in 

paragraphs (g)(4)(i), (g)(4)(ii), and (g)(4)(iii) of 

this AD. All provisions of the referenced 

ADs, including applicable post-modification 

inspection thresholds, remain fully 

applicable and must be complied with. 

(i) Repairs of the aft tension tie channels 

done in accordance with this AD are AMOCs 

for the repair requirements of paragraph A. 

of AD 84–19–01, amendment 39–4913, and 

paragraphs (a)(2) and (b)(2) of AD 94–13–06, 

amendment 39–8946. 

(ii) The inspection requirements of this AD 

are AMOCs for the post-modification 

inspection requirements of paragraph B. of 

AD 84–19–01, and paragraph (b) of AD 94–

13–06. 

(iii) The inspection requirements of this 

AD are AMOCs for the inspections of 

structural significant item (SSI) F–19A of 

Boeing Supplemental Structural Inspection 

Document D6–35022, Revision G, dated 

December 2000, as required by paragraphs (c) 

and (d) of AD 2004–07–22, amendment 39–

13566. 

Material Incorporated by Reference 

(h) You must use Boeing Special Attention 

Service Bulletin 747–53–2502, dated April 

21, 2005, to perform the actions that are 

required by this AD, unless the AD specifies 


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Federal Register / Vol. 71, No. 8 / Thursday, January 12, 2006 / Rules and Regulations 1949 

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 

December 30, 2005. 

Linda Navarro, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 06–183 Filed 1–11–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22053; Directorate 

Identifier 2004–NM–74–AD; Amendment 39–

14449; AD 2006–01–10] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

Series Airplanes, and Model C4–605R 

Variant F Airplanes (Collectively Called 

A300–600 Series Airplanes); and 

Airbus Model A310 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 airplanes, listed above. This AD 

requires installing two-stage relays in 

the electronics rack (90VU), and 

performing related corrective and 

investigative actions. This AD results 

from reports of inadvertent rudder trim 

activation when the autopilot is on. We 

are issuing this AD to prevent 

inadvertent trim activation when the 

autopilot is on and the slats are 

extended, which could result in rudder 

activation when the autopilot is turned 

off. 

DATES: This AD becomes effective 

February 16, 2006. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of February 16, 2006. 

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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2125; 

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 A300 B4–

600, B4–600R, and F4–600R series 

airplanes, and Model C4–605R Variant F 

airplanes (collectively called A300–600 

series airplanes); and Airbus Model 

A310 series airplanes. That NPRM was 

published in the Federal Register on 

August 10, 2005 (70 FR 46437). That 

NPRM proposed to require installing 

two-stage relays in the electronics rack 

(90VU), and performing related 

corrective and investigative actions. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Support for the Proposed Rule 

Several commenters support the 

intent of the proposed AD. 

Request To Change Applicability 

One commenter, the airplane 

manufacturer, requests that we revise 

the applicability of the proposed AD to 

exclude airplanes on which Airbus 

Modification 11442 has been 

accomplished. 

We agree with the commenter. The 

requested change would clarify the 

applicability for operators and be in line 

with the applicability of the parallel 

French airworthiness directive. We have 

revised paragraph (c) of the AD to 

exclude these airplanes. 

Request To Identify Certain Part 

Numbers 

One commenter requests that the 

parts to be installed be identified in the 

proposed AD by manufacturer or part 

number. The commenter assumes that 

specific part numbers are identified in 

the referenced service information; 

however, since such information is not 

generally available to the public, it is 

not possible for the commenter to 

determine precisely which relays are to 

be installed. 

The same commenter also requests 

that the proposed AD provide for the 

possible existence of approved PMA 

parts by appending the phrase ‘‘or FAAapproved equivalent part number’’ to 

the part number of the part required to 

be installed. The commenter states that 

because it cannot determine which 

relays are to be installed, it is unable to 

identify if any possible alternatives 

approved under section 21.303 of the 

Federal Aviation Regulations (14 CFR 

21.303) exist. The commenter notes that 

airframe manufacturers, particularly 

foreign-based manufacturers, do not 

consider the impact of 14 CFR 21.303 in 

the creation of their service bulletins. 

Therefore, service documents can, and 

often do, create conditions that ‘‘seek to 

contravene existing law’’ by mandating 

the installation of a certain partnumbered part to the exclusion of all 

other parts that may now or in the 

future exist as FAA-approved 

alternatives. 

We do not concur with the 

commenter’s requests. Accomplishing 

the requirements of this AD involves 

installing two-stage relays in the 

electronics rack (90VU). Part numbers 

associated with accomplishing the 

installation are listed in the service 

bulletins referenced in this AD as the 

appropriate sources of service 

information. We find that it is 

impractical for us to list these numerous 

part numbers in the AD. 

However, the commenter’s remarks 

are timely in that the Transport 

Airplane Directorate currently is in the 

process of reviewing the issue of 

addressing PMA parts in ADs as that 

issue applies to transport category 

airplanes. Once we have thoroughly 

examined all aspects of this issue and 

have made a final determination, we 

will consider whether our policy needs 

to be revised. We consider that to delay 

this AD action would be inappropriate, 

since we have determined that an 


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