This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

5969 

Vol. 71, No. 24 

Monday, February 6, 2006 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22425; Directorate 

Identifier 2005–NM–066–AD; Amendment 

39–14468; AD 2006–03–04] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Model DC–8–33, DC–8–51, 

DC–8–53, DC–8–55, DC–8F–54, DC–8F– 

55, DC–8–63, DC–8–62F, DC–8–63F, 

DC–8–71, DC–8–73, DC–8–71F, DC–8– 

72F, and DC–8–73F 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 

transport category airplanes, identified 

above. 

This AD requires repetitive 

inspections for cracks of the doorjamb 

corners of the main cabin cargo door, 

and repair if necessary. This AD also 

provides an optional preventive 

modification that extends certain 

repetitive intervals. This AD results 

from reports of cracks in the fuselage 

skin at the corners of the doorjamb for 

the main cabin cargo door. We are 

issuing this AD to detect and correct 

fatigue cracks in the fuselage skin, 

which could result in rapid 

decompression of the airplane. 

DATES: This AD becomes effective 

March 13, 2006. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of March 13, 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, Long Beach Division, 3855 

Lakewood Boulevard, Long Beach, 

California 90846, Attention: Data and 

Service Management, Dept. C1–L5A 

(D800–0024), for service information 

identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Jon 

Mowery, Aerospace Engineer, Airframe 

Branch, ANM–120L, FAA, Los Angeles 

Aircraft Certification Office, 3960 

Paramount Boulevard, Lakewood, 

California 90712–4137; telephone (562) 

627–5322; fax (562) 627–5210. 

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 McDonnell Douglas 

Model DC–8–33, DC–8–51, DC–8–53, 

DC–8–55, DC–8F–54, DC–8F–55, DC–8– 

63, DC–8–62F, DC–8–63F, DC–8–71, 

DC–8–73, DC–8–71F, DC–8–72F, and 

DC–8–73F airplanes. That NPRM was 

published in the Federal Register on 

September 16, 2005 (70 FR 54674). That 

NPRM proposed to require repetitive 

inspections for cracks of the doorjamb 

corners of the main cabin cargo door, 

and repair if necessary. That NPRM also 

proposed an optional preventive 

modification that extends certain 

repetitive intervals. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment received. 

Request to Refer to Inspections in 

Service Bulletin 

The commenter requests that we 

change paragraph (f) of the NPRM to 

refer to the inspections in Paragraph 

1.E., Table 1, of Boeing Service Bulletin 

DC8–53–079, Revision 01, dated June 

26, 2002, rather than using the current 

wording of paragraph (f). As proposed 

in the NPRM, paragraph (f) states: ‘‘Do 

detailed, high frequency eddy current, 

and radiographic inspections, as 

applicable * * * ,’’ which the 

commenter states can be interpreted to 

require that all inspection types be 

accomplished for the main cabin cargo 

door jamb corners. The commenter 

states that referring to Paragraph 1.E., 

Table 1, would clarify the intent of the 

required inspection techniques. The 

commenter also notes that this change 

would be consistent with the wording in 

two other ADs related to door jamb 

corners: AD 2000–20–08, amendment 

39–11919, for passenger and service 

door jambs; and AD 2005–18–07, 

amendment 39–14247, for the lower 

cargo door jamb. 

We agree with the commenter. The 

requested change clarifies the intent of 

the inspection techniques, and is also 

consistent with the wording in similar 

ADs. We have revised paragraph (f) of 

the final rule to include this change. We 

have also deleted Note 1, which 

describes an inspection technique that 

is no longer mentioned in the AD. 

Clarification of Paragraph (g)(2) 

We have revised paragraph (g)(2) of 

this action to clarify that, for any corner 

where any crack is greater than 2.50 

inches in length, the repair should be 

done using a method approved in 

accordance with the procedures 

specified in paragraph (k), rather than 

just in accordance with paragraph (k). 

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 comment 

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. 


wwhite on PROD1PC65 with RULES
5970 Federal Register / Vol. 71, No. 24 / Monday, February 6, 2006 / Rules and Regulations 

Costs of Compliance 

There are about 225 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. The average labor 

rate is $65 per hour. 

ESTIMATED COSTS

Action Work hours Parts Cost per airplane Number of U.S.-registered airplanes Fleet Cost 

Inspection, per inspection cycle.20 None ............................ $1,300, per inspection 

cycle.

166 .............................. $215,800, per inspection cycle. 

Optional preventive 

modification (per corner).

80 $26,881 to $30,913 

(per corner, depending on airplane configuration).

$32,081 to $36,113 ..... Up to 166 .................... Up to between 

$5,325,446 and 

$5,994,758 (for one 

corner). 

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): 

2006–03–04 McDonnell Douglas: 

Amendment 39–14468. Docket No. 

FAA–2005–22425; Directorate Identifier 

2005–NM–066–AD. 

Effective Date 

(a) This AD becomes effective March 13, 

2006. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to McDonnell Douglas 

Model DC–8–33, DC–8–51, DC–8–53, DC–8–

55, DC–8F–54, DC–8F–55, DC–8–63, DC–8–

62F, DC–8–63F, DC–8–71, DC–8–73, DC–8–

71F, DC–8–72F, and DC–8–73F airplanes, 

certificated in any category; as identified in 

Boeing Service Bulletin DC8–53–079, 

Revision 01, dated June 26, 2002. 

Unsafe Condition 

(d) This AD results from reports of cracks 

in the fuselage skin at the corners of the 

doorjamb for the main cabin cargo door. We 

are issuing this AD to detect and correct 

fatigue cracks in the fuselage skin, which 

could result in rapid decompression 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. 

Inspections 

(f) At the applicable time in paragraph 

(f)(1) or (f)(2) of this AD: Do the applicable 

inspections for cracking of the doorjamb 

corners of the main cabin cargo door in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin DC8–

53–079, Revision 01, dated June 26, 2002; the 

applicable inspections are specified in Table 

1 of Paragraph 1.E. ‘‘Compliance’’ of the 

service bulletin. Except as provided by 

paragraphs (g) and (h) of this AD, repeat the 

inspections thereafter at intervals not to 

exceed the applicable intervals specified in 

Table 1 of Paragraph 1.E. ‘‘Compliance’’ of 

the service bulletin. 

(1) For airplanes that have been converted 

from passenger to cargo under Amended 

Type Certificate Data Sheet 4A25, Notes 25 

and 26, and McDonnell Douglas 

Supplemental Type Certificates SA3749WE 

and SA3403WE: Within 15,000 flight cycles 

after the conversion; or within 12 months 

after the effective date of this AD; whichever 

occurs later. 

(2) For airplanes that have not been 

converted from passenger to cargo: Before the 

accumulation of 15,000 total flight cycles, or 

within 3,000 flight cycles after the effective 

date of this AD, whichever occurs later. 

Corrective Actions and New Repetitive 

Intervals 

(g) If any crack is found during any 

inspection required by this AD, before further 

flight: Do the applicable action in paragraph 

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

the Accomplishment Instructions of Boeing 

Service Bulletin DC8–53–079, Revision 01, 

dated June 26, 2002. 

(1) For any corner where all cracks are 2.50 

inches or less in length, install an external 

doubler in accordance with the service 

bulletin: Before the accumulation of 17,000 

flight cycles after the installation, do the next 

inspection of that corner as specified in 

paragraph (f) of this AD. Repeat the 

inspections in paragraph (f) of this AD for 

that corner thereafter at intervals not to 

exceed 4,400 flight cycles. 

(2) For any corner where any crack is 

greater than 2.50 inches in length, repair the 


wwhite on PROD1PC65 with RULES
Federal Register / Vol. 71, No. 24 / Monday, February 6, 2006 / Rules and Regulations 5971 

crack using a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

Optional Preventive Modification 

(h) Installing an external doubler on a 

corner in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin DC8–53–079, Revision 01, 

dated June 26, 2002, terminates the repetitive 

inspection intervals of paragraph (f) of this 

AD for that corner. Before the accumulation 

of 17,000 flight cycles after the installation: 

Do the next inspection of that corner, as 

specified in paragraph (f) of this AD. Repeat 

the inspections in paragraph (f) of this AD for 

that corner thereafter at intervals not to 

exceed 4,400 flight cycles. 

No Reporting Required 

(i) Although the service bulletin referenced 

in this AD specifies to submit certain 

information to the manufacturer, this AD 

does not include that requirement. 

Actions Accomplished In Accordance With 

Previous Issue of Service Bulletin 

(j) Actions accomplished before the 

effective date of this AD in accordance with 

McDonnell Douglas Service Bulletin C8–53–

079, dated January 31, 2001, are acceptable 

for compliance with the corresponding action 

in this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Los Angeles 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, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane and 14 

CFR 25.571, Amendment 45, and the 

approval must specifically refer to this AD. 

(4) Inspections required by this AD of 

specified areas of Principal Structural 

Element (PSE) 53.08.044 are acceptable for 

compliance with the applicable requirements 

of paragraphs (a) and (b) of AD 93–01–15, 

amendment 39–8469 (58 FR 5576, January 

22, 1993). The remaining areas of the affected 

PSEs must be inspected and repaired as 

applicable, in accordance with AD 93–01–15. 

Material Incorporated by Reference 

(l) You must use Boeing Service Bulletin 

DC8–53–079, Revision 01, dated June 26, 

2002, 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, Long 

Beach Division, 3855 Lakewood Boulevard, 

Long Beach, California 90846, Attention: 

Data and Service Management, Dept. C1–L5A 

(D800–0024), 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 January 

24, 2006. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 06–987 Filed 2–3–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21702; Directorate 

Identifier 2005–NM–024–AD; Amendment 

39–14473; AD 2006–03–09] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200 and –300 Series Airplanes, 

A340–200 and –300 Series Airplanes, 

and A340–541 and –642 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 Model A330–200 and –300 series 

airplanes, A340–200 and –300 series 

airplanes, and A340–541 and –642 

airplanes. This AD requires repetitive 

borescope inspections of the left and 

right fuel tanks of the trimmable 

horizontal stabilizers (trim tanks) for 

detached or damaged float valves; 

related investigative/corrective actions 

if necessary; and the eventual 

replacement of all float valves in the left 

and right trim tanks with new, 

improved float valves, which terminates 

the need for the repetitive inspections. 

This AD also requires repetitive 

replacement of certain new, improved 

float valves. This AD results from 

reports of detached and damaged float 

valves in the trim tanks. We are issuing 

this AD to prevent, in the event of a 

lightning strike to the horizontal 

stabilizer, sparking of metal parts and 

debris from detached and damaged float 

valves, or a buildup of static electricity, 

which could result in ignition of fuel 

vapors and consequent fire or explosion. 

DATES: This AD becomes effective 

March 13, 2006. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of March 13, 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: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2797; 

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 A330 and 

A340 series airplanes. That NPRM was 

published in the Federal Register on 

June 29, 2005 (70 FR 37296). That 

NPRM proposed to require repetitive 

borescope inspections of the left and 

right fuel tanks of the trimmable 

horizontal stabilizers (trim tanks) for 

detached or damaged float valves; 

related investigative/corrective actions 

if necessary; and the eventual 

replacement of all float valves in the left 

and right trim tanks with new, 

improved float valves, which terminates 

the need for the repetitive inspections. 

That NPRM also proposed to require 

repetitive replacement of certain new, 

improved float valves. 


wwhite on PROD1PC65 with RULES